A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger and a second relatively large low pressure (LP) turbocharger. The turbine of the LP turbocharger is connected in series downstream of the turbine of the HP turbocharger. A first exhaust bypass flow passage provides a bypass flow path around the HP turbine. A second exhaust bypass flow passage provides a bypass flow path around the LP turbine. A rotary valve is located at a junction of the first and second bypass flow passages and a first exhaust gas flow passage. The rotary valve comprises a valve rotor which is rotatable selectively to permit or block flow to the LP turbine and to permit or block flow to the first and second bypass paths.
F02D 23/00 - Controlling engines characterised by their being supercharged
F02B 37/18 - Control of the pumps by bypassing exhaust
F02B 37/00 - Engines characterised by provision of pumps driven at least for part of the time by exhaust
F02B 37/013 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in series
F16K 11/06 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only sliding valves
A compressor for compressing a gas, the compressor comprising: a housing having an axial inlet and an annular outlet volute; an impeller wheel including a plurality of blades, the wheel being rotatably mounted within the housing between the inlet and outlet volute; the axial inlet being defined by a tubular inducer portion of the housing and the annular outlet volute being defined by an annular diffuser passage surrounding the impeller, the diffuser having an annular outlet communicating with the outlet volute; the housing having an inner wall defining a surface located in close proximity to radially outer edges of the impeller blades which sweep across the surface as the impeller wheel rotates; wherein the compressor housing incorporates at least one section comprised of a deformable, energy absorbing material arranged to deform and absorb energy generated as a result of impeller wheel failure. A turbine incorporating similar deformable, energy absorbing materials is also described, as are turbochargers incorporating such a compressor and/or turbine.
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02C 6/12 - Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
F04D 29/42 - CasingsConnections for working fluid for radial or helico-centrifugal pumps
A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger (1) and a second relatively large low pressure (LP) turbocharger (2). The turbine (6) of the LP turbocharger (2) is connected in series downstream of the turbine (4) of the HP turbocharger (1) in a first exhaust gas passage (11). An exhaust bypass flow passage (12) provides a bypass flow path around the HP turbine (4). A rotary valve (8) is located at a junction of the bypass flow passage (12) and a first exhaust gas flow passage (11). The rotary valve (8) comprises a valve rotor (19) which is rotatable to selectively permit or block flow to the LP turbine (6) from either the first exhaust gas passage (11) or the bypass gas passage (12).
F02B 33/40 - Engines with pumps other than of reciprocating-piston type with rotary pumps of non-positive-displacement type
F01D 25/24 - CasingsCasing parts, e.g. diaphragms, casing fastenings
F02M 26/08 - EGR systems specially adapted for supercharged engines for engines having two or more intake charge compressors or exhaust gas turbines, e.g. a turbocharger combined with an additional compressor
F02M 26/10 - Constructional details, e.g. structural combinations of EGR systems and supercharger systemsArrangement of the EGR and supercharger systems with respect to the engine having means to increase the pressure difference between the exhaust and intake system, e.g. venturis, variable geometry turbines, check valves using pressure pulsations or throttles in the air intake or exhaust system
A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger and a second relatively large low pressure (LP) turbocharger. The turbine of the LP turbocharger is connected in series downstream of the turbine of the HP turbocharger. A first exhaust bypass flow passage provides a bypass flow path around the HP turbine. A second exhaust bypass flow passage provides a bypass flow path around the LP turbine. A rotary valve is located at a junction of the first and second bypass flow passages and a first exhaust gas flow passage. The rotary valve comprises a valve rotor which is rotatable selectively to permit or block flow to the LP turbine and to permit or block flow to the first and second bypass paths.
F02B 37/18 - Control of the pumps by bypassing exhaust
F02D 9/16 - Throttle valves specially adapted thereforArrangements of such valves in conduits having slidably-mounted valve-membersThrottle valves specially adapted thereforArrangements of such valves in conduits having valve-members movable longitudinally of conduit the members being rotatable
F02B 37/00 - Engines characterised by provision of pumps driven at least for part of the time by exhaust
F02B 37/013 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in series
F02B 37/16 - Control of the pumps by bypassing charging air
F02M 26/08 - EGR systems specially adapted for supercharged engines for engines having two or more intake charge compressors or exhaust gas turbines, e.g. a turbocharger combined with an additional compressor
A turbocharger system comprises a first relatively small turbocharger and a second relatively large turbocharger connected in series and an exhaust gas flow control valve. The exhaust control valve has an inlet port communicating with the exhaust gas flow upstream of the first turbine a first outlet port communicating with the exhaust flow downstream of said first turbine but upstream of said second turbine, and a second outlet port communicating with the exhaust flow downstream of said second turbine. The valve is operable to selectively permit or block flow through the first and second outlet ports.
F02B 39/00 - Component parts, details, or accessories relating to driven charging or scavenging pumps, not provided for in groups
F02B 37/18 - Control of the pumps by bypassing exhaust
F02B 37/16 - Control of the pumps by bypassing charging air
F02B 37/013 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in series
F02B 37/007 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in parallel
A variable geometry turbine comprises: a turbine wheel in a housing for rotation about a turbine axis; an annular inlet passage defined between respective radial inlet surfaces of first and second wall members, at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage; an array of vanes extending across the inlet passage, said vanes being connected to said first wall member; a complementary array of vane slots defined by the second wall member, said vane slots configured to receive said vanes to accommodate relative movement between the first and second wall members; the second wall member comprising at least two axially adjacent co-axial plates, a first plate defining a first array of openings which overlie a second array of openings defined by a second plate so as to define said array of vane slots, said first plate being fixed to said second plate.
A variable geometry turbine comprises: a turbine wheel in a housing assembly defining a radial gas flow inlet passage; an annular wall member which is displaceable to control gas flow through the inlet passage; and a linkage mechanism comprising at least one actuating member operably connected to the annular wall member to control displacement of the wall member. The actuating member has a terminal portion defining a radially extending flange and extends in a direction substantially parallel to the turbine axis through an aperture defined by a retaining member to locate the radially extending flange in between said retaining member and annular wall member. The terminal portion is contacted by the retaining member to connect the actuating member to the annular wall member. The aperture defines a clearance to accommodate displacement of the retaining member relative to the actuating member.
A method for assembling a variable geometry turbomachine with a bearing housing, an adjacent turbine housing, a turbine wheel rotating in the turbine housing about a turbine axis; an inlet passage upstream of the turbine wheel between inlet surfaces of first and second wall members, one wall member moveable along the turbine axis to vary the inlet passage size; vanes across the inlet passage connected to a first wall member; an array of vane slots defined by the second wall member to receive the vanes for relative movement between the wall members; the second wall member comprising a shroud defining vane slots; the second wall member supported by a support member retained by a mounting feature; the mounting feature being one of the bearing housings, the turbine housing, or the actuation element; and the shroud is fixed to the support member.
According to an embodiment of the present invention, there is provided a variable geometry turbine comprising: a turbine wheel mounted on a turbine shaft within a housing assembly for rotation about a turbine axis, the housing assembly defining a gas flow inlet passage upstream of the turbine wheel; an annular wall member defining a wall of the inlet passage and which is displaceable in a direction substantially parallel to the turbine axis to control gas flow through the inlet passage; at least one moveable rod operably connected via a first end of the rod to the annular wall member, the rod being moveable to control displacement of the annular wall member, the rod extending in a direction substantially parallel to the turbine axis; wherein the rod is provided with a region of reduced radius which extends only partly around the rod, the region of reduced radius being remote from a second end of the rod to which a component of an actuator assembly for moving the rod is connectable.
During engine braking of a turbocharged internal combustion engine, the exhaust gas pressure increases and this is used to pressurize the seals between the turbocharger shaft and the bearing housing so as to prevent oil leakage into the compressor housing. Immediately after engine braking, stored exhaust gas pressure is used to pressurize the seals at the turbine end so as to prevent oil leakage into the turbine housing. In an alternative arrangement the exhaust gas is used to generate a reduced pressure in the bearing housing to increase the pressure gradient across the seals.
F01L 13/06 - Modifications of valve-gear to facilitate reversing, braking, starting, changing compression ratio, or other specific operations for braking
A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between the passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, in other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width.
F04D 29/42 - CasingsConnections for working fluid for radial or helico-centrifugal pumps
F04D 17/02 - Radial-flow pumps specially adapted for elastic fluids, e.g. centrifugal pumpsHelico-centrifugal pumps specially adapted for elastic fluids having non-centrifugal stages, e.g. centripetal
F04D 29/68 - Combating cavitation, whirls, noise, vibration, or the likeBalancing by influencing boundary layers
A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between the passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, hi other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width.
A speed sensor for use in measuring the speed of rotation of a rotationally salient rotating member. The speed sensor comprises an electrode and a sensor circuit. The sensor circuit comprises a constant voltage source for supplying a voltage to the electrode to generate an electric field in a dielectric medium. A current detector detects current flow between the constant voltage source and the electrode due to perturbation of the electric field by passage of at least one salient feature of the rotating member through the electric field as the rotating member rotates. The current detector outputs a first signal modulated at a frequency corresponding to the frequency of perturbation of the electric field. The first signal is amplified to produce an amplified signal modulated at a frequency corresponding to the frequency of perturbation of the electric field.
G01B 7/30 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring angles or tapersMeasuring arrangements characterised by the use of electric or magnetic techniques for testing the alignment of axes
G01P 3/44 - Devices characterised by the use of electric or magnetic means for measuring angular speed
H02K 11/00 - Structural association of dynamo-electric machines with electric components or with devices for shielding, monitoring or protection
G01B 7/14 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring distance or clearance between spaced objects or spaced apertures
G01D 5/24 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage by varying capacitance
G01P 3/483 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals delivered by variable capacitance detectors
H03K 17/955 - Proximity switches using a capacitive detector
A turbomachine comprising a housing defining a bearing cavity and a turbine chamber separated by a first wall, a heat shield disposed between the first wall and the turbine wheel, a heat shield cavity defined between the first wall and the heat shield. The shaft extends through a passage defined in part by a first aperture in the wall and a second aperture in the heat shield. A first seal is provided between the shaft and the first aperture. The housing defines a first gas channel communicating with the heat shield cavity for connection to a pressure source for raising pressure within the heat shield cavity. A second channel is provided between the heat shield cavity and the passage, the second channel opening to the passage on the opposite side of the first seal to the bearing assembly. A second seal is provided between the shaft and the second aperture.
A turbocharger system comprises a first relatively small turbocharger and a second relatively large turbocharger connected in series and an exhaust gas flow control valve. The exhaust control valve has an inlet port communicating with the exhaust gas flow upstream of the first turbine a first outlet port communicating with the exhaust flow downstream of said first turbine but upstream of said second turbine, and a second outlet port communicating with the exhaust flow downstream of said second turbine. The valve is operable to selectively permit or block flow through the first and second outlet ports.
F02B 37/013 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in series
F02B 37/18 - Control of the pumps by bypassing exhaust
F02D 23/00 - Controlling engines characterised by their being supercharged
F02B 37/00 - Engines characterised by provision of pumps driven at least for part of the time by exhaust
F02B 37/007 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in parallel
F02B 37/16 - Control of the pumps by bypassing charging air
F02B 39/00 - Component parts, details, or accessories relating to driven charging or scavenging pumps, not provided for in groups
Sensor arrangement for measuring a rotation speed of a salient member of a rotatable body comprising a first electrode arrangement providing a first input, a second electrode arrangement providing a second input different from the first input, the first and second electrode arrangements configured so noise in the first and second inputs is substantially the same, and wherein variations in the first and second inputs are caused by rotation of the rotatable body and the salient member past the first and second electrode arrangements, an output arrangement for receiving the first and second inputs, and for providing an output proportional to a difference between the first and second inputs, and a retaining member for retaining one or more of the first and second electrode arrangements and output arrangement, the speed of rotation of the salient member measurable from a variation in the output caused by rotation of that salient member.
G01P 3/44 - Devices characterised by the use of electric or magnetic means for measuring angular speed
G01P 3/48 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
G01B 7/30 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring angles or tapersMeasuring arrangements characterised by the use of electric or magnetic techniques for testing the alignment of axes
F01D 17/06 - Arrangement of sensing elements responsive to speed
F02B 39/00 - Component parts, details, or accessories relating to driven charging or scavenging pumps, not provided for in groups
G01P 3/481 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals
G01P 3/483 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals delivered by variable capacitance detectors
Variable geometry turbomachine with a bearing housing, an adjacent turbine housing, a turbine wheel rotating in the turbine housing about a turbine axis; an inlet passage upstream of the turbine wheel between inlet surfaces of first and second wall members, one wall member moveable along the turbine axis to vary the inlet passage size; vanes across the inlet passage connected to a first wall member; an array of vane slots defined by the second wall member to receive the vanes for relative movement between the wall members; the second wall member comprising a shroud defining vane slots; the second wall member supported by a support member retained by a mounting feature; the mounting feature being one of the bearing housings, the turbine housing, or the actuation element; and the shroud is fixed to the support member so axial movement of the shroud relative to the support member is substantially prevented.
A compressor comprises an impeller wheel mounted within a housing defining an inlet and an outlet. The wheel has a plurality of vanes and is rotatable about an axis. The housing has an inner wall defining a surface located in close proximity to radially outer edges of the impeller vanes which sweep across said surface as the impeller wheel rotates about its axis. The inlet comprises a tubular wall extending away from the impeller wheel in an upstream direction. An enclosed chamber is defined between said inner wall and an outer wall and in communication with at least one opening in said in said inner wall. The outer wall is penetrated by at least one ventilation aperture that is designed to be connected via a conduit to a location upstream of the inlet and downstream of an air filter.
According to an aspect of the present invention, there is provided a turbocharger assembly, comprising: a turbocharger; one or more actuators for controlling a flow of fluid in, around, or associated with the operation of the turbocharger; control electronics for use in controlling actuation of the one or more actuators; and boost electronics configured to receive an input voltage, and to provide a boosted output voltage to the control electronics.
A turbine wheel mounted within a housing rotating about a turbine axis; a gas flow control passage upstream of the turbine wheel between a radial first surface of a movable wall member and a facing wall of the housing, the movable wall member comprising second and third surfaces opposing the first surface. The movable wall member moves in an axial direction to vary the size of the gas flow control passage. A first gas region of the turbine, being upstream of the gas flow control passage, includes a portion of the gas flow control passage; a second gas region of the turbine downstream of the gas flow control passage containing the turbine wheel; and a third gas region of the turbine downstream of the turbine wheel. The first gas region comprises the first and second surfaces, and the second gas region or third gas region comprises the third surface.
A variable geometry turbine comprising a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway and of vanes that are received in corresponding slots in the facing wall. Each vane major surface such that at a predetermined axial position of the nozzle ring relative to the facing wall the recess is in axial alignment with the slot and affords an exhaust gas leakage path through the inlet passageway. The recess is configured to reduce the efficiency of the turbine at small inlet gaps appropriate to engine braking or exhaust gas heating modes.
A rotating machine comprising such as an axial power turbine or a turbocharger has a housing with a bearing cavity and a chamber separated by a first wall. A shaft is rotatable about an axis in the bearing cavity, extends through an opening in the first wall and is mounted for rotation on a bearing assembly provided in the bearing cavity. An oil sealing arrangement including an oil diffuser device is arranged on the shaft for displacing oil away from the shaft as it rotates. This restricts the flow of oil to the opening. The oil diffuser device defines a diffuser passage between the bearing assembly and the first wall, the passage extending outwardly of the axis.
A piston ring for sealing gas flow past a sliding cylinder is provided at the interface of the turbine and bearing housings, and is axially close to the turbine inlet. A V-band or similar connection joins the turbine and bearing housings but it is axially further away from the turbine inlet. The piston ring is provided with a spacer element between it and the bearing housing that is at least partially thermally decoupled from the bearing housing.
A compressor wheel for a turbocharger comprising a central hub and a plurality of impeller blades extending outwardly from the hub. Each of the blades defines a leading edge, a trailing edge and a root portion which connects the blade to the hub. At least one of the blades has a surface provided with a variable thickness surface layer of a ceramic material. The leading edge of the blade is provided with a thicker surface layer of the ceramic material than the trailing edge of the blade, the root portion of the blade, or both the trailing edge and root portion of the blade.
A variable geometry turbomachine comprises a housing which defines a bearing housing and an adjacent turbine housing (1); a turbine wheel supported in the turbine housing for rotation about a turbine axis; and an annular inlet passage (9) upstream of said turbine wheel defined between respective inlet surfaces of first and second wall members. At least one of said first and second wall members is moveable by an actuation element along the turbine axis to vary the size of the inlet passage (9). The turbomachine also comprises an array of vanes extending across the inlet passage (9), said vanes being connected to said first wall member; and a complementary array of vane slots (30) defined by the second wall member, said vane slots (30) being configured to receive said vanes to accommodate relative movement between the first and second wall members. The second wall member comprises a shroud (29) which defines said vane slots (30); the second wall member being supported by a support member (33). A portion of the support member (33) is configured to be received by a corresponding mounting feature (28) such that the support member (33) is retained by the mounting feature (28). The mounting feature (28) is provided by one of the bearing housing, the turbine housing (1) or the actuation element; and the shroud (29) is fixed to the support member (33) such that axial movement of the shroud (29) relative to the support member (33) is substantially prevented.
A variable geometry turbine comprising: a housing; a turbine wheel supported within said housing for rotation about a turbine axis; an annular inlet passage within said housing upstream of said turbine wheel and defined between respective radial inlet surfaces of first and second wall members; an outlet passage within said housing downstream of said turbine wheel; an array of vanes extending across the inlet passage, said vanes being connected to said first wall member; at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage and/or at least one of said vanes being rotationally moveable about an axis that is substantially parallel to said turbine axis to vary the size of the inlet passage; wherein at least one particulate filter is provided within said housing at a location such that said particulate filter can be contacted by particulate matter flowing through said turbine during use.
F03B 11/08 - Parts or details not provided for in, or of interest apart from, groups for removing foreign matter, e.g. mud
F02B 37/22 - Control of the pumps by varying the cross-section of exhaust passages or air passages
F01N 3/021 - Exhaust or silencing apparatus having means for purifying, rendering innocuous, or otherwise treating exhaust for cooling, or for removing solid constituents of, exhaust by means of filters
F02B 37/24 - Control of the pumps by using pumps or turbines with adjustable guide vanes
F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
F02B 39/16 - Other safety measures for, or other control of, pumps
A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger and a second relatively large low pressure (LP) turbocharger. The turbine of the LP turbocharger is connected in series downstream of the turbine of the HP turbocharger. A first exhaust bypass flow passage provides a bypass flow path around the HP turbine. A second exhaust bypass flow passage provides a bypass flow path around the LP turbine. A rotary valve is located at a junction of the first and second bypass flow passages and a first exhaust gas flow passage. The rotary valve comprises a valve rotor which is rotatable selectively to permit or block flow to the LP turbine and to permit or block flow to the first and second bypass paths.
F02B 37/007 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in parallel
F02B 37/013 - Engines characterised by provision of pumps driven at least for part of the time by exhaust with exhaust-driven pumps arranged in series
F02B 37/00 - Engines characterised by provision of pumps driven at least for part of the time by exhaust
F02B 37/18 - Control of the pumps by bypassing exhaust
A variable geometry turbine comprises: a turbine wheel (5) in a housing (1) for rotation about a turbine axis, an annular inlet passage (9) defined between respective radial inlet surfaces of first and second wall members (11, 12), at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage; an array of vanes (14) extending across the inlet passage, said vanes being connected to said first wall member; a complementary array of vane slots (28) defined by the second wall member, said vane slots configured to receive said vanes to accommodate relative movement between the first and second wall members; the second wall member comprising at least two axially adjacent co-axial plates (29, 30), a first plate (29) defining a first array of openings which overlie a second array of openings defined by a second plate (30) so as to define said array of vane slots, said first plate being fixed to said second plate.
A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis. The housing defines an annular inlet passage around an inducer portion of the turbine wheel and an outlet passage including a tubular wall disposed around an exducer portion of the turbine wheel; the inlet passage is defined between first and second radial inlet surfaces, one of the inlet surfaces being defined by a moveable wall member and the other of the inlet surfaces being defined by a facing wall of said housing. The moveable wall member is moveable relative to the facing wall of the housing along the turbine axis to vary the size of the inlet passageway. The moveable wall member is displaceably mounted within an annular cavity defined between the tubular wall and a surrounding wall of the housing.
A variable geometry turbine comprises a turbine wheel (5) supported in a housing (1) for rotation about a turbine axis. An annular inlet passage (9) is defined between first and second radial inlet surfaces, one of said first and second inlet surfaces being defined by a moveable wall member (40). A substantially annular array of vanes (41) is provided which extend across the inlet passageway (9); each vane (41) being fixed to said first inlet surface. Each vane (41) has first and second major vane surfaces (45, 46) having a chordal length extending between a radially outer leading vane edge (47) and a radially inner trailing vane edge (48), the first major vane surface (45) facing generally away from the axis and the second major vane surface (46) facing generally towards the axis. A rib (43) extends across at least a substantial portion of the chordal length of at least one of the first and second major vane surfaces (45, 46) of one or more vanes (41) of the array.
Sensor arrangement for measuring a speed of rotation of a salient member of a rotatable body comprising a first electrode arrangement providing a first input, a second electrode arrangement providing a second input different from the first input, the first and second electrode arrangements being configured such that noise in the first and second inputs is substantially the same, and wherein variations in the first and second inputs are caused by rotation of the rotatable body and the salient member past the first and second electrode arrangements, an output arrangement for receiving the first and second inputs, and for providing an output proportional to a difference between the first input and the second inputs, and a retaining member for retaining one or more of the first and second electrode arrangements and output arrangement, the speed of rotation of the salient member being measurable from a variation in the output caused by rotation of that salient member
G01P 3/48 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
G01P 3/481 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals
G01P 3/483 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals delivered by variable capacitance detectors
F02B 37/18 - Control of the pumps by bypassing exhaust
F02C 6/12 - Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
F02D 41/00 - Electrical control of supply of combustible mixture or its constituents
A variable geometry turbine of the kind used in a turbocharger has a variable geometry element such as a nozzle ring that is operated by an actuator. The actuator comprises a motor which drives a cross-shaft in rotation. The cross-shaft in turn drives a pair of guide rods on which the nozzle ring is supported in translation so as to move the nozzle ring and control the width of the inlet passage of the turbine. The cross-shaft and guide rods are drivingly engaged by a rack and pinion or thread or another toothed or threaded formation suitable for converting rotational movement into translational movement. The cross-shaft can be located in close proximity to the guide rods and the output of the motor shaft so as to provide a compact package. Moreover, the torque required to resist movement of the nozzle ring in operation is much reduced in comparison to existing designs.
A variable geometry turbine comprises: a turbine wheel mounted within a housing assembly for rotation about a turbine axis, the housing assembly defining a radial gas flow inlet passage; an annular wall member defining one wall of the inlet passage and which is displaceable in a direction substantially parallel to the turbine axis to control gas flow through the inlet passage; and a linkage mechanism comprising at least one actuating member operably connected to the annular wall member to control displacement of the wall member. The actuating member extends in a direction substantially parallel to the turbine axis through an aperture defined by a retaining member such that a first bearing surface defined by the actuating member extending transverse to the turbine axis is contacted by a surface of the retaining member so as to connect the actuating member to the annular wall member. The aperture is appropriately dimensioned to define a clearance between a wall of the aperture and a portion of the actuating member located within the aperture so as to accommodate displacement of the retaining member, resulting from displacement of the annular wall member, relative to the actuating member.
A compressor for a turbocharger is supplied with crank case ventilation (CCV) gases from the engine which is turbocharged. The CCV gases are piped into an inlet of the compressor housing which supports an insert with an MWE structure. The MWE structure comprises an outer wall and an inner wall with a gas flow passage defined between them. At high r.p.m. of the compressor impeller air flows through the passage to provide more air volume to the impeller and at low r.p.m. excess air is bled out of the passage for recirculation. The CCV gases are directed to a position upstream of an inlet to the gas flow passage where they emerge through an outlet which may be defined in the insert. The CCV gases may be supplied to the outlet via a chamber defined between the insert and the compressor housing. The arrangement provides for improved mixing of CCV gases with the incoming air and does not compromise noise reduction.
F02B 33/44 - Passages conducting the charge from the pump to the engine inlet, e.g. reservoirs
F02B 25/06 - Engines having ports both in cylinder head and in cylinder wall near bottom of piston stroke the cylinder-head ports being controlled by working pistons, e.g. by sleeve-shaped extensions thereof
A variable geometry turbine comprises a turbine wheel (5) supported in a housing for rotation about a turbine axis with an annular inlet passageway (9) defined between a radial face of a nozzle ring (11) and a facing wall of the housing (10). The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway and has a circumferential array of vanes (20) that are received in corresponding slots (24) in the facing wall. A wastegate valve (15) is provided in a chamber behind the facing wall and gas bypasses the turbine through the chamber to the wastegate port (14) at high flow rates.
A compressor comprises an impeller wheel mounted within a housing defining an inlet and an outlet. The wheel has a plurality of vanes and is rotatable about an axis. The housing has an inner wall defining a surface located in close proximity to radially outer edges of the impeller vanes which sweep across said surface as the impeller wheel rotates about its axis. The inlet comprises inner and outer tubular walls extending away from the impeller wheel in an upstream direction and defining between them gas flow passage. A bleed passage between the gas flow passage and the impeller wheel is selectively opened and closed by movement of a sliding sleeve in a helical direction.
A turbocharger system comprises a first relatively small turbocharger and a second relatively large turbocharger connected in series and an exhaust gas flow control valve. The exhaust control valve has an inlet port communicating with the exhaust gas flow upstream of the first turbine a first outlet port communicating with the exhaust flow downstream of said first turbine but upstream of said second turbine, and a second outlet port communicating with the exhaust flow downstream of said second turbine. The valve is operable to selectively permit or block flow through the first and second outlet ports.
A rotating machine (1) comprising such as an axial power turbine or a turbocharger has a housing (5) with a bearing cavity (8) and a chamber separated by a first wall. A shaft (7) is rotatable about an axis in the bearing cavity, extends through an opening in the first wall (13) and is mounted for rotation on a bearing assembly (10) provided in the bearing cavity. An oil sealing arrangement (30) including an oil diffuser device (31) is arranged on the shaft for displacing oil away from the shaft as it rotates. This restricts the flow of oil to the opening. The oil diffuser device defines a diffuser passage (39) between the bearing assembly and the first wall, the passage extending outwardly of the axis.
A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel, an upstream axial compressor impeller wheel and an intermediate stator. The compressor housing has an inlet with inner and outer walls that define between them an MWE gas flow passage. An upstream opening defined by the flow passage provides communication between the passage and the intake and at least one first slot downstream of the upstream opening provides communication between the passage and the inner surface of the inner wall. The stator comprises a plurality of fixed vanes and is disposed in the inner wall of the inlet between the radial and axial impeller wheels. The position of the slot can be at one of several positions along the gas flow passage, in other embodiments there are second and third slots and the flow passage is divided into two parts. All the arrangements are designed to improve the compressor map width.
An oil control device inhibits the flow of oil along a shaft (8) rotating about an axis. The oil control device comprises an annular body (19) for rotation with said shaft (8) and includes a first face (30) extending generally radially from said axis. A second radially outer circumferential surface (40) is provided, extending generally axially. An oil slinging groove (32) extends into said body (19) and has a mouth (37) defined between a first circumferentially extending rim (38) and a second circumferentially extending rim (39). The second rim (39) is spaced both radially and axially from the first rim (38). The groove (32) is defined at least in part by a wall (34) which meets the first rim (38) at an acute angle to a radial plane. The groove (32) is also defined at least in part by a wall (35) which meets the second rim (39) at an acute angle to the direction of the axis.
a) separated by a first wall. A heat shield (72) is disposed between the first wall and the turbine wheel (77), a heat shield cavity (78) being defined between the first wall and the heat shield (72). The shaft (81) extends through a passage (85) defined at least in part by a first aperture (86) in said wall and a second aperture (87) in the heat shield (72). A first seal (88) is provided between the shaft (81) and said first aperture (86). The housing defines a first gas channel (79) communicating with the heat shield cavity (78) for connection to a pressure source for raising pressure within the heat shield cavity (78). A second channel (92) is provided between the heat shield cavity (78) and said passage (85), the second channel opening to said passage (85) on the opposite side of said first seal (88) to said bearing assembly (82). A second seal (89) is provided between the shaft (81) and said second aperture (87).
A compressor (1) has a housing (3) defining a gas inlet flow path and a gas outlet and a rotatable impeller wheel (2) between the gas inlet flow path and the gas outlet. The housing (3) has an inner wall (10) defining a surface (6) located in close proximity to radially outer edges of impeller wheel vanes (5) that sweep across said surface (6) as the impeller wheel (2) rotates. At least one opening (13) is provided in the inner wall (10) at the surface (6). A port (14) is provided in the compressor housing (3) in gas communication with the at least one opening (13) and for diverting gas in a direction away from the gas inlet flow path during relatively low gas flow rate conditions. A gas displacement device such as a pump (16) is disposed outside of the gas inlet flow path and connected to said port (14), the pump (16) being operable to remove gas selectively through the at least one opening (13) and the port (14) in a direction away from said gas inlet flow path.
A speed sensor for use in measuring the speed of rotation of a rotationally salient rotating member The speed sensor comprises an electrode and a sensor circuit. The sensor circuit comprises a constant voltage source for supplying a voltage to the electrode to generate an electric field in a dielectric medium. A current detector detects current flow between the constant voltage source and the electrode due to perturbation of the electric field by passage of at least one salient feature of the rotating member through the electric field as the rotating member rotates. The current detector outputs a first signal modulated at a frequency corresponding to the frequency of perturbation of the electric field. The first signal is amplified to produce an amplified signal modulated at a frequency corresponding to the frequency of perturbation of the electric field. The electrode voltage, the amplifier gain and the electrode position relative to the rotating member are selected such that modulation of the second signal is predominantly caused by perturbation of the electric field within the dielectric medium by the creation and/or movement of ions within the field.
G01P 3/48 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage
A turbocharger has a sealing arrangement between the turbocharger shaft and the bearing housing adjacent to the turbine and/or the compressor housings to restrict leaking of gas into the bearing housing. At least a pair of spaced sealing rings project from an annular surface of the bearing housing into corresponding annular recesses formed on the shaft. The trailing face of the second ring or the opposite surface of the recess has a plurality of radial grooves that define leak passages that serve to maintain a very small flow of gas from the turbine or compressor housing into the bearing housing. Alternatively there is a slot in the second ring to provide the leak passage. This ensures that there is a minimum gas flow so that a large pressure gradient is not applied across the second seal thereby avoiding wear, overheating and collapse of the ring.
A turbocharger bearing housing defines a bore in which the turbocharger shaft is mounted for rotation in journal bearings. Lubricating oil is delivered to the journal bearings and a residue is retained in reservoirs in which the journal bearings are located. Two fluid retaining members are disposed around the shaft, each forming a wall of the reservoir and being sealed to the bearing housing. The lubricating fluid reservoir is provided between the fluid retaining members to a depth that at least partially immerses the journal bearings even when the oil supply is interrupted. This ensures that there is sufficient oil to lubricate the bearings at engine start-up, thereby reducing the risk of wear.
A variable geometry turbine of the kind used in a turbocharger has a variable geometry element such as a nozzle ring or an annular array of swing vanes that is operated by an actuator. The actuator has an output shaft coupled to a transmission mechanism for moving the variable geometry element. A rotary sensor device coupled to the output shaft of the actuator has a sensor wheel with a stop, slip clutch mechanism and a rotary position sensor. The device converts movement of the actuator output shaft into rotation of the wheel and the sensor generates an output signal representative of the rotary position of the wheel to provide a value indicative of the position of the variable geometry element. The actuator is calibrated to the position of the variable geometry element by rotating the sensor wheel in a first rotational direction until the variable geometry element reaches the first limit position, then rotating the sensor wheel in a second direction until the variable geometry element reaches the second limit position. The value of the output signal is logged at one of these positions as a limit value. The sensor wheel is allowed to declutch in the event that it encounters the stop in either direction of rotation. The output signal is monitored and the limit value is deducted to determine the position of the variable geometry element.
A control system for controlling the supply of oil to a turbocharger fitted to an internal combustion comprises an oil supply valve (21) controlled by a controller (20) and at least one sensor (23-28) for monitoring a parameter associated with the existence or potential occurrence of a leak in the turbocharger oil supply, or of a condition potentially resulting in such a leak. The controller (20) is operable to determine the existence or possible occurrence of an oil leak in the turbocharger oil supply in response to a signal received from the sensor (23-28) and to close the oil supply control valve (21) in the event of said determination to cut off the oil supply to the turbocharger.
F02D 43/00 - Conjoint electrical control of two or more functions, e.g. ignition, fuel-air mixture, recirculation, supercharging or exhaust-gas treatment
During engine braking of a turbocharged internal combustion engine, the exhaust gas pressure increases and this is used to pressurize the seals between the turbocharger shaft and the bearing housing so as to prevent oil leakage into the compressor housing. Immediately after engine braking, stored exhaust gas pressure is used to pressurize the seals at the turbine end so as to prevent oil leakage into the turbine housing. In an alternative arrangement the exhaust gas is used to generate a reduced pressure in the bearing housing to increase the pressure gradient across the seals.
A variable geometry turbine has a gas inlet chamber and a gas flow inlet passage downstream of the inlet chamber and upstream of said turbine wheel. The inlet passage is defined between a moveable first wall and a second wall and an actuator is operable to control displacement of the first wall in order to vary the size of the gas flow inlet passage. A piston member defining the first wall or being connected to it is received in a piston chamber and serves to move the first wall as a result of displacement of the piston member in the piston chamber. A bypass passage defined in the housing and extends between the piston chamber and a location in the turbine upstream of the inlet passage for delivering gas to the piston chamber. The bypass passage is disposed such that gas introduced through the bypass passage pressurizes the chamber and applies a force to displace the piston member in a direction that causes the first wall to move towards the second wall. The gas, which may be the exhaust gas from an engine, thus serves to assist the operation of the actuator.
A variable geometry turbine comprising: a housing; a turbine wheel supported within said housing for rotation about a turbine axis; an annular inlet passage within said housing upstream of said turbine wheel and defined between respective radial inlet surfaces of first and second wall members; an outlet passage within said housing downstream of said turbine wheel; an array of vanes (429) extending across the inlet passage, said vanes being connected to said first wall member (425); at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage and/or at least one of said vanes being rotationally moveable about an axis that is substantially parallel to said turbine axis to vary the size of the inlet passage; wherein at least one particulate filter (431) is provided within said housing at a location such that said particulate filter can be contacted by particulate matter flowing through said turbine during use.
A variable geometry turbine comprises: a turbine wheel (5) in a housing (1) for rotation about a turbine axis,- an annular inlet passage (9) defined between respective radial inlet surfaces of first and second wall members (11, 12), at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage; an array of vanes (14) extending across the inlet passage, said vanes being connected to said first wall member; a complementary array of vane slots (28) defined by the second wall member, said vane slots configured to receive said vanes to accommodate relative movement between the first and second wall members; the second wall member comprising at least two axially adjacent co-axial plates (29, 30), a first plate (29) defining a first array of openings which overlie a second array of openings defined by a second plate (30) so as to define said array of vane slots, said first plate being fixed to said second plate.
The speed of rotation of a rotary member such as a compressor or turbine wheel of a turbocharger is determined by directing an ultrasonic signal into a blade cavity and receiving the reflected signal, which is amplitude modulated by virtue of the passage of the blades across the ultrasonic transducer. The received signal is demodulated to determine the frequency of amplitude modulation of the received signal caused by passage of blades between the first and second locations. This enables the speed of rotation to be calculated. The performance of the turbocharger can thus be optimised in the context of the overall engine system via an engine control module.
A compressor comprises an impeller wheel mounted within a housing defining an inlet and an outlet. The wheel has a plurality of vanes and is rotatable about an axis. The housing has an inner wall defining a surface located in close proximity to radially outer edges of the impeller vanes which sweep across said surface as the impeller wheel rotates about its axis. The inlet comprises a tubular wall extending away from the impeller wheel in an upstream direction. An enclosed chamber is defined between said inner wall and an outer wall and in communication with at least one opening in said in said inner wall. The outer wall is penetrated by at least one ventilation aperture that is designed to be connected via a conduit to a location upstream of the inlet and downstream of an air filter. The arrangement maintains the advantages of a conventional MWE structure and further improves the surge margin. In addition, the risk of debris being drawn into the compressor via the opening is eliminated.
A variable geometry turbine comprises a turbine wheel (38) supported in a housing (30) for rotation about a turbine axis. The housing (30) defines an annular inlet passage (36) around an inducer portion (37) of the turbine wheel (38) and an outlet passage including a tubular wall (37) disposed around an exducer portion (39) of the turbine wheel (38); the inlet passage (36) is defined between first and second radial inlet surfaces, one of the inlet surfaces being defined by a moveable wall member (144) and the other of the inlet surfaces being defined by a facing wall of said housing. The moveable wall member (44) is moveable relative to the facing wall of the housing along the turbine axis to vary the size of the inlet passageway (36). The moveable wall member (44) is displaceably mounted within an annular cavity (40) defined between the tubular wall (37) and a surrounding wall (42) of the housing (32).
A variable geometry turbine of the kind used in a turbocharger has a variable geometry element such as a nozzle ring that is operated by an actuator. The actuator comprises a motor which drives a cross-shaft in rotation. The cross-shaft in turn drives a pair of guide rods on which the nozzle ring is supported in translation so as to move the nozzle ring and control the width of the inlet passage of the turbine. The cross-shaft and guide rods are drivingly engaged by a rack and pinion or thread or another toothed or threaded formation suitable for converting rotational movement into translational movement. The cross-shaft can be located in close proximity to the guide rods and the output of the motor shaft so as to provide a compact package. Moreover, the torque required to resist movement of the nozzle ring in operation is much reduced in comparison to existing designs.
A variable geometry turbine comprises: a turbine wheel (5) mounted within a housing assembly (1) for rotation about a turbine axis, the housing assembly defining a radial gas flow inlet passage (9); an annular wall member (11) defining one wall of the inlet passage and which is displaceable in a direction parallel to the turbine axis to control gas flow through the inlet passage; and a linkage mechanism comprising at least one actuating member (16) operably connected to the annular wall member to control displacement of the wall member. The actuating member extends in a direction parallel to the turbine axis through an aperture (29) defined by a retaining member (24) such that a first bearing surface defined by the actuating member extending transverse to the turbine axis is contacted by a surface of the retaining member so as to connect the actuating member to the annular wall member. The aperture is dimensioned to define a clearance (30) between a wall of the aperture and a portion of the actuating member located within the aperture.
A turbomachine system comprises a first turbocharger comprising an exhaust gas flow first turbine for location in an exhaust path and a first compressor driven by said first turbine; a turbomachine for location in the exhaust path upstream or downstream of said first turbocharger and comprising an exhaust gas flow second turbine and a second compressor driven by said second turbine. The first turbine has an outlet that is in fluid communication with an inlet of the second turbine. One of said first and second turbines is a radial outflow turbine. The arrangement provides for a relatively compact package. The radial outflow turbine may have a particular structure in which there is provided a deflector member at or near its inlet for directing the gas outwards, a stator for introducing swirl and a downstream turbine rotor. A shroud is fixed to blades of the turbine rotor to prevent leakage and to provide additional structural rigidity.
A variable geometry turbine comprises a turbine wheel (5) supported in a housing (1) for rotation about a turbine axis. An annular inlet passage (9) is defined between first and second radial inlet surfaces, one of said first and second inlet surfaces being defined by a moveable wall member (40). A substantially annular array of vanes (41) is provided which extend across the inlet passageway (9); each vane (41) being fixed to said first inlet surface. Each vane (41) has first and second major vane surfaces (45, 46) having a chordal length extending between a radially outer leading vane edge (47) and a radially inner trailing vane edge (48), the first major vane surface (45) facing generally away from the axis and the second major vane surface (46) facing generally towards the axis. A rib (43) extends across at least a substantial portion of the chordal length of at least one of the first and second major vane surfaces (45, 46) of one or more vanes (41) of the array.
A hydraulic seal is defined between a rotating member such as a turbocharger shaft and a stationary member such as part of a bearing housing of a turbocharger. The members define a projecting annular disc that is received in an annular channel that is filled with hydraulic sealing fluid such as oil. Rotation of the rotary member applies a centrifugal force to the fluid thereby ensuring that it is retained in the channel between walls thereof and the disc. This annulus of fluid provides a hydraulic seal around the shaft between the bearing housing and the compressor or turbine housing. The oil is delivered into the channel from a supply in the rotary member. One of the walls of the channel serves as a weir whereby when the channel has an excess supply of oil is overflows the wall and passes the drain. The arrangement provides an effective seal against blow-by across the turbine end seal and restricts gas flow from the relatively high pressure regions of the compressor and turbine housings into the relatively low pressure area of the bearing housing. It also ensures that there is a continuous flow of oil across the seal so as to prevent it degrading in the high temperature environment.
A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger (1) and a second relatively large low pressure (LP) turbocharger (2). The turbine (6) of the LP turbocharger (2) is connected in series downstream of the turbine (4) of the HP turbocharger (1) in a first exhaust gas passage (11). An exhaust bypass flow passage (12) provides a bypass flow path around the HP turbine (4). A rotary valve (8) is located at a junction of the bypass flow passage (12) and a first exhaust gas flow passage (11). The rotary valve (8) comprises a valve rotor (19) which is rotatable to selectively permit or block flow to the LP turbine (6) from either the first exhaust gas passage (11) or the bypass gas passage (12).
F02D 23/00 - Controlling engines characterised by their being supercharged
F16K 11/074 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only sliding valves with pivoted closure members with flat sealing faces
F16K 11/085 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with all movable sealing faces moving as one unit comprising only taps or cocks with cylindrical plug
A variable geometry turbine comprises a turbine wheel (5) supported in a housing for rotation about a turbine axis with an annular inlet passageway (9) defined between a radial face of a nozzle ring (11) and a facing wall of the housing (10). The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway and has a circumferential array of vanes (20) that are received in corresponding slots (24) in the facing wall. A wastegate valve (15) is provided in a chamber behind the facing wall and gas bypasses the turbine through the chamber to the wastegate port (14) at high flow rates.
F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
F01D 17/16 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
63.
Method and apparatus for manufacturing turbine or compressor wheels
A method for forming a turbine or compressor wheel from a semi-solid material uses a die assembly that has an inner cartridge made up from a plurality of segments and an outer die. The semi-solid material is injected under pressure and high temperature into the die so that it flows into blade cavities defined between the segments of the cartridge. The cartridge is removed from the outer die and the segments are then separated to release the wheel.
A compressor for a turbocharger is supplied with crank case ventilation (CCV) gases from the engine which is turbocharged. The CCV gases are piped into an inlet of the compressor housing which supports an insert with an MWE structure. The MWE structure comprises an outer wall and an inner wall with a gas flow passage defined between them. At high r.p.m. of the compressor impeller air flows through the passage to provide more air volume to the impeller and at low r.p.m. excess air is bled out of the passage for recirculation. The CCV gases are directed to a position upstream of an inlet to the gas flow passage where they emerge through an outlet which may be defined in the insert. The CCV gases may be supplied to the outlet via a chamber defined between the insert and the compressor housing. The arrangement provides for improved mixing of CCV gases with the incoming air and does not compromise noise reduction.
A turbocharger wastegate valve assembly comprises a first bypass port communicating with a first portion of an exhaust inlet and a first valve member adapted for engaging and sealing a first valve seat surrounding the first bypass port. The valve assembly further comprises a second bypass port communicating with a second portion of an exhaust inlet and a second valve member adapted for engaging and sealing a second valve seat surrounding the second port. A shaft supports each valve member for rotation about a shaft axis to lift both the first and second valve members from sealing engagement with the first and second valve seats respectively. The first valve seat is inclined relative to the second valve seat and the shaft has freedom of movement in the axial direction.
F02D 23/00 - Controlling engines characterised by their being supercharged
F16K 11/16 - Multiple-way valves, e.g. mixing valvesPipe fittings incorporating such valvesArrangement of valves and flow lines specially adapted for mixing fluid with two or more closure members not moving as a unit operated by one actuating member, e.g. a handle which only slides, or only turns, or only swings in one plane
A compressor for compressing a gas comprises an impeller wheel mounted within a housing (2) defining an inlet and an outlet. The inlet comprises a map-width enhanced structure with an annular flow passage (11) defined between inner (9) and outer (7) tubular walls. The flow passage (11) is in fluid communication with the impeller wheel by virtue of a slot (13) in the inner wall (9). A flow-conditioning member (14) is positioned in the annular flow passage (11) and serves to remove swirl from the gas flow that recirculates through the passage. The flow-conditioning member (14) comprises a body penetrated by a plurality of bores (15). The arrangement provides for a significant improvement in the surge margin of the compressor and is particularly suitable for use in a turbocharger.
A compressor has a diffuser section with one or more detachable wall portions that define a diffuser surface. The wall portions may be detachably connected to an intermediate portion of the compressor housing between the inlet and outlet and/or to the bearing housing of a turbocharger to which the compressor housing is connected. The diffuser wall portions can be easily detached once the compressor housing is removed so as to allow cleaning of deposits or simple replacement. This provides for easy servicing to avoid the compressor performance being compromised by a built up of deposits and particulates on the diffuser surfaces that is a particular problem in turbochargers that receive recirculated crank case ventilation gases from the engine.
A turbine housing (13) for a radial flow turbine, particularly a turbine used in an exhaust gas turbocharger. The housing has a general volute shape with a substantially annular part extending around the turbine axis and an inlet duct (20) extending therefrom. The inlet duct (20) has a first wall facing part of the outer surface of the annular part of the housing, a pair of spaced webs (44) extending from the outer surface of the circular part of the housing to the first wall, the webs defining a valley (45) therebetween. The arrangement renders the housing stiffer and less prone to fatigue cracking.
A turbomachine comprises a housing (71) defining a bearing cavity (71) a and a turbine chamber (77a) separated by a first wall. A heat shield (72) is disposed between the first wall and the turbine wheel (77), a heat shield cavity (78) being defined between the first wall and the heat shield (72). The shaft (81) extends through a passage (85) defined at least in part by a first aperture (86) in said wall and a second aperture (87) in the heat shield (72). A first seal (88) is provide between the shaft (81) and said first aperture (86). The housing defines a first gas channel (79) communicating with the heat shield cavity (78) for connection to a pressure source for raising pressure within the heat shield cavity (78). A second channel (92) is provided between the heat shield cavity (78) and said passage (85), the second channel opening to said passage (85) on the opposite side of said first seal (88) to said bearing assembly (82). A second seal (89) is provided between the shaft (81) and said second aperture (87).
An oil control device inhibits the flow of oil along a shaft (8) rotating about an axis. The oil control device comprises an annular body (19) for rotation with said shaft (8) and includes a first face (30) extending generally radially from said axis. A second radially outer circumferential surface (40) is provided, extending generally axially. An oil slinging groove (32) extends into said body (19) and has a mouth (37) defined between a first circumferentially extending rim (38) and a second circumferentially extending rim (39). The second rim (39) is spaced both radially and axially from the first rim (38). The groove (32) is defined at least in part by a wall (34) which meets the first rim (38) at an acute angle to a radial plane. The groove (32) is also defined at least in part by a wall (35) which meets the second rim (39) at an acute angle to the direction of the axis.
A compressor typically for use in a turbocharger comprises a downstream radial compressor impeller wheel (11), an upstream axial compressor impeller wheel (10) and an intermediate stator (12). The compressor housing (13) has an inlet (19) with inner and outer walls (22, 23) that define between them an MWE gas flow passage (27). An upstream opening defined by the flow passage (27) provides communication between said passage and the intake (19) and at least one first slot (30) downstream of the upstream opening provides communication between the passage (27) and the inner surface (24) of the inner wall (22). The stator (12) comprises a plurality of fixed vanes (45) and is disposed in the inner wall (22) of the inlet between the radial and axial impeller wheels (10, 11). The position of the slot (30) can be at one of several positions along the gas flow passage (27). In other embodiments there are second and third slots (70, 71) and the flow passage (27) is divided into two parts (27a, 27b). All the arrangements are designed to improve the compressor map with.
A turbocharger system comprises a first relatively small turbocharger and a second relatively large turbocharger connected in series and an exhaust gas flow control valve. The exhaust control valve has an inlet port communicating with the exhaust gas flow upstream of the first turbine a first outlet port communicating with the exhaust flow downstream of said first turbine but upstream of said second turbine, and a second outlet port communicating with the exhaust flow downstream of said second turbine. The valve is operable to selectively permit or block flow through the first and second outlet ports.
A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a movable nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway. A substantially annular rib is provided either on the face of the nozzle ring (such that the minimum width of the inlet passageway is defined between the rib and the facing wall of the housing) or on the facing wall of the housing (such that the minimum width of the inlet passageway is defined between the rib and the nozzle ring).
An engine generator set comprises an internal.combustion engine (10) having an output shaft (12) that is coupled to an electrical generator (14) for producing an AC electrical power output'. The engine is operable to rotate the shaft (12) at a first rotational speed so that the generator (14) is driven to produce electrical power at a first frequency and a second rotational speed at which the generator is driven to produce electrical power at a second frequency. An exhaust gas turbocharger (11) is operatively connected to the engine (10) and has a compressor with a housing that defines a gas inlet (22). At least two guide, vane assemblies (40, 40') that are releasably and interchangeably connectable to the inlet (22) to match the compressor performance with the first or second engine speed. The guide vanes of the first guide vane assembly extend in a downstream direction towards the impeller wheel (19) at an angle relative to the inlet that is different to the corresponding angle of the guide vanes second guide vane assembly (40).
A turbocharger bearing housing defines a bore in which the turbocharger shaft is mounted for rotation in journal bearings. Lubricating oil is delivered to the journal bearings and a residue is retained in reservoirs in which the journal bearings are located. Two fluid retaining members are disposed around the shaft, each forming a wall of the reservoir and being sealed to the bearing housing. The lubricating fluid reservoir is provided between the fluid retaining members to a depth that at least partially immerses the journal bearings even when the oil supply is interrupted. This ensures that there is sufficient oil to lubricate the bearings at engine start-up, thereby reducing the risk of wear.
A turbocharger shaft (4) is supported for rotation about its axis in a bearing housing (1) by a pair of journal bearings (5,6) disposed between the turbine wheel (2) and the compressor impeller (3). A device (15) such as a hydraulic or magnetic actuator applies a non-axial force to the shaft at an axial location offset from the bearing so as to suppress non-axial sub- synchronous shaft vibrations that occur during operation of the turbocharger. This reduces turbocharger noise.
A variable geometry turbine of the kind used in a turbocharger has a variable geometry element such as a nozzle ring or an annular array of swing vanes that is operated by an actuator. The actuator has an output shaft coupled to a transmission mechanism for moving the variable geometry element. A rotary sensor device coupled to the output shaft of the actuator has a sensor wheel with a stop, slip clutch mechanism and a rotary position sensor. The device converts movement of the actuator output shaft into rotation of the wheel and the sensor generates an output signal representative of the rotary position of the wheel to provide a value indicative of the position of the variable geometry element. The actuator is calibrated to the position of the variable geometry element by rotating the sensor wheel in a first rotational direction until the variable geometry element reaches the first limit position, then rotating the sensor wheel in a second direction until the variable geometry element reaches the second limit position. The value of said output signal is logged at one of these positions as a limit value. The sensor wheel is allowed to declutch in the event that it encounters the stop in either direction of rotation. The output signal is monitored and the limit value is deducted to determine the position of the variable geometry element.
A turbocharger has a sealing arrangement between the turbocharger shaft and the bearing housing adjacent to the turbine and/or the compressor housings to restrict leaking of gas into the bearing housing. At least a pair of spaced sealing rings project from an annular surface of the bearing housing into corresponding annular recesses formed on the shaft. The trailing face of the second ring or the opposite surface of the recess has a plurality of radial grooves that define leak passages that serve to maintain a very small flow of gas from the turbine or compressor housing into the bearing housing. Alternatively there is a slot in the second ring to provide the leak passage. This ensures that there is a minimum gas flow so that a large pressure gradient is not applied across the second seal thereby avoiding wear, overheating and collapse of the ring.
A turbocharger comprises a turbine wheel (5) mounted within a housing assembly (1, 3) for rotation about a turbine axis, a gas flow inlet passage (8) upstream of the turbine wheel (5), and a gas flow control mechanism (10, 16, 32) located within the housing assembly (1, 3) upstream of the turbine wheel (5) and operable to control gas flow through said gas flow inlet passage (9). An actuator assembly is mounted to the housing assembly and comprises: A lead screw including a lead screw shaft (37) defining a lead screw axis, and a lead screw nut (36) threadedly engaged on a threaded portion of the lead screw shaft (37). The lead screw (36, 37) being arranged so that rotation of one of said shaft and nut relative to the housing assembly produces linear movement in the other of said shaft and nut in the direction of the lead screw axis: The lead screw (36, 37) engages the gas flow control mechanism (10, 16, 32) at a location within a housing cavity defined within said housing assembly (1, 3).
A turbocharger has a variable geometry turbine (1) of the swing vane kind. The vanes (24) are pivotally mounted on a vane carrier (23) and extend into an annular passageway (13) defined between a first surface (21) of the vane carrier and the turbine housing or the bearing housing. The carrier has a second surface (28) that is connected to a supporting wall (30) of the bearing housing (3) or the turbine housing (4) by means of a plurality of substantially radially extending key connections (41,43). These resist the rotational force applied to the carrier by the passage of the exhaust gas over the vanes and also permit thermal expansion of the vane carrier (23) relative to the supporting wall.
A speed sensor for use in measuring the speed of rotation of a rotationally salient rotating member The speed sensor comprises an electrode and a sensor circuit. The sensor circuit comprises a constant voltage source for supplying a voltage to the electrode to generate an electric field in a dielectric medium. A current detector detects current flow between the constant voltage source and the electrode due to perturbation of the electric field by passage of at least one salient feature of the rotating member through the electric field as the rotating member rotates. The current detector outputs a first signal modulated at a frequency corresponding to the frequency of perturbation of the electric field. The first signal is amplifed to produce an amplified signal modulated at a frequency corresponding to the frequency of perturbation of the electric field. The electrode voltage, the amplifier gain and the electrode position relative to the rotating member are selected such that modulation of the second signal is predominantly caused by perturbation of the electric field within the dielectric medium by the creation and/or movement of ions within the field.
G01B 7/14 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring distance or clearance between spaced objects or spaced apertures
G01D 5/24 - Mechanical means for transferring the output of a sensing memberMeans for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for convertingTransducers not specially adapted for a specific variable using electric or magnetic means influencing the magnitude of a current or voltage by varying capacitance
G01P 3/483 - Devices characterised by the use of electric or magnetic means for measuring angular speed by measuring frequency of generated current or voltage of pulse signals delivered by variable capacitance detectors
H03K 17/955 - Proximity switches using a capacitive detector
A control system for controlling the supply of oil to a turbocharger fitted to an internal combustion comprises an oil supply valve (21) controlled by a controller (20) and at least one sensor (23-28) for monitoring a parameter associated with the existence or potential occurrence of a leak in the turbocharger oil supply, or of a condition potentially resulting in such a leak. The controller (20) is operable to determine the existence or possible occurrence of an oil leak in the turbocharger oil supply in response to a signal received from the sensor (23-28) and to close the oil supply control valve (21) in the event of said determination to cut off the oil supply to the turbocharger.
A compressor comprises an impeller wheel mounted within a housing defining an inlet and an outlet. The wheel has a plurality of vanes and is rotatable about an axis. The housing has an inner wall defining a surface located in close proximity to radially outer edges of the impeller vanes which sweep across said surface as the impeller wheel rotates about its axis. The inlet comprises a tubular wall extending away from the impeller wheel in an upstream direction. An enclosed chamber is defined between said inner wall and an outer wall and in communication with at least one opening in said in said inner wall. The outer wall is penetrated by at least one ventilation aperture that is designed to be connected via a conduit to a location upstream of the inlet and downstream of an air filter. The arrangement maintains the advantages of a conventional MWE structure and further improves the surge margin. In addition, the risk of debris being drawn into the compressor via the opening is eliminated.
The speed of rotation of a rotary member such as a compressor or turbine wheel of a turbocharger is determined by directing an ultrasonic signal into a blade cavity and receiving the reflected signal, which is amplitude modulated by virtue of the passage of the blades across the ultrasonic transducer. The received signal is demodulated to determine the frequency of amplitude modulation of the received signal caused by passage of blades between the first and second locations. This enables the speed of rotation to be calculated. The performance of the turbocharger can thus be optimised in the context of the overall engine system via an engine control module.
A hydraulic seal is defined between a rotating member such as a turbocharger shaft and a stationary member such as part of a bearing housing of a turbocharger. The members define a projecting annular disc that is received in an annular channel that is filled with hydraulic sealing fluid such as oil. Rotation of the rotary member applies a centrifugal force to the fluid thereby ensuring that it is retained in the channel between walls thereof and the disc. This annulus of fluid provides a hydraulic seal around the shaft between the bearing housing and the compressor or turbine housing. The oil is delivered into the channel from a supply in the rotary member. One of the walls of the channel serves as a weir whereby when the channel has an excess supply of oil is overflows the wall and passes the drain. The arrangement provides a seal against blow-by across the turbine end seal and restricts gas flow from the high pressure regions of the compressor and turbine housings into the low pressure area of the bearing housing.
F16J 15/42 - Sealings between relatively-moving surfaces by means of fluid kept in sealing position by centrifugal force
F01D 11/04 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type using sealing fluid, e.g. steam
A method of logging information about events for an internal combustion engine having an ignition circuit, and an event logging device arranged to implement the method. The method comprises incrementing a current value of a counter (50) at a predetermined rate when the ignition circuit is turned on, detecting that an event has occurred (53), creating a new event record (54) having at least two fields, populating the fields within the new event record with information about the event (55), including at least an event type and the current value of the counter; and storing the new event record (57).
G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time
G01M 15/05 - Testing internal-combustion engines by combined monitoring of two or more different engine parameters
A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger (1) and a second relatively large low pressure (LP) turbocharger (2). The turbine (6) of the LP turbocharger (2) is connected in series downstream of the turbine (4) of the HP turbocharger (1) in a first exhaust gas passage (11). An exhaust bypass flow passage (12) provides a bypass flow path around the HP turbine (4). A rotary valve (8) is located at a junction of the bypass flow passage (12) and a first exhaust gas flow passage (11). The rotary valve (8) comprises a valve rotor (19) which is rotatable to selectively permit or block flow to the LP turbine (6) from either the first exhaust gas passage (11) or the bypass gas passage (12). The rotary valve (8) is operated to at least partially restrict flow to the LP turbine to generate a braking back pressure.
A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger (1) and a second relatively large low pressure (LP) turbocharger (2). The turbine (6) of the LP turbocharger (2) is connected in series downstream of the turbine (4) of the HP turbocharger (1) in a first exhaust gas passage (11). An exhaust bypass flow passage (12) provides a bypass flow path around the HP turbine (4). A rotary valve (8) is located at a junction of the bypass flow passage (12) and a first exhaust gas flow passage (11). The rotary valve (8) comprises a valve rotor (19) which is rotatable to selectively permit or block flow to the LP turbine (6) from either the first exhaust gas passage (11) or the bypass gas passage (12). The valve (8) is operated during a fired mode of the engine to block exhaust gas flow through the exhaust bypass and at least partially restrict exhaust flow to the LP turbine to raise the exhaust gas temperature.
A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway and has a circumferential array of vanes that are received in corresponding slots in the facing wall. Each vane has a recess defined in its major surface such that at a predetermined axial position of the nozzle ring relative to the facing wall the recess is in axial alignment with the slot and affords an exhaust gas leakage path through the inlet passageway. The recess is configured to reduce the efficiency of the turbine at small inlet gaps appropriate to engine braking or exhaust gas heating modes.
A turbocharger system comprises a first relatively small high-pressure (HP) turbocharger (1) and a second relatively large low pressure (LP) turbocharger (2). The turbine (6) of the LP turbocharger (2) is connected in series downstream of the turbine (4) of the HP turbocharger (1) in a first exhaust gas passage (11). An exhaust bypass flow passage (12) provides a bypass flow path around the HP turbine (4). A rotary valve (8) is located at a junction of the bypass flow passage (12) and a first exhaust gas flow passage (11). The rotary valve (8) comprises a valve rotor (19) which is rotatable to selectively permit or block flow to the LP turbine (6) from either the first exhaust gas passage (11) or the bypass gas passage (12).
A turbine housing (13) for a radial flow turbine, particularly a turbine used in an exhaust gas turbocharger. The housing has a general volute shape with a substantially annular part extending around the turbine axis and an inlet duct (20) extending therefrom. The inlet duct (20) has a first wall facing part of the outer surface of the annular part of the housing, a pair of spaced webs (44) extending from the outer surface of the circular part of the housing to the first wall, the webs defining a valley (45) therebetween. The arrangement renders the housing stiff er and less prone to fatigue cracking.
A compressor for compressing a gas comprises an impeller wheel mounted within a housing (2) defining an inlet and an outlet. The inlet comprises a map-width enhanced structure with an annular flow passage (11) defined between inner (9) and outer (7) tubular walls. The flow passage (11) is in fluid communication with the impeller wheel by virtue of a slot (13) in the inner wall (9). A flow-conditioning member (14) is positioned in the annular flow passage (11) and serves to remove swirl from the gas flow that recirculates through the passage. The flow-conditioning member (14) comprises a body penetrated by a plurality of bores (15). The arrangement provides for a significant improvement in the surge margin of the compressor and is particularly suitable for use in a turbocharger.
A turbocharger wastegate valve assembly comprises a first bypass port (30) communicating with a first portion of an exhaust inlet and a first valve member (36) adapted for engaging and sealing a first valve seat surrounding the first bypass port. The valve assembly further comprises a second bypass port (31) communicating with a second portion of an exhaust inlet and a second valve member (37) adapted for engaging and sealing a second valve seat surrounding the second port. A shaft (39) supports each valve member for rotation about a shaft axis (40) to lift both the first and second valve members from sealing engagement with the first and second valve seats respectively. The first valve seat is inclined relative to the second valve seat and the shaft has freedom of movement in the axial direction.
A variable geometry turbine comprises a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a movable nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway. A substantially annular rib is provided either on the face of the nozzle ring (such that the minimum width of the inlet passageway is defined between the rib and a the facing wall of the housing) or on the facing wall of the housing (such that the minimum width of the inlet passageway is defined between the rib and the nozzle ring).
A method for forming a turbine or compressor wheel from a semi-solid material uses a die assembly that has an inner cartridge made up from a plurality of segments and an outer die. The semi-solid material is injected under pressure and high temperature into the die so that it flows into blade cavities defined between the segments of the cartridge. The cartridge is removed from the outer die and the segments are then separated to release the wheel.
A variable geometry turbine comprises a turbine wheel (9) supported in a housing (1) for rotation about an axis. A nozzle ring (5) is moveably mounted within a cavity (19) provided within the housing for adjustment of the width of an annular inlet passageway (4) extending radially inwards towards the turbine wheel (9). An array of inlet guide vanes (8) extends between a radial face of the nozzle ring (5) and an opposing wall of the inlet (4) defining a radial vane passage. A first circumferential array of apertures (25) is provided through the radial face, each of which lies substantially within the vane passage. A second circumferential array of apertures (24) is also provided in said radial face, each of lies substantially upstream or downstream of the first array (25) of apertures. The inlet (4) and cavity (19) are in fluid communication via both the first and second sets of apertures (25, 24).
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
Turbochargers, air compressors and wastegates for machinery
and for engines (other than engines for land vehicle
propulsion); machines and machine tools, motors;
incubators; parts and accessories for all the aforesaid
goods included in this class. Turbochargers, air compressors and wastegates, all for land
vehicle propulsion; parts and fittings included for all the
aforesaid goods. Maintenance, repair and servicing of engines and of parts
thereof; maintenance, repair and servicing of turbochargers
and air compressors and parts and fittings therefor.
01 - Chemical and biological materials for industrial, scientific and agricultural use
04 - Industrial oils and greases; lubricants; fuels
07 - Machines and machine tools
12 - Land, air and water vehicles; parts of land vehicles
37 - Construction and mining; installation and repair services
Goods & Services
(1) Chemical motor oil additives.
(2) Motor oil and non-chemical motor oil additives.
(3) Turbochargers, air compressors and wastegates for machinery and for engines (other than engines for land vehicle propulsion); machines namely industrial machine presses; metal working machines, namely machining centres; machine tools; motors for airplanes; motors for boats; electric motors for machines; incubators; turbines and turbine wheels; turbomachinery; superchargers; blades, exhausts, cylinders, air pumps, wheels, fluid and ball bearings, compressor wheels; oil outlets, oil inlets and air inlets; turbochargers, air compressors and wastegates, all for land vehicle propulsion; parts and fittings for all the aforesaid goods.
(4) Motors namely motors for automobiles; parts and accessories for all the aforesaid goods. (1) Maintenance, repair and servicing of engines and of parts thereof; maintenance, repair and servicing of turbochargers and air compressors and parts and fittings therefor.
