A compressor system including: a first compressor having a compressor suction side and a compressor delivery side; an anti-surge line having an inlet and an outlet; an anti-surge valve arranged along the anti-surge line and controlled for recirculating a gas flow from the compressor delivery side back to the compressor suction side; a gas temperature manipulation arrangement, functionally connected to the inlet of the anti-surge line, configured to reduce or prevent liquid phase in the anti-surge line when the anti-surge valve is open.
An apparatus for handling a turbomachine part, particularly during disassembling and reassembling operations. More specifically, an apparatus for handling the stator cone of a gas turbine suitable to completely manipulate the stator cone during disassembling and reassembling operations. The apparatus allows to disassemble and reassemble the stator cone of a gas turbine without the need to dismount the turbomachine enclosure and without the necessity to have personnel inside the turbomachine package during the operations.
An unshrouded turbomachine impeller is disclosed. The impeller comprises a hub and a plurality of sequentially arranged blades. Each blade extends from a blade root at the hub to a blade tip and is comprised of a first blade edge and a second blade edge. A flow vane is formed between each pair of neighboring blades. A connection member extends across each flow vane between neighboring blades and rigidly or monolithically connects a first modal displacement region of a first one of the pair of neighboring blades to a second modal displacement region of a second one of the pair of neighboring blades.
The shaft seal arrangement for a rotating turbomachine shaft having a rotation axis, comprises a rotor part and a stationary part. A dry gas seal is further provided, in combination with a cooling fluid volume arranged for receiving a cooling fluid and in heat exchange relationship with the dry gas seal. A venting arrangement collectively vents exhaust cooling fluid and dry sealing gas from the shaft seal arrangement.
F04D 29/58 - CoolingHeatingDiminishing heat transfer
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
F01D 11/00 - Preventing or minimising internal leakage of working fluid, e.g. between stages
5.
Control system and method for pressure-let-downs stations
A system for depressurizing a gas in a pipeline is described. The system com-prises an expander configured and arranged for generating mechanical power by expanding gas from a first pressure to a second pressure. The system further comprises a heat pump and a heat transfer circuit containing a heat transfer fluid circu-lating therein, for receiving heat from the heat pump and delivering heat to the gas through a heat exchanger. A controller is further provided, configured and arranged for modulating a flow rate of the heat transfer fluid circulating in the heat transfer circuit as a function of a heat rate to be transferred from the heat transfer fluid to the gas, particularly as a function of temperature differentials between the gas and the heat transfer fluid at a gas inlet side and a gas outlet side of the heat exchang-er.
F17D 1/075 - Arrangements for producing propulsion of gases or vapours by mere expansion from an initial pressure level, e.g. by arrangement of a flow-control valve
A modular gas turbine system for on-shore LNG plants is disclosed. The module comprises a base plate having a top side and a bottom side and supports on the top side thereof at least a gas turbine engine, a control and electrical room wired to the gas turbine engine, at least part of auxiliaries of the gas turbine engine. Additionally, at least one compressor is supported on the base plate and mechanically coupled to the gas turbine engine and driven into rotation by said gas turbine engine.
A Centrifugal compressor impeller including a plurality of blades extending from a hub, each blade having a first wall defining a pressure side of the blade, and a second wall defining a suction side of the blade, and a free end defining a tip of the blade, the tip presenting a raised rim aligned to the first wall, the second wall of the blade being at least partially aligned with a surface of the tip free from the raised rim.
The turbomachine comprises a stationary casing with a rotating member configured to rotate about a rotation axis in the stationary casing. The turbomachine further includes a rotating balance drum, arranged for co-rotation with the rotating member. A stationary sleeve is arranged in a fixed relationship with the stationary casing and surrounds the balance drum. The stationary sleeve comprises a plurality of consecutively arranged sleeve sections. A fluid channel is defined by an outer surface of the balance drum and an inner surface of the stationary sleeve. Between at least one pair of sequentially arranged upstream sleeve section and downstream sleeve section an annular chamber is provided, fluidly coupled to the fluid channel. Shunt holes are arranged on the upstream sleeve section, each shunt hole having a shunt hole inlet on an inner surface of the upstream sleeve section, and a shunt hole outlet in the annular chamber.
A compressed air energy storage system is described, including a compressor fluidly coupled to a compressed air reservoir and an expansion train including at least a first turbine. The system further includes an electric machine aggregate configured: for converting electric power into mechanical power and driving the compressor therewith during the energy storing mode; and for converting mechanical power produced by the expansion train into electric power during the power production mode. A combustor is configured for receiving fuel and compressed air and producing combustion gas, and for supplying the combustion gas to the first turbine.
F02C 6/16 - Gas-turbine plants having means for storing energy, e.g. for meeting peak loads for storing compressed air
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
F02C 6/06 - Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
F02C 7/143 - Cooling of plants of fluids in the plant of working fluid before or between the compressor stages
10.
Method for uniforming temperature in a shaft supported by a fluid bearing, bearing system and turbomachine
The method is used for uniforming temperature in a shaft supported by a fluid bearing during rotation of the shaft; a journal portion of the shaft is located inside the fluid bearing; at least one passage is provided inside the shaft at least along the journal portion so to cross it; at least one flow of heat-exchange fluid is established in the at least one passage; the method allows to overcome the problems due to the “Morton effect”. A bearing system implementing the method is advantageously used in a turbomachine.
F16C 17/24 - Sliding-contact bearings for exclusively rotary movement characterised by features not related to the direction of the load with devices affected by abnormal or undesired conditions, e.g. for preventing overheating, for safety
A charge gas compression train for ethylene including a first compressor including a first group of compression stages, a second group of compression stages, and a third group of compression stages. The first group of compression stages includes an outlet configured to be connected to a first intercooler inlet. The second group of compression stages includes a second compressor inlet configured to be connected to a first intercooler outlet, and a second compressor outlet configured to be connected to a second intercooler inlet. The third group of compression stages includes a third compressor inlet configured to be connected to a second intercooler outlet. The first, the second, and the third group of compression stages are integrated in a first common casing and operate at the same rotation speed. The first compressor includes a plurality of unshrouded and shrouded impellers, where an unshrouded impeller is positioned upstream to a shrouded impeller.
F04D 29/28 - Rotors specially adapted for elastic fluids for centrifugal or helico-centrifugal pumps
F25J 3/02 - Processes or apparatus for separating the constituents of gaseous mixtures involving the use of liquefaction or solidification by rectification, i.e. by continuous interchange of heat and material between a vapour stream and a liquid stream
F02K 5/00 - Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
12.
Compressor system with a cooling arrangement between the anti-surge valve and the compressor suction side and relevant method
F25J 1/00 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
F25J 1/02 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen
F04D 17/10 - Centrifugal pumps for compressing or evacuating
13.
Method for starting and operating a plant for the liquefaction of a gaseous product
A method for starting and operating a plant for the liquefaction of a gaseous product comprising the steps of electrically connecting a variable frequency drive to a motor of a first machine string; increasing the speed of the motor of the first machine string up until a first predefined threshold; electrically disconnecting the variable frequency drive from the motor of the first machine string; electrically connecting the variable frequency drive to a motor of a second machine string; the first predefined threshold is function of said frequency of the power supply grid. The variable frequency drive can be switched during operation of the plant among the strings according to process requirements.
F25J 1/02 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures requiring the use of refrigeration, e.g. of helium or hydrogen
F25J 1/00 - Processes or apparatus for liquefying or solidifying gases or gaseous mixtures
F25B 1/00 - Compression machines, plants or systems with non-reversible cycle
F25B 1/053 - Compression machines, plants or systems with non-reversible cycle with compressor of rotary type of turbine type
F02C 3/045 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor
14.
Motorcompressor and method to improve the efficiency of a motorcompressor
A motorcompressor comprising an electric motor, a load, a shaft assembly, the electric motor and the load being mounted on the shaft assembly, a casing configured to completely house the electric motor, the load and the shaft assembly for its entire length, a divider located in the casing to define a motor chamber and a load chamber, the divider comprising at least a pumping device configured to transfer a part of the fluid present in the motor chamber to the load chamber so as to obtain in the motor chamber a pressure that is lower than a pressure at a load inlet.
A casing for a subsea compressor comprises a main body having a central axis; a plurality of interconnection flanges attached to the main body; wherein the main body comprises an inner layer made of corrosion resistant material; an outer layer applied over the inner layer and made of a composite material; wherein the outer layer extends along the entire length of said main body.
B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or coreShaping by spray-up, i.e. spraying of fibres on a mould, former or core
B29K 71/00 - Use of polyethers as moulding material
16.
Measuring total pressure of a fluid in a turbo machine
A turbomachine airfoil component is disclosed, having a leading edge and a trailing edge. The airfoil component comprises a hole extending from an inlet positioned at the leading edge towards the interior of the airfoil component and forming a total pressure probe. The hole is fluidly connected to a pressure measuring device.
A gas turbine combustor is disclosed, comprising: a combustor liner; a combustor casing, at least partly housing the combustor liner, and a liner support arrangement. The liner support arrangement comprises individual support elements located between the combustor liner and the combustor casing. Each support element comprises a liner support member fixed to the combustor liner and a casing support member fastened to the combustor casing. Each casing support member comprises a casing stop seat fixed on the combustor casing and a replaceable casing stop, detachably coupled to the casing stop seat.
An integrated turbomachine is described, comprising: a casing; an electric motor and a driven turbomachine component housed in the casing; a rotating shaft drivingly connecting the electric motor and the driven turbomachine component; a thrust bearing and a radial bearing rotatingly supporting the shaft; an axial locking device housed inside the casing, for applying a thrust to the shaft, parallel to the rotation axis (A-A) of the shaft, and comprised of an actuator member, configured to selectively activate and/or deactivate the axial locking device.
F04D 29/62 - MountingAssemblingDisassembling of radial or helico-centrifugal pumps
F01D 17/12 - Final actuators arranged in stator parts
F01D 25/16 - Arrangement of bearingsSupporting or mounting bearings in casings
F01D 3/04 - Machines or engines with axial-thrust balancing effected by working fluid axial thrust being compensated by thrust-balancing dummy piston or the like
19.
Device for controlling the flow in a turbomachine, turbomachine and method
A device for controlling the flow in a turbomachine, in an embodiment, a centrifugal compressor; the device includes a plurality of fixed blades and a plurality of adjustable blades adjacent to the plurality of fixed blades so that each of the adjustable blades has an aerodynamic interaction with one of the fixed blades; each of the adjustable blades is pivoted to rotate about a fixed axis substantially located at the center of pressure of the adjustable blade; the center of pressure is evaluated when the blade is at a reference orientation.
A seal assembly (1) for a valve stem (104) comprises an external seal (2) placed on a valve stem (104) facing an external environment (E); an internal seal (3) placed on the valve stem (104) facing a process environment (P); the external (2) and internal seals (3) define a chamber (4) for the containment of barrier fluid; the chamber (4) has an inlet (5) configured to be placed into fluid communication with a source (S) of barrier fluid; a detector (6) of the amount of barrier fluid; a pressurizer device (7) for providing the chamber (4) with a positive pressure with respect to the process environment (E); the pressurizer device (7) is configured to be installed coaxially with the valve stem (104).
Fluid flow adapter (1) for a cylinder (100) of a reciprocating compressor, said cylinder (100) having a side wall (101) provided with a valve seat (103), said fluid flow adapter (1) comprising a filler element (2) having an internal surface (3) facing an internal volume (104) of the cylinder (101) and an external surface (4) facing the valve, said filler element (2) having at least a channel (5) connecting the internal surface (3) to the external surface (4), wherein said internal surface (3) is flush with the side wall (101) of the cylinder (100), said channel (5) being configured to allow the passage of fluid between the internal volume (104) of the cylinder (100) and the valve.
Compression unit (1) for supplying high and low pressure services to a plant comprising a single driver (2) associated with two driver shaft-ends (3, 4) projecting apart from said driver (2), a first driver shaft end (3) and a second driver shaft end (4), a first unit (10) being operatively connected to the first driver shaft-end (3) and a second unit (20) being operatively connected to the second driver shaft-end (4).
A combustor for a gas turbine is described. The combustor comprises a combustor liner (3), a metering plate (7) attached to an end of the combustor liner and a combustor casing (5) at least partially surrounding the combustor liner (3). An end cover (18) is further connected to the combustor casing (5). The combustor liner (3) is connected to the combustor casing (5) by means of a retainer (21) arranged between the metering plate (7) and the end cover (18), and attached to the metering plate and to the end cover.
The arrangement allows to stabilize a rotating shaft. It comprises a shaft (12) being arranged substantially vertically in a machine (10) so as to rotate during machine operation, first pressure delivery system(22, 23, 30) for delivering a fluid pressure, in particular of a fluid circulating inside the machine (10), at a first location (1) of the machine (10). Said first location (1) is close to the shaft (12) and part of said first pressure delivery system (22, 23, 30) is arranged at said first location (1) so as to exert a lateral pulling or pushing action on the shaft (12).
The method allows to control a test apparatus for a gas turbine engine; WI values of one or more tentative fuel gas mixtures are predicted by calculations and the predicted WI values are used for setting the composition of a fuel gas mixture to be supplied to a combustor of a gas turbine (GT) engine under test. The test apparatus (1) comprises: a first supply flow line (11) for fuel gas; a second supply flow line (21) for inert gas; a mixer (30) with a first inlet for fuel gas and a second inlet for inert gas, and with an outlet (31) for supplying the mixture of fuel gas and inert gas to the combustor; a set of meters (12, 13, 14, 22, 23, 24, 25); and a flow control device (40) for the inert gas.
The coupling load measurement method allows to measure load between a first driving shaft (1) and a second driven shaft (2) connected by means of a hub (3) coupled both with the first shaft (1) and with the second shaft (2) by means of at least one flexible coupling element (5,6) coupled to said hub (3) and to said first shaft (1) and/or to said second shaft (2); the method comprises, during operation of the shafts (1,2), a measurement step of measuring a distance variation respect to a reference distance between a first flange of the hub (31) and a second flange (61) of the flexible coupling element (5,6) and the step of using said measured distance variation for calculating said load.
G01M 15/14 - Testing gas-turbine engines or jet-propulsion engines
G01L 5/12 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes for measuring axial thrust in a rotary shaft, e.g. of propulsion plants
27.
METHOD AND SYSTEM FOR PREDICTING RESIDUAL USEFUL LIFE OF AN AIR FILTER
A method for predicting the residual useful life of an air filter arrangement is described. The method comprises the following steps: providing a plurality of predetermined reference degradation curves (Cj); measuring a degradation parameter (x; Δp) of the filter arrangement (25; 29; 31, 33); estimating the residual useful life (RUL(Ti)) of the filter arrangement (25; 29; 31, 33) by comparing the predetermined reference degradation curves (Cj) and an actual degradation curve (CF) defined by measured values of the degradation parameter.
A packing case (1) for a plunger (2) or a piston rod of a reciprocating machine comprises a plurality of packing cups (11A-11E), each packing cup comprising a body (12) with a hole (13) for the passage of the plunger or rod (2) and a sealing ring seat (14) for housing a sealing ring (15) which slidably bear against the plunger or rod (2). Said packing cups are aligned with each other in series. Said packing case comprises a plurality of lube oil ducts (A,B,C) for supplying lube oil from an end of the packing case to an area of the sealing ring seat (14), wherein all the packing cups of the packing case are identical each other. Each packing cup comprises sectors (31,32,33) angularly offset with each other, each sector comprising at least lube oil duct portions (41,42). The packing cups are selectively positionable with each other to bring, for each packing cup, one sector at a time in an activation position, in such activation position at least some of the lube oil duct portions of said sector being operatively connected with the lube oil duct portions of a sector in the activation condition of an adjacent packing cup so as to form said lube oil ducts. The packing cups are lockable each by each at one position corresponding to the activation position of a circular sector. The corresponding method of assembling such a packing case (1) is also disclosed.
The motor-compressor unit (1) for sub-sea applications, comprises a pressure casing (3), and an electric motor (5) housed in a motor compartment (9) formed in the pressure casing (3) and a compressor (7) housed in a compressor compartment (11) formed in the pressure casing (3). A shaft (15) drivingly connects the electric motor (5) and the compressor (7). At least one magnetic bearing (21, 23, 25, 27) rotatingly supports the shaft (15) and a control system (37A-37D) is provided for controlling the magnetic bearing (21, 23, 25, 27). The control system (37A-37D) is housed in a control system compartment (31) structurally connected to and supported by the pressure casing (3).
A welding tool (2) comprises a main body (20) to be held by a welder, a handle (21) attached to the main body (20), an electrode (3) attached to the main body (20), an adjusting device (4) for moving the consumable electrode (3) forward/backward with respect to the main body (20), a control unit connected to the adjusting device (4) and configured to act on the adjusting device (4) for maintaining a substantially constant distance between the electrode (3) and a weld area.
A welding assistance device comprises a welding mask (9), a welding velocity sensor attached on the welding mask (9) and configured to detect a welding velocity, a visualization device (15) attached to the welding mask (9) and arranged to show a representation of the welding velocity and of consequent heat input to a welder.
An handling apparatus (18) for performing a TIG weld comprises a main body (27) for holding a filler rod (R), a feeding device (19) attached to the main body (27) and configured to advance the filler rod (R) during welding, and a control unit configured to act on the feeding device (19) and to regulate the speed of the filler rod (R).
A device (1) for dampening pressure pulsations in a gas flow comprises a vessel (2) with an inlet (4) and an outlet (5), the vessel (2) defines an internal volume (3) for the transit of the gas; a choke tube (6) in fluid communication with the vessel (2) and placed completely outside the internal volume (3) of the vessel (2).
Method for generating a machining program of a plunge mulling machine tool, comprising the steps of: establishing a machining (15) to be performed on a workpiece (10); acquiring first machining information (20) that indicates stable cut conditions of said machine tool for said workpiece (10); acquiring second machining information (30) that indicates engagement cut conditions of said machine tool during said machining on said workpiece (10); carrying out a determination of the rotation speeds of said machine tool during said machining (15) on the basis of said second machining information (30) and said first machining information (20); wherein said machining program is generated on the basis of the determination carried out.
G05B 19/4093 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by part programming, e.g. entry of geometrical information as taken from a technical drawing, combining this with machining and material information to obtain control information, named part programme, for the NC machine
An automatic ring valve 10 comprising a valve seat 12 provided with a plurality of gas flow passages 14 arranged according to at least one annular row, at least a shutter 18 comprising at least one ring-shaped portion for selectively closing and opening the gas flow passages 14, wherein said ring-shaped portion of the shutter 18 comprises a fiber-reinforced matrix 40, at least one contrasting member for contrasting an opening movement of ring-shaped portion of the shutter 18, wherein said ring-shaped portion of the shutter 18 comprises a structural core 18A made by said fiber-reinforced matrix 40, and wherein at least a portion of said structural core 18A is covered by at least one primary layer 18B, designed to improve fracture and/or impact and/or wear resistance of said ring-shaped portion.
Metal alloys are disclosed, comprising at least cobalt, nickel, iron and carbon, wherein: the content of cobalt is at least about 20% by weight; the content of iron and cobalt in combination is comprised between about 40% and about 70% by weight; the content of nickel is comprised between about 5% and about 25% by weight; and the content of carbon is more than 0% but less than about 0.05% by weight.
A sector (2) for the assembly of a stage (1) of a turbine comprises a central (2a) and a peripheral portion (2b); a plurality of blades (6) attached between the central (2b) and the peripheral portions (2a); a first (16) and a second side (17) opposite to each other, the first side (16) is configured to join with the second side (17) of another sector (2), the first side (16) is provided with a first connecting portion (18) and the second side (17) is provided with a second connecting portion (19) configured to mate with a first connecting portion (18) of a first side (16) of another sector (2).
The centrifugal compressor comprises a compressor chassis (3) defining an inlet passageway (13), a diffuser (15) fluidly coupled to the inlet passageway, and a return channel (17) extending from the diffuser(15). The compressor further comprises a first impeller (7) rotatably arranged in the chassis (3), between the inlet passageway (13) and the diffuser (15), and a second impeller (9) arranged in the chassis (3) downstream of the return channel (17). Movable inlet guide vanes (21)are arranged in the inlet passageway (13). Movable return guide vanes (25) are arranged in the return channel (17). An actuation system simultaneously moves the movable inlet guide vanes and the movable return guide vanes.
A mounting system for supporting rotating machinery is described. The system corn-prises a base frame (9) having an upper side for mounting the rotating machinery (3, 5, 7), and a lower side. A set of main supporting members (13) are arranged according to a triangular arrangement and forming a three-point mounting arrangement defining a mounting plane. Moreover, a set of auxiliary supporting members (15), having a variable stiffness (S1,S2) in at least one direction, are provided and are configured and arranged such as to increase the stiffness thereof when the base frame (9) is subject to an overload, thus reducing load on the main supporting members (13).
F16M 5/00 - Engine beds, i.e. means for supporting engines or machines on foundations
B23Q 1/01 - Frames, beds, pillars or like membersArrangement of ways
F02C 1/00 - Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
F16M 7/00 - Details of attaching or adjusting engine beds, frames, or supporting-legs on foundation or baseAttaching non-moving engine parts, e.g. cylinder blocks
The turbomachine assembly (200) comprises a first turbomachine (210) having an inlet (21 1), an outlet (212) and a rotary shaft (213), a second turbomachine (220) having an inlet (221), an outlet (222) and a rotary shaft (223), a transfer duct (240) fluidly connecting the outlet (212) of the first turbomachine (210) to the inlet (221) of the second turbomachine (220), and a casing (230) housing the turbomachines (210, 220) and the transfer duct (240); the turbomachines (201, 220) are located adjacent to each other so that the outlet (222) of the second turbomachine (220) is close to the outlet (212) of the first turbomachine (210) and the inlet (221) of the second turbomachine (220) is remote from the outlet (212) of the first turbomachine (210); the outlet (222) of the second turbomachine (220) has an end portion (225) shaped like a cochlea (i.e. a spiral duct); the transfer duct (240) has an annular shape, and surrounds the end portion (225) of the outlet (222) of the second turbomachine (220).
A method for reducing NOx emissions in a gas turbine in which a flow of primary air and a flow of fuel are fed into a dual annular counter rotating swirler (4), said primary air flow being fed into the inner and outer annular chambers (51,52), wherein the method comprises the step of injecting the flow of fuel into the inner annular chamber (51). Another embodiment is a gas turbine air fuel mixer (1) comprising a dual annular counter rotating swirler (4) comprising a fuel supplying element (3) adapted to supplying fuel inside the inner chamber (51) of the swirler; another embodiment is a gas turbine provided by such air fuel mixer.
A drive system for driving a load, comprising a gas turbine configured and arranged for driving the load, an electric motor/generator electrically connected to an electric power grid, a first load coupling connecting the gas turbine to the load, a second load coupling, connecting the load to the electric motor/generator. The electric motor/generator is adapted to function as a generator for converting excess mechanical power from the gas turbine into electrical power and delivering the electrical power to the electric power grid, and as a motor for supplementing driving power to the load. The drive system comprises furthermore a disconnecting device to reversibly disconnect the load from the gas turbine, so that the load can be driven only by the motor.
F01D 15/10 - Adaptations for driving, or combinations with, electric generators
F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
H02K 7/18 - Structural association of electric generators with mechanical driving motors, e.g.with turbines
H02P 9/04 - Control effected upon non-electric prime mover and dependent upon electric output value of the generator
F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
F02C 3/04 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
F16H 47/02 - Combinations of mechanical gearing with fluid clutches or fluid gearing the fluid gearing being of the volumetric type
H02K 7/108 - Structural association with clutches, brakes, gears, pulleys or mechanical starters with friction clutches
F02C 3/10 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
43.
SEAL FOR A GAP BETWEEN AN OUTER AND AN INNER CYLINDRICAL SURFACE
A seal (1) for a gap (2) between an outer (3a) and an inner cylindrical surface (2b), coaxial with a central axis (A) in common and arranged to rotate reciprocally, the seal (1) comprises a plurality of plate elements (7) stacked onto one another to define a ring (11) between the outer (2a) and inner cylindrical surfaces (2b), wherein each plate has a concave (8) and a convex side (9), the convex side (9) of each plate element (7) being adjacent to the concave side (8) of the next plate element (7).
A turbomachine has a casing (10) where liquid may accumulate; at least one liquid level detector (11) is located inside the casing (10) for automatically detecting liquid accumulated inside the casing (10) during operation of the turbomachine; the liquid level detector (11) may be arranged for detecting one or two or three or four liquid levels (L1, L2, L3, L4) inside the casing (10); the liquid level detector (11) is typically connected to an electronic unit (13) at least for automatically signaling (14) the liquid level. Advantageously, the electronic unit controls at least one valve for automatically discharging the accumulated liquid from the casing; in this way, the status of the turbomachine is not only monitored but also managed.
A method for checking a geometry of an electric discharge machining electrode (11) is described. The method comprises the following steps: • providing a file containing a native 3D-model (21) of the electric discharge machining electrode; • providing a manufactured electric discharge machining electrode (11) based on the native 3D-model; • light scanning a set of images of the manufactured electric discharge machining electrode in different positions and generating therewith a scanned 3D-model (23) of the manufactured electric discharge machining electrode; comparing the native 3D-model (21) and the scanned 3D-model (23) and generating electrode compensation coordinates for an electric discharge machining apparatus, to correct an electrode path during electric discharge machining.
B23H 7/20 - Electric circuits specially adapted therefor, e.g. power supply for programme-control, e.g. adaptive
G05B 19/404 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by control arrangements for compensation, e.g. for backlash, overshoot, tool offset, tool wear, temperature, machine construction errors, load, inertia
B23H 1/04 - Electrodes specially adapted therefor or their manufacture
B23H 7/18 - Electric circuits specially adapted therefor, e.g. power supply for maintaining or controlling the desired spacing between electrode and workpiece
An internally cooled centrifugal compressor 1 is described. The compressor comprises: a casing 3; an upstream impeller 9 and a downstream impeller 11 sequentially arranged for rotation in the casing; a stationary diaphragm 5 arranged in the casing and comprised of an internal diaphragm portion 21 and an external diaphragm portion 23; an upstream diffuser 13 fluidly coupled to an outlet of the upstream impeller; a return channel 15 fluidly coupled to the upstream diffuser 13 and to an inlet of the downstream impeller 11, the return channel 15 provided with a plurality of return-channel blades 19 connecting the internal diaphragm portion to the external diaphragm portion; a downstream diffuser 17 fluidly coupled to an outlet of the downstream impeller 11. A first coolant passage 47 is provided in the internal diaphragm portion 21 and extends around a first inner core arranged in the internal diaphragm portion, the first coolant passage 47 being in heat-exchange relationship with the upstream diffuser 13 and the return channel 15. A second coolant passage 49 and a third coolant passage 48 are provided in the external diaphragm portion 23, separated by a second inner core arranged in the external diaphragm portion 23, the second coolant passage 49 and third coolant passage 48 being in heat-exchange relationship with the return channel 15 and the downstream diffuser 17.
A method for manufacturing a machine component made of metal-based material is described. The method comprises the steps of: providing a powder blend comprising at least one metal-containing powder material and at least one strengthening dispersor in powder form, wherein the strengthening dispersor in powder form has an average grain size less than an average grain size of the metal-containing powder material; forming the machine component by an additive manufacturing process using the powder blend.
B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
C22C 32/00 - Non-ferrous alloys containing at least 5% by weight but less than 50% by weight of oxides, carbides, borides, nitrides, silicides or other metal compounds, e.g. oxynitrides, sulfides, whether added as such or formed in situ
F01D 5/00 - BladesBlade-carrying membersHeating, heat-insulating, cooling, or antivibration means on the blades or the members
48.
FUEL DISTRIBUTION DEVICE, GAS TURBINE ENGINE AND MOUNTING METHOD
The fuel distribution device (1) wherein an axis is defined; the device comprises a body (10; 20) housing a distribution path for fuel; the distribution path has one inlet (11; 21) and a plurality of outlets (12, 13, 14, 15; 22, 23, 24, 25, 26); the inlet (11; 21) is located on the external surface of the body (10; 20) at an end of an inlet branch of the distribution path; the plurality of outlets (12, 13, 14, 15; 22, 23, 24, 25, 26) are located on the external surface of the body (10; 20) at ends of a corresponding plurality of outlet branches of the distribution path; the inlet branch and the outlet branches are fluidly connected to a distribution space (100, 200); the outlet branches are arranged radially.
A method for manufacturing turbomachine impellers is described. The method provides for manufacturing a plurality of tubular components (13), each tubular component forming an inner passage (21), which is shaped as one of the flow passages of the final impeller (1). The tubular components are assembled together forming a semi-finished impeller (1S). The semi-finished impeller is provided with annular cavities (41, 43) extending around the rotation axis of the impeller and gaps (S) between adjacent tubular components (13). The gaps and cavities are filled with metal powder and the semi-finished impeller is subject to hot isostatic pressing, to density the metal powder and form a monolithic final impeller (1).
A crosshead (1 ) for a piston rod (4) comprises a main body (3) having a first (5) and a second seat (6), the first seat (5) is configured to hold a connecting rod (2), the second seat (6) is configured to hold a piston rod (4) wherein said main body (3) is made as a single piece.
Turbomachines, as well as their components, are disclosed being in the field of production and treatment of oil and gas containing e.g. hydrocarbon plus hydrogen sulfide, carbon dioxide, with or without other contaminants. Said components are made of a high corrosion high temperature resistant alloy, capable of resisting to corrosion and/or stress at high temperature better than state of art martensitic stainless steels and behaving similarly to premium nickel base superalloys.
The method for manufacturing a turbomachine component comprises the following steps: (a) producing by additive manufacturing a plurality of separate segments (1S) of the tubomachine component (1), having a skin surrounding an empty volume (11V) corresponding to a massive part of the turbomachine component; (b) assembling the separate segments of the turbomachine component together forming a semi-finished component, with an empty cavity therein; (c) filling cavity of the semi-finished component with a bulk flowable material; (d) densifying and solidifying the bulk flowable material in the cavity.
A drive system for driving a load by a gas turbine. The gas turbine comprises a gas generator having a gas-generator rotor and comprising at least one gas-generator compressor and one high-pressure turbine driving the gas-generator compressor. The gas turbine further comprises a power turbine having a power-turbine rotor, which is torsionally independent of the gas-generator rotor. The load is connected to the power-turbine rotor. The system further comprises an electric motor/generator mechanically connected to the gas-generator rotor and electrically connected to an electric power grid. The electric motor/generator is adapted to function alternatively: as a generator for converting mechanical power from the gas turbine into electrical power; and as a motor for supplementing driving power to the load. A set of movable nozzle guide vanes is arranged at the inlet of the power turbine.
F02C 3/00 - Gas-turbine plants characterised by the use of combustion products as the working fluid
F02C 6/00 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use
F02C 3/05 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor the compressor and the turbine being of the radial flow type
F02C 9/20 - Control of working fluid flow by throttlingControl of working fluid flow by adjusting vanes
F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
F01D 15/10 - Adaptations for driving, or combinations with, electric generators
F02C 3/10 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
F01D 15/00 - Adaptations of machines or engines for special useCombinations of engines with devices driven thereby
A dry gas extraction device is described, for extracting a dry gas from a wet gas flow. The device comprises a wet gas duct (24) having a side wall surrounding an inner gas flow volume. The device further comprises at least one dry gas intake port (57) located in a position inside the gas flow volume at a distance from the side wall.
A wet-gas centrifugal compressor (1) is disclosed. The compressor comprises a compressor casing (3) and at least one impeller (9) arranged in the compressor casing for rotation around a rotation axis (A-A). A stationary diffuser (21) is arranged in the compressor casing and extends around the impeller (9). The diffuser (21) has a curved end portion (21A) with a radially inner curved wall (27) and a radially outer curved wall (29). A plurality of dry-gas extraction holes (35) is provided, ending at a plurality of respective inlet ports arranged around the rotation axis and on the inner curved wall of the curved end portion of the diffuser. Each dry-gas extraction hole extends from the respective inlet port towards the rotation axis and is inclined over a radial direction, such that each dry-gas extraction hole (35) is oriented in a counter-flow direction with respect to a direction of the gas flow in the curved end portion (21A) of the diffuser (21).
A sealing device (1) is described, for separating a first compartment (3) from a second compartment (5) in a turbomachine, a wet gas being processed in the first compartment. The sealing device comprises a rotary component (7) and a stationary component (11). A sealing member (15T) is arranged between the rotary component and the stationary component. The device further comprises an annular wet-particles collector (21) and an oil-jet element (13), mounted on the rotary component (7) for rotation there with. The oil-jet element is surrounded by the annular wet-particles collector, such that wet particles contacting the oil-jet element are projected by centrifugal force into the annular wet-particles collector.
A wet-gas compressor (10) s described, comprising a compressor casing (1) and a rotor (31, 33, 35) arranged for rotation in the compressor casing and comprised of at least one impeller (31, 33). In the compressor casing at least one cavity (3; 3.1-3.6) is provided, where liquid (L) contained in a wet gas processed by the compressor (10) can collect during operation of the compressor. A drain port (5) is provided at the bottom of the cavity and a vent port (13) is provided in a position above the drain port of the cavity. The drain port (5) and vent port (13) are in fluid communication with a liquid-level measuring chamber (9). A level gauge (15) is provided at the liquid-level measuring chamber (9) and a drainage valve (21) is arranged for discharging liquid from the cavity (3; 3.1-3.6) towards a liquid discharge line fluidly connected to the drain port (5) through the drainage valve (21). A control arrangement (17) is configured for receiving a signal from the level gauge (15) and for controlling the drainage valve (21) such that the drainage valve is opened when liquid in the liquid- measuring chamber (9) reaches a threshold level (TH).
The method of manufacturing a component (40) of a turbomachine by powder metal hot isostatic pressing uses a container (41) defining outside surfaces (42A, 42B, 42C, 42D, 42E, 42F, 42G, 42H) of the component (40); a metal insert (443) is located inside the container (41) before filling the container (41) with metal powder; the insert (443) is left in the component (40) after the end of its manufacturing. Advantageously, a metal core (44) is located inside the container (41) before filling the container (41) with metal powder, the core (44) is removed from the component (40) before the end of its manufacturing. In this way, net shape surfaces may be obtained without manufacturing trials.
B22F 7/06 - Manufacture of composite layers, workpieces, or articles, comprising metallic powder, by sintering the powder, with or without compacting of composite workpieces or articles from parts, e.g. to form tipped tools
59.
METHOD FOR PREVENTING THE CORROSION OF AN IMPELLER-SHAFT ASSEMBLY OF A TURBOMACHINE
A method for preventing corrosion of an impeller-shaft assembly of a turbomachine comprises the steps of assembling an impeller (2) on a shaft (3) in order to define an impeller-shaft assembly (1); plating the assembly (1) by inserting said assembly (1) into a plating bath (12); coating at least a first predefined surface (5) on the impeller (2) and a second predefined surface (7) on the shaft (3), the coating step is performed by spraying the predefined surfaces (5, 7).
The component of the turbomachine comprises:a body (406) of the component, a bond layer (404) covering a base surface of the body (406), and a top layer (402) covering the bond layer (404) and made of abradable ceramic material; the base surface of the component has patterned protrusions (414) and, through two covering steps used for forming the bond layer (404) and the top layer (402), also the top surface of the component has patterned protrusions (410). The pattern protrusions of the base surface may be obtained in different ways, for example casting, milling, grinding, electric discharge machining or additive manufacturing. The patterned protrusions belong to an abradable seal of the turbomachine, and may be shaped and sized at best.
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
F01D 11/12 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible, deformable or resiliently biased part
61.
APPARATUS AND METHOD TO DETERMINE DISPLACEMENT OF A CONTINUOUS SURFACE OF A ROTATING ROTOR
Is described an apparatus for determining displacement of a continuous surface (51) of a rotating rotor (50), the apparatus comprising: at least a first proximity probe (20) facing said continuous surface (51), and adapted to repeatedly provide distance data of the area (11, 26) of said continuous surface during rotation of the rotor (50); a reference probe (5) adapted to detect a reference (10) on said rotor (50) and to provide reference phase data based on the rotations of the rotor (50); an electronic processing unit (6) connected to said proximity probe (20) and to said reference probe (5), and configured to carry out a selective sampling of distance data on the basis of reference phase data; wherein said selective sampling is programmed to obtain displacement information of at least a predetermined area (12) of said continuous surface (51) during rotation.
G01B 21/16 - Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring distance or clearance between spaced objects
G01H 1/00 - Measuring vibrations in solids by using direct conduction to the detector
G01B 5/16 - Measuring arrangements characterised by the use of mechanical techniques for measuring distance or clearance between spaced objects or spaced apertures between a succession of regularly spaced objects or regularly spaced apertures
G01B 7/15 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring distance or clearance between spaced objects or spaced apertures being regularly spaced
G01B 11/14 - Measuring arrangements characterised by the use of optical techniques for measuring distance or clearance between spaced objects or spaced apertures
62.
METHOD OF MONITORING RUBBING BETWEEN A ROTARY PART AND A STATIONARY PART IN A ROTATING TURBOMACHINE, MONITORING ARRANGEMENT AND TURBOMACHINE
The arrangement for monitoring rubbing between a rotary part and a stationary part in a rotating turbomachine comprises: at least one mechanical oscillations detector (11, 12, 13) for measuring mechanical oscillations at least one point of the turbomachine, at least one particles detector (21) for measuring debris passing in at least one section of a flow path of the turbomachine, and an electronic monitoring unit (50) electrically or electromagnetically connected to the oscillations detector and the particles detector (21), and arranged to acquire and process signals generated by the oscillations detector and the particles detector; the electronic monitoring unit (50) uses the oscillations measurement primarily for estimating presence of rubbing and the debris measurement primarily for estimating severity of rubbing.
F01D 21/00 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for
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
63.
METHOD OF PROTECTING A COMPONENT OF A TURBOMACHINE FROM LIQUID DROPLETS EROSION, COMPONENT AND TURBOMACHINE
The method of protecting a component of a turbomachine from liquid droplets erosion provides covering at least one region of a component surface exposed to a flow of a fluid containing a liquid phase to be processed by the turbomachine with a protective layer; the protective layer consists of a plurality of adjacent sub-layers of different materials having high hardness in the range of 1000-3000 HV and low fracture toughness below 20 MPam1/2; the materials are typically nitrides or carbides of titanium or aluminum or chromium or tungsten; advantageously, the covering is carried out by a PVD technique, in particular by Cathodic Arc PVD, or a CVD technique. The method may be applied to any component of turbomachines, but it is particularly advantageous for parts of centrifugal compressors.
A scroll for use in conjunction with a fluid compressor is described. The scroll (13) comprises a fluid inlet (17) adapted to receive a fluid flow and a fluid outlet (23) adapted to discharge the fluid flow. The scroll (13) further comprises a scroll-shaped wall (19) defining an inner flow volume (21). At least one blade (15) is provided in the inner flow volume (21) of the scroll. The blade (15) is configured and arranged for correcting a direction of the flow of fluid in the flow volume when the scroll is operating in off-design conditions.
A drive system for driving at least one compressor is described. The system comprises a gas turbine configured and arranged for driving the compressor. The gas turbine has a hot end and a cold end. A load coupling for connection of said gas turbine to the compressor is arranged at hot end of the gas turbine. An electric motor/generator arranged at the cold end of the gas turbine. The electric motor/generator is electrically connected to an electric power grid and is adapted to function as a generator for converting excess mechanical power from the gas turbine into electrical power and delivering the electrical power to the electric power grid, and as a motor for supplementing driving power to the compressor.
Method of starting a gas turbine, comprising the steps of providing an apparatus (1) for regulating the flow of fuel in a gas turbine, the apparatus (1) comprising a main line (4) connecting a fuel source (2) to a nozzle array (N); an auxiliary line (8) connecting the fuel source (2) to the nozzle array (N); the method further comprises the steps of keeping the main line (4) sealed while increasing the auxiliary line (8) fuel flow rate; firing the gas turbine while keeping the main line (4) sealed; after the combustion has started in the gas turbine, opening the main line (4) for increasing the main line (4) fuel flow rate; the auxiliary line (8) maximum flow rate is less than the main line (4) maximum flow rate.
A turbomachine assembly (1) comprises: -a shaft (10), -a radial gas expander (2) supported on the shaft (10) between at one first bearing (11) and a second bearing (12), -a compressor (3) supported on the shaft(10) in overhung position adjacent to one or the other of said first and second bearings, -said compressor (3) including a plurality of movable inlet nozzles (20) and said radial gas expander (2) including a plurality of movable guide vanes (5a,b).
The compressor system comprises a compressor (1) having first compressor stage (1A) and a second compressor stage (1B) in a back-to-back arrangement. A first gas flow (Fl) is provided at the suction side of the compressor (1). A seal arrangement (17) is provided between the first compressor stage (1A) and the second compressor stage (1B). A side stream line (19) is in fluid communication with the suction side (12) of the second compressor stage (1B). A side stream valve (20) on the side stream line (19) and a side stream controller (22) are provided, for adjusting the flow (F2) of the second gas. An antisurge arrangement comprised of a bypass line (21) and an antisurge valve (23) is arranged at the first compressor stage for preventing surge of the first compressor stage. The side stream controller (22) is configured for reducing the flow (F2) of the second gas when an alteration of the pressure ratio across the first compress stag (1A) is detected, provoked by a recirculation of gas through the antisurge arrangement.
Gas turbines, centrifugal and axial compressors, pipeline compressors, turbocompressors, motocompressors, turbo engines, electric motors and generators, turbogenerators and moto generators for pipeline applications in the Oil and Gas Industry.
70.
BASE UNIT FOR ASSEMBLING A CRANKCASE OF A RECIPROCAL COMPRESSOR
A base unit (1) for assembling a crankcase (101) of a reciprocal compressor comprises a housing (2) configured to hold at least part of a crankshaft (100); an access port (3) placed onto the housing (2) and configured to hold a connecting rod for a piston; the base unit (1) having at least an interface zone (4) on the housing (2), configured to be coupled with another interface zone (4) of another base unit (1) for assembling the crankcase (101).
F04B 27/053 - Multi-cylinder pumps specially adapted for elastic fluids and characterised by number or arrangement of cylinders having cylinders in star- or fan-arrangement with an actuating element at the inner ends of the cylinders
F04B 27/04 - Multi-cylinder pumps specially adapted for elastic fluids and characterised by number or arrangement of cylinders having cylinders in star- or fan-arrangement
F04B 39/00 - Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups
The system for driving a reciprocating compressor comprises a reciprocating compressor (1) with a crankshaft (31). A Stirling engine (50) is drivingly connected to the crankshaft (31) of the reciprocating compressor (1). A heat source (71), for example a waste heat source, provides heat to the hot end of the Stirling engine. Heat is partly converted into mechanical power to drive the reciprocating compressor (1).
The CNG system comprises a gas inlet line (14) and a reciprocating compressor (41) arranged and configured for compressing gas from the gas inlet line and delivering compressed gas towards a dispenser (140; 142). A Stirling engine (47) is drivingly connected to the reciprocating compressor. A burner (48) receives gas from the gas inlet line and generates thermal energy for powering the Stirling engine.
F02G 1/043 - Hot gas positive-displacement engine plants of closed-cycle type the engine being operated by expansion and contraction of a mass of working gas which is heated and cooled in one of a plurality of constantly communicating expansible chambers, e.g. Stirling cycle type engines
F04B 35/00 - Piston pumps specially adapted for elastic fluids and characterised by the driving means to their working members, or by combination with, or adaptation to, specific driving engines or motors, not otherwise provided for
F17C 5/06 - Methods or apparatus for filling pressure vessels with liquefied, solidified, or compressed gases for filling with compressed gases
73.
RECIPROCATING MOTOR-COMPRESSOR WITH INTEGRATED STIRLING ENGINE
The reciprocating motor-compressor comprises a frame (3) wherein a crankshaft (5) is rotatingly housed. Compressor pistons (17A, 17B) are drivingly connected to the crankshaft (5) and are reciprocatingly moved thereby in respective compressor cylinders (13A, 13B). The crankshaft is driven into rotation by an embedded Stirling engine (1B). The Stirling engine comprises at least a hot cylinder (53) and a cold cylinder (73), wherein a respective hot piston (55) and a respective cold piston (75) are reciprocatingly moving. Thermal power is provided to the hot cylinder and partially converted into mechanical power for driving the reciprocating compressor.
F02G 1/043 - Hot gas positive-displacement engine plants of closed-cycle type the engine being operated by expansion and contraction of a mass of working gas which is heated and cooled in one of a plurality of constantly communicating expansible chambers, e.g. Stirling cycle type engines
F01D 15/08 - Adaptations for driving, or combinations with, pumps
F04B 35/00 - Piston pumps specially adapted for elastic fluids and characterised by the driving means to their working members, or by combination with, or adaptation to, specific driving engines or motors, not otherwise provided for
74.
MULTISTAGE TURBOMACHINE WITH EMBEDDED ELECTRIC MOTORS
A multistage turbomachine (1) is disclosed, comprising a casing (3) with a fluid inlet (5) and a fluid outlet (7), and a plurality of stages (13A, 13B) arranged in the casing (3). A flow path extends from the fluid inlet (5) to the fluid outlet (7) through the sequentially arranged stages (13A, 13B). Each stage is comprised of a rotating impeller (17A, 17B) and an electric motor embedded in the casing (3) and arranged for rotating the impeller (17A, 17B) at a controlled rotary speed. Each electric motor comprises a motor rotor (31A, 31B), arranged on the impeller (17A, 17B) and integrally rotating therewith, and a motor stator (33A, 33B) stationarily arranged in the casing (3). Pairs of sequentially arranged impellers are configured for rotation in opposite directions.
A centrifugal compressor impeller 9 is disclosed. The impeller comprises a gas inlet and a gas outlet. The impeller moreover comprises a disc 23 having a plurality of blades 25 extending therefrom. Each blade 25 has a leading edge 25L at the impeller inlet and a trailing edge 25T at the impeller outlet, as well as a blade base extending along the disc 23 between the leading edge and the trailing edge, a blade tip extending between the leading edge and the trailing edge opposite the disc, a pressure side and a suction side. Each blade 25 has a three-dimensional curvature in at least a portion of the surface thereof, adjacent the leading edge 25L. The leading edge of each blade has a curved, non-linear profile in a meridian plane. The blade portion adjacent the leading edge has a double-curvature. Starting at the leading edge 25L and for at least a portion of the blade 25, each blade has a first metal angle distribution at the blade base, a second metal angle distribution at the blade tip and at least a third metal angle distribution at an intermediate location between the blade base and the blade tip, such that the suction side and pressure side are concave and convex, or vice-versa, depending upon the shape of the leading edge.
A compressed-air energy-storage system (1) is described. The system comprises: a first compressor arrangement (3) for compressing an air stream; a thermal energy storage unit (13), where through compressed air from the first compressor arrangement (3) exchanges heat against a heat accumulation means; an air storage device (17) arranged and configured for receiving and accumulating compressed air from the thermal energy storage unit (13); at least one expander (21) for receiving compressed air from the air storage device (17) and producing useful power therefrom. A further compressor arrangement (15) is located between the thermal energy storage unit (13) and the air storage device (17).
The impeller comprises a main body with a root (1), a shroud (2) and a plurality of blades (3) connecting the root and the shroud; protection elements (10) are associated to the blades (3) and constitute at least the front part of the blades (3); the protection elements (10) may consist of separate bodies or may be grouped together to form one or more protection bodies; advantageously, the material of the protection elements is different from the material of the main body, and may be, for example, a cobalt base alloy having a chromium content greater than 20% or nickel base alloy having a chromium content greater than 12%.
A multi-section centrifugal compressor (1) comprises at least a first (2) and a second section (3); each section (2, 3) has an inlet duct (7, 8) and a discharge duct (9, 10), the discharge duct (9) of the first section (2) is placed in fluid communication with the inlet duct (8) of the second section (3), the second section (3) is configured to compress a fluid compressed by the first section (2); the discharge duct (10) of the second section (3) is adjacent to the inlet duct (7) of the first section (2).
An apparatus (1) for sealing an internal environment of a turbomachine, comprises a first chamber (2) connectable in fluid communication with a high pressure environment (HP) of a turbomachine (100) so that a working fluid can flow from the high pressure environment (HP) to the first chamber (2); a second chamber (3) in fluid communication with a lubrication circuit ( 106) so that a lubricant can flow from the lubrication circuit (106) to the second chamber (3); the first (2) and second chambers (3) are arranged in fluid communication with each other so that the working fluid can flow from the first (2) to the second chamber (3); a return line (4) for the working fluid in fluid communication with the first chamber (2) and connectable in fluid communication with a low pressure environment (LP) of the turbomachine (100) so that the working fluid can flow from said first chamber (2) to said low pressure environment (LP); a pressure regulating device (5) along the return line (4) configured to provide a predetermined pressure drop.
A set of impellers (1A, 5B, 1C, 5D, 1E) that are axially adjacent to each other and that have respective axial through holes (2A, 6B, 2C, 6D, 2E) are assembled; at least a first and a second axial tie rods (4A, 4B, 4C) are used; at least one connection element (5B, 5D) being axially adjacent to two impellers (1A, 1C, 1C, 1E) respectively at its two sides and having an axial through hole (6B, 6D) is provided; the connection element (5B, 5D) is used for securing, at one side of its axial through hole (6B, 6D), an end of the first axial tie rod (4A, 4B) and, at the other side of its axial through hole (6B, 6D), an end of the second axial tie rod (4B, 4C); typically and advantageously, the connection element (5B, 5D) is one of the impellers (1A, 5B, 1C, 5D, 1E) of the set.
The off-shore gas turbine system comprises a floating structure with at least one deck (25) and a baseplate (31) mounted on the deck. The baseplate supports a gas turbine (1) having: a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, an intermediate pressure turbine and a low pressure turbine. The low pressure compressor is driven into rotation by the intermediate pressure turbine and the high pressure compressor is driven by the high pressure turbine. The low pressure turbine has a load coupling. The system further comprises a driven equipment (57, 59) mechanically connected to the load coupling (21) of the low pressure turbine and driven into rotation by the low pressure turbine. An intercooler (19) is provided between the low pressure compressor and the high pressure compressor and connected to them through displacement-tolerant connections. The baseplate (31) is supported on the deck (25) separately from the intercooler (19).
The off-shore gas turbine system comprises a floating structure with at least one deck (25) and a baseplate (31) mounted on the deck. The baseplate supports a gas turbine (1) having: a low pressure compressor, a high pressure compressor, a combustor, a high pressure turbine, an intermediate pressure turbine and a low pressure turbine. The low pressure compressor is driven into rotation by the intermediate pressure turbine and the high pressure compressor is driven by the high pressure turbine. The low pressure turbine has a load coupling. The system further comprises a driven equipment (57, 59) mechanically connected to the load coupling (21) of the low pressure turbine and driven into rotation by the low pressure turbine. An intercooler (19) is provided between the low pressure compressor and the high pressure compressor and connected to them through displacement-tolerant connections. The baseplate (31) is supported on the deck (25) separately from the intercooler (19).
A double-effect reciprocating compressor is described. The compressor comprises a cylinder (3) and a reciprocatingly moving arrangement comprised of a piston (7), a crosshead (37) and a piston rod (15) connecting the crosshead to the piston. A crank-shaft (31) drives the reciprocatingly moving arrangement into reciprocating motion via a connecting rod (33). At least one part of the piston and of the piston rod is at least partly made of a composite material.
F04B 39/00 - Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups
84.
METHODS OF WASHING GAS TURBINE ENGINES AND GAS TURBINE ENGINES
Washing of the gas turbine engine, during operation of the gas turbine engine, comprises a washing phase that consists in spraying (4) a detergent liquid substance towards the inlet of the compressor (1) of the engine; the mass flow of the detergent liquid substance to be sprayed is set so that the liquid-to-gas ratio at the inlet of the compressor (1) is more than 1% and less than 5% with reference to the rated mass flow of the compressor (1); the washing phase comprises a first sub-phase during which the flow of the detergent liquid substance is increased gradually and a second sub-phase during which the flow of the detergent liquid substance is maintained constant.
The nozzle (4) is used for spraying a liquid substance towards a compressor (1) of a gas turbine engine, and comprises: - an elongated body (20) having an end for ejecting the liquid substance, - a conduit (21) for said liquid substance internal to said elongated body (20) and extending up to said end, - a recess (22) located at said end, wherein said conduit (21) ends in said recess (22); wherein said recess (22) opens towards the lateral surface of said elongated body (20), typically a cylindrical body, and said conduit (21) is tangential to the bottom of said recess (22).
The tool to measure the radial stacking angle of a cylindrical blade (1) comprises: a base (6c) configured to indicate a radial direction (R) of the hub (3), a component (7) slidable over the blade (1) and configured to indicate the stacking direction (S) of the cylindrical blade (1), reference elements (60) to provide a reference scale, a setting element (13) configured to set the position of the component (7) with respect to the base (6c), a marker element (14) configured to indicate the magnitude of the angle between the stacking direction and the radial direction using the reference elements (60); the angle corresponds to the radial stacking angle.
A shaftless motor-compressor (1) is disclosed, comprising a casing (3) and at least one compressor stage (9A, 9B) arranged in the casing. Each compressor stage comprises a respective impeller (11A, 11B) arranged for rotation in the casing (3) around a rotation axis (A-A). Each impeller (11A, 11B) is combined with an embedded electric motor (13A, 13B) housed in the casing (3) and comprised of a motor stator (15A, 15B) and a motor rotor (17A, 17B). The motor stator (15A, 15B) of each compressor stage (9A, 9B) circumferentially surrounds the impeller (11A, 1B) and the motor rotor (17A, 17B), integral with the impeller. The motor rotor (17A, 17B) of each stage (9A, 9B) is arranged inside the respective motor stator.
A control valve (1) comprising: a cylindrical hollow trim (2) defining an inner bore (5) extending along an axis (Y) between a first opening (3) and a second opening (4), said first opening (3) defining an inlet of said valve (1), said trim (2) comprising: a first outer cylinder (11) extending along said axis (Y) and comprising a first plurality (14) of radial through holes defining an outlet, a second cylinder (12), housed in said first cylinder (11) and coaxial therewith, said second cylinder comprising a second plurality (15) of radial through holes, said holes of said first plurality (14) being smaller and in greater number than the holes of said second plurality (15), for each hole (14, 15) of one of said first and second cylinders (11, 12) the projection along a radial direction on the other of said first and second cylinders (12, 11) being spaced from each hole (15, 14)of the other of said first and second plurality a plug (6) sized to fit inside the bore (5) and slidably movable along said axis (Y).
A piston-cylinder assembly (1) for a reciprocating compressor comprises a cylinder (2); a piston (4) inside the cylinder (2), the piston (4) defining a first (6) and a second working chamber (7) for compressing a working fluid; the working chambers (6, 7) having each an intake opening (6a, 7a) and a discharge opening (6b, 7b) for the working fluid; a flow regulator (9) acting on the working chambers (6, 7) for controlling an outgoing flow of working fluid through said discharge openings (6b, 7b), the flow regulator (9) comprising a bypass duct (10) in fluid connection with the first (6) and with the second working chamber (7), at least a regulating valve (16) located along the bypass duct (10) for opening and/or closing the bypass duct (10) so that the fluid can flow between the first (6) and the second working chamber (7), wherein said bypass duct (10) is placed inside the piston (4).
F04B 7/00 - Piston machines or pumps characterised by having positively-driven valving
F04B 39/00 - Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups
90.
CROSSHEAD-PISTON ROD ASSEMBLY FOR A RECIPROCATING COMPRESSOR
A crosshead-piston rod assembly for a reciprocating compressor comprises: a piston rod (4), a crosshead (3) having a bore (5); a connection element (6) attached to the piston rod (4) and at least partially inserted into the bore (5) for connecting the crosshead (3) to a piston.
F04B 39/00 - Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups
F16C 5/00 - CrossheadsConstructions of connecting-rod heads or piston-rod connections rigid with crossheads
F16J 1/16 - Connection to driving members with connecting-rods, i.e. pivotal connections with gudgeon-pinGudgeon-pins
Awashing system is described for a gas turbine engine with an axial compressor (3), comprising: an inlet screen (30) at the air flow inlet of the compressor (3) to protect the compressor (3) from foreign object damage, an arrangement of nozzles and manifolds for spraying the washing liquid, and a washing liquid supply system connected to the arrangement; the inlet screen (30) comprises a supporting structure (10, 11, 12) and a filtering net (19) fixed to the supporting structure (10, 11, 12); the arrangement of nozzles and manifolds is integrated in said supporting structure of the inlet screen. FIGURE
F02C 7/052 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
F02C 7/055 - Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with intake grids, screens or guards
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
The centrifugal compressor impeller (9) comprises an inlet, an outlet and a disk (23) extending from the inlet to the outlet. A plurality of blades (25) extend from the disk (23), each blade having a leading edge (25L) at the inlet, a trailing edge (25T) at the outlet, a blade base (25B) extending along the disk between the leading edge and the trailing edge, and a blade tip (25A) extending between the leading edge and the trailing edge opposite the disk. The trailing edge is S-shaped with an intermediate inflection.
A crosshead (1) for a piston rod comprises a main body (3) having a first seat (5) and a second seat (6) being configured to hold a connecting rod (2), said second seat (6) being configured to hold a piston rod (4); said main body (3) comprising a linking portion (3a) defining at least partially said first seat (5) and said second seat (6) for holding respectively the connecting rod (2) and the piston rod (4); said main body (3) comprising a closing portion (3b) defining at least partially said second seat (6) and being configured to secure said piston rod (4) inside said second seat (6).
F16C 5/00 - CrossheadsConstructions of connecting-rod heads or piston-rod connections rigid with crossheads
F16J 1/16 - Connection to driving members with connecting-rods, i.e. pivotal connections with gudgeon-pinGudgeon-pins
F04B 39/00 - Component parts, details, or accessories, of pumps or pumping systems specially adapted for elastic fluids, not otherwise provided for in, or of interest apart from, groups
A coupling guard (1) for a rotating member (15) comprises: a shell (11) surrounding the rotating member (15), a plenum (25) disposed in the shell (11), at least an injection tube (12) for injecting a cooling gas and an outlet (13) for discharging the cooling gas, wherein said injection tube (12) extends through said plenum (25) from a first axial opening (31) proximal to said shell (11) to a second axial opening (32) proximal to said rotating member (15), said injection tube (12) having a leading edge (41) which first contacts the gas circulating in the plenum and a trailing edge (42) opposite to the leading edge (41), said second opening (32) having a first portion (32a) orthogonal to the axis (X) of said injection tube (12) and a second portion (32b) across said trailing edge (42), adjacent to said first portion (32a) and parallel to the axis (X) of said injection tube (12).
A method for manufacturing a stage (1) of a steam turbine comprising the steps of milling a block of material to define a sector (2) having a plurality of blades (6), each blade (6) having an external surface (7); machining an opening (8) in the external surface (7) of at least one of the blades (6); machining a cavity (9) in fluid communication with the opening (8); the step of machining the cavity (9) being performed by wire electric discharge machining.
A turbo machine (100) comprising a barrel casing (1) having a cylindrical internal surface defining an internal containment volume, a bundle (5) having a cylindrical shape, adapted to be accommodated into said internal containment volume, a cylindrical cover (2) connected to the bundle (5) to close said internal containment volume and hold the bundle (5) inside the barrel casing (1), a split shear ring (3) adapted to fix said barrel casing (1) with said cylindrical cover (2) wherein the external cylindrical surface of the cylindrical cover (2) and the cylindrical internal surface of the barrel casing (1) are provided with a first circumferential groove (6) and a second circumferential groove (4) adapted to accommodate said shear ring (3) and wherein said first grooves (6) is adapted to completely accommodate the cross section of said split shear ring (3).
The turbomachine (1) comprises a stationary component (7), a rotary component (11), rotatingly supported in the stationary component (7), and a sealing arrangement (21) between the rotary component and the stationary component. A cooling arrangement (29) is further provided, which is configured and designed for delivering a cooling fluid to the sealing arrangement and removing heat therefrom.
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
F04D 29/16 - Sealings between pressure and suction sides
F04D 29/58 - CoolingHeatingDiminishing heat transfer
98.
POWER PLANTS WITH AN INTEGRALLY GEARED STEAM COMPRESSOR
The power plant comprises an integrally geared vapor compressor arrangement (300), comprised of a bull gear (313) and a compressor shaft (315) with a pinion (317) meshing with the bull gear. The plant further comprises a vapor source (301), fluidly connectable with an inlet of the integrally geared vapor compressor arrangement (300). A vapor turbine arrangement (327, 329) is fluidly connectable with an outlet of the integrally geared vapor compressor arrangement for receiving a stream of compressed and superheated vapor from the integrally geared vapor compressor arrangement. An electric generator (331) driven by the vapor turbine arrangement converts mechanical power produced by the vapor turbine arrangement into electric power.
An automatic ring valve (10) comprising a valve seat (12) provided with a plurality of gas flow passages (14) arranged according to at least one annular row, at least a shutter comprising at least one ring-shaped portion (18) for selectively closing and opening the gas flow passages (14), wherein said ring-shaped portion of the shutter comprises a fiber-reinforced matrix (40), at least one contrasting member for contrasting an opening movement of ring-shaped portion of the shutter, wherein said ring-shaped portion of the shutter comprises continuous fibers, at least some of said fibers developing for at least 360° of the annular development of the ring-shaped portion.
A polishing method is described for polishing a machine component (1A, IB) comprising at least one airfoil portion (7) comprised of a suction side (7S), a pressure side (7P), a leading edge (7A) and a trailing edge (7B). The method provides for arranging the machine component (1A, IB) in a container (11) and constraining the machine component (1A, IB) to the container (11). A polishing mixture (M) is added in the container (11), and the container (11) is caused to vibrate together with the machine component (1A, IB) constrained thereto, thereby generating a polishing mixture (M) flow along the airfoil portion (7) until a final arithmetic average roughness is achieved.
B24B 19/14 - Single purpose machines or devices for particular grinding operations not covered by any other main group for grinding turbine blades, propeller blades or the like
B24B 31/06 - Machines or devices designed for polishing or abrading surfaces on work by means of tumbling apparatus or other apparatus in which the work or the abrasive material is looseAccessories therefor involving oscillating or vibrating containers
B23P 15/00 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
