A masking apparatus (110; 600) for masking a part (20) during coating and comprising at least two sintered pieces (112, 114, 116, 118) of a mask material. The pieces (112, 114, 116, 118) have an assembled condition forming a compartment shaped to accommodate an airfoil (22; 608) of the part (20). The pieces (112, 114, 116, 118) have an average overall composition of: alumina and in one or more phases of a remainder nickel as a largest by-weight constituent aluminum as a second largest by-weight constituent and chromium as a third largest by-weight constituent.
C23C 24/08 - Coating starting from inorganic powder by application of heat or pressure and heat
C23C 24/10 - Coating starting from inorganic powder by application of heat or pressure and heat with intermediate formation of a liquid phase in the layer
C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
F01D 11/02 - Preventing or minimising internal leakage of working fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
A method for fabricating a composite material using chemical vapor infiltration, comprising: providing one or more fibrous preforms and a porous dummy preform; positioning the fibrous preforms proximate to the porous dummy preform and an area where a poisoning molecule is generated within a reaction chamber of a chemical vapor infiltration assembly; heating the reaction chamber to a chemical vapor infiltration temperature for matrix densification; introducing into the reaction chamber a matrix precursor gas; reacting the matrix precursor gas with the porous dummy preform to deposit a matrix material and generate a poisoning molecule; depositing uniformly one or more coating layers of the matrix material on and within the fibrous preforms; and fabricating one or more composite materials.
C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
A gas turbine engine (800) rotor (150) has: a shaft (98) having an outer diameter groove (100) having a forward surface (104), an aft surface (102), and an inner diameter base surface (106); a seal ring in the groove and having a forward surface (34), an aft surface (36), and an outer diameter (OD) surface (30); and a disk (152) having an inner diameter (ID) surface (156) with a portion (110) facing or contacting the seal ring OD surface. Along at least one of the disk ID surface portion, a portion of said groove forward surface, and a portion of said groove aft surface a layering is formed from WC-Co and MCrAlY (214, 224).
A component protection casing (10) includes a first segment (14a) that includes a first bias means (16) configured to impart a bias load to a first surface (12b) of a gas turbine engine component, a second segment (14b) that includes a second bias means (18) to impart a bias load to a second surface (12c) of the gas turbine engine component, and a latch mechanism (14c) configured to fasten the first segment to the second segment when the first segment and second segment are positioned in a closed configuration and the latch mechanism is engaged. The first segment and second segment are configured to receive and fully surround damage susceptible portions of a gas turbine engine component. The first bias load and second bias load are selected to secure the gas turbine engine component inside the component protection case when the first segment and second segment are positioned in a closed configuration and the latch mechanism is engaged.
In a method (804) for coating a metallic blade (20) substrate (22), the blade substrate has: an airfoil section (40); a root section (42); and a platform section (44) between the root section and the airfoil section. The method comprises: applying (844, 846) a maskant to a portion of an underside (52) of the platform bearing an MCrAlY coating and a portion of the root lacking an MCrAlY coating; and heating (848), the heating causing aluminum depletion from the MCrAlY into the maskant.
An aircraft propulsion system includes a core engine that includes a core flow path through a main compressor where an inlet airflow is compressed and communicated to a combustor to generate an exhaust gas flow that is expanded through a main turbine section to generate power used to drive the main compressor and a propulsive fan. A water augmentation system includes a tank where water is stored and at least one location where water is communicated into the core flow path, and a controller programmed to operate the water augmentation system according to a selected mode of operation, a detected quantity of water and other conditions impacting engine operation.
F02C 3/30 - Adding water, steam or other fluids to the combustible ingredients or to the working fluid before discharge from the turbine
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
F01N 3/04 - 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 liquids
F02C 9/28 - Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
344-BN multilayer coating having one or more alternating layers comprising at least one layer of silicon nitride at a first thickness; and at least one layer of boron nitride at a second thickness.
9.
HYBRID COATING FOR ENHANCED CMAS RESISTANCE OF THERMAL BARRIER COATING
A method for coating a substrate (22) includes: applying a columnar ceramic coating (26); infiltrating the ceramic coating; and sealing the infiltrated ceramic coating. The infiltrating is via melt infiltration or sol-gel infiltration and the sealing is via ALD, PVD, CVD, or thin film deposition. The coated substrate may be a gas turbine engine component.
C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
A method is provided for densifying a ceramic matrix composite (CMC) preform in which a porous CMC preform is subjected to slurry infiltration wherein metal carbide particulate material is introduced into the spaces between fiber tows of the CMC preform to form an infiltrated CMC preform. Thereafter, molten metal or molten metal alloy is introduced into the infiltrated CMC preform by melt infiltration to react the metal or molten metal alloy with the metal carbide particulate material and create a ceramic matrix within the CMC preform forming a ceramic matrix composite. The metal carbide particulate material is selected from zirconium carbide particles, hafnium carbide particles, tantalum carbide particles, niobium carbide particles, titanium carbide particles, tungsten carbide particles, cobalt carbide particles, vanadium carbide particles, chromium carbide particles, ytterbium carbide particles, yttrium carbide particles, tantalum hafnium carbide particles, and mixtures thereof.
An article (20) has a metallic substrate (22) and a coating (28) atop the substrate. The coating has an at least local composition by weight percent of: Ni as a largest by weight content; 14.00 to 18.00 Cr; 20.00 to 24.00 Co; 11.00 to 13.50 Al; 0.40 to 0.80 Y; 0.10 to 0.40 Hf; 0.30 to 0.70 Si; to 0.02 C, if any; to 0.01 S, if any; to 0.01 P, if any; to 0.40 Fe, if any; to 0.10 Mo, if any; 0.05 to 0.90 Ta; to 0.40 W, if any; to 0.60 Zr, if any; and to 1.0 other, if any, total. In weight percent, one or more of: Zr+W+Ta+Fe is 0.50 to 1.30; Zr+W is 0. 40 to 0.90; and Zr+W+Ta is 0.40 to 1.10.
C22C 19/03 - Alloys based on nickel or cobalt based on nickel
C22C 19/05 - Alloys based on nickel or cobalt based on nickel with chromium
C23C 28/02 - Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of main groups , or by combinations of methods provided for in subclasses and only coatings of metallic material
C23C 4/073 - Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
B32B 15/01 - Layered products essentially comprising metal all layers being exclusively metallic
12.
Hexavalent Chromium-Free Stripping Bath and Process for Aluminum Anodizing Removal
33 in mM. The solution may include: 5 mM to 75.0 mM combined Zr4+, Mo6+, Nb5+, and Cr3+; and/or at least one of 8-hydroxyquinoline, 2-quinolinecarboxylic acid, salicylaldoxime, and benzotriazole.
A method for fabricating a melt-infiltrated ceramic matrix composite, comprising the steps of providing a ceramic preform comprising at least one fiber, fiber bundle, or fiber tow; optionally depositing an interface coating on the fiber, fiber bundle or fiber tow; fabricating a structure comprising a carbon-containing coating within the ceramic preform; infiltrating at least one molten metal, one molten metalloid, molten metal alloy, or molten metalloid alloy, within the ceramic preform and in contact with the structure; and reacting the molten metal, molten metalloid, molten metal alloy, or molten metalloid alloy, with the carbon-containing coating present on or within the structure to form the melt-infiltrated ceramic matrix composite.
A method for fabricating a metal-infiltrated ceramic matrix composite, comprises: providing a ceramic fiber preform comprising a fiber tow; depositing an interface coating material around the fiber tow to form an interface coating therearound, and form an interfaced coated ceramic preform containing the interface coated fiber tows; depositing a silicon carbide layer around the interface coated fiber tow; depositing a reaction-barrier coating around the interface coated, silicon carbide coated fiber tow of the interface coated, silicon carbide coated ceramic preform; infiltrating the interface coated, silicon carbide coated ceramic preform with a slurry comprising a carbon source; drying the slurry infiltrated interface coated, silicon carbide coated ceramic preform; and infiltrating the dried slurry infiltrated interface coated, silicon carbide coated ceramic preform with a molten ternary metal alloy, a molten ternary metalloid alloy, a molten ternary metal alloy comprising boron as a constituent, a molten ternary metalloid alloy comprising boron as a constituent, a ternary metal melt, a ternary metalloid melt, a ternary metal melt comprising boron as a constituent, or a ternary metalloid melt comprising boron as a constituent, combinations comprising at least one of the foregoing; to form a melt-infiltrated ceramic matrix composite.
x1xx2y1yy2y2, wherein y is 1, 2, 3, 4 or 5; y1 and y2 are each independently 0 or 1; and, y + y2 ≥ 2; and, an outermost layer of SiBN, and methods for protecting, including making, a fiber or a ceramic matrix material containing the fiber from degradation, by coating the fiber.
A coated fiber, which may be present in a ceramic matrix composite material, having layers in the following order: immediately on the fiber, an optional SiN layer, e.g., amorphous SiN layer, immediately on the SiN layer or fiber a carbon layer, immediately on the carbon layer a hexagonal BN layer (h-BN) layer, wherein the h-BN layer is a temperature gradient h-BN layer, wherein a high temperature h-BN is immediately on the carbon layer followed by a lower temperature h-BN through a temperature gradient, or the h-BN layer contains at least two distinct h-BN sub-layers, wherein the carbon layer followed by the h-BN layer provides a carbon and h-BN layer sequence that can be present 1, 2, 3, 4 or 5 times sequentially without any further layers therebetween, and an outermost layer of SiBN, which layers are useful for protecting a fiber or a ceramic matrix material containing the fiber from degradation.
x1xx2>> 2; and, an outermost layer of SiBN, as well as a method for protecting a fiber or a ceramic matrix material containing the fiber from degradation, by coating the fiber.
A method and apparatus coat an airfoil tip (105) with an abrasive (120;304) held by a matrix. The coating may be of an individual blade (20) airfoil or of multiple airfoils integral with a rotor (200). The method includes laser (910) securing an abrasive (120; 304) to a substrate (101). The abrasive is held down such as by a transparent plate (902) or a roller (300) during solidification of a powder (129, 305) melted by the laser.
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
A bipolar plate for a battery includes a metal sheet that has a first side and a second, opposite side. The metal sheet is folded so as to form a series of loops on the second side. The loops are spaced apart to define flow field passages therebetween on the second side. Each of the loops is bonded along an edge at the first side so as to enclose an internal passage.
H01M 8/0228 - Composites in the form of layered or coated products
H01M 8/0254 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the form corrugated or undulated
H01M 8/026 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant characterised by grooves, e.g. their pitch or depth
H01M 12/08 - Hybrid cellsManufacture thereof composed of a half-cell of a fuel-cell type and a half-cell of the secondary-cell type
H01M 8/0267 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors having heating or cooling means, e.g. heaters or coolant flow channels
H01M 8/0263 - CollectorsSeparators, e.g. bipolar separatorsInterconnectors characterised by the configuration of channels, e.g. by the flow field of the reactant or coolant having meandering or serpentine paths
20.
MULTI-ALLOY AIRFOIL PRODUCED VIA ADDITIVE MANUFACTURING
A substrate of an airfoil element (20) is manufactured via directed energy deposition (DED) from a first source (708A) and a second source (708B). The substrate has: an airfoil having a pressure side wall (82) and a suction side wall (84) and a plurality of ribs (80A, 80B; 80A... 80F) joining the pressure side wall to the suction side wall. The method includes: DED of the ribs at least partially from the first source; and DED of the pressure side wall and suction side wall at least partially from the second source and at least partially from the first source so that a composition of the pressure side wall and suction side wall differs from a composition of the plurality of ribs.
B22F 5/04 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
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
B22F 10/25 - Direct deposition of metal particles, e.g. direct metal deposition [DMD] or laser engineered net shaping [LENS]
B22F 12/55 - Two or more means for feeding material
F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
F01D 9/06 - Fluid supply conduits to nozzles or the like
F01D 11/08 - Preventing or minimising internal leakage of working fluid, e.g. between stages for sealing space between rotor blade tips and stator
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
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
A blade fuel injector (74) for a gas turbine engine, including: a mixer (108), the mixer (108) having a first set of openings (114,116) located on opposite sides of the mixer (108) and a second set of openings (118) located below the first set of openings (114, 116); and a blade injector (110), the blade injector (110) having a plurality of atomizers (112), wherein some of the first set of openings (114, 116) align with the plurality of atomizers (112).
A chemical vapor infiltration (CVI) reactor includes a body defining an internal volume, an inlet for receiving a flow of reactive gas, an outlet for exhausting the flow of reactive gas, a dedicated fluid pathway for transporting the flow of reactive gas extending from the inlet, and a plurality of vertically stacked plates defining a plurality of levels, each of the plurality of plates including at least one channel disposed within the plate and in fluid communication with the dedicated fluid pathway, and a plurality of holes extending from the at least one channel to a surface of the plate.
C23C 16/04 - Coating on selected surface areas, e.g. using masks
C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
C23C 16/458 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for supporting substrates in the reaction chamber
C23C 16/52 - Controlling or regulating the coating process
23.
MULTI LEVEL INJECTOR FOR CHEMICAL VAPOR INFILTRATION REACTOR
A chemical vapor infiltration (CVI) reactor includes a body defining an internal volume, at least one inlet for receiving a flow of reactive gas, at least one outlet for exhausting the flow of reactive gas, a plurality of vertically stacked plates defining a plurality of levels, and at least one dedicated fluid pathway for transporting the flow of reactive gas, the at least one dedicated fluid pathway extending from the at least one inlet and including a plurality of injector ports within each level of the plurality of levels.
C23C 16/455 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for introducing gases into the reaction chamber or for modifying gas flows in the reaction chamber
C23C 16/458 - Chemical coating by decomposition of gaseous compounds, without leaving reaction products of surface material in the coating, i.e. chemical vapour deposition [CVD] processes characterised by the method of coating characterised by the method used for supporting substrates in the reaction chamber
B01J 4/00 - Feed devicesFeed or outlet control devices
B01J 19/24 - Stationary reactors without moving elements inside
C23C 16/52 - Controlling or regulating the coating process
C23C 16/54 - Apparatus specially adapted for continuous coating
H01L 21/67 - Apparatus specially adapted for handling semiconductor or electric solid state devices during manufacture or treatment thereofApparatus specially adapted for handling wafers during manufacture or treatment of semiconductor or electric solid state devices or components
A seal ring (20) comprising: a split ring substrate (200) having: an inner diameter surface (35); an outer diameter surface (210); and Co as a largest by-weight constituent element and at least 18.0 weight percent Cr; and a coating (202, 204) having at least a first layer (202) atop the outer diameter surface, wherein the outer diameter surface has texturing characterized by: a pattern (248) of depth of at least 0.010 millimeter.
In a method for using a gas turbine engine (720, 720A, 720B), the gas turbine engine has: a compressor section (840, 842); a combustor section (844) including a plurality of fuel nozzles (860); and a turbine section (846, 848) having one or more stages of blades (400). The method includes spraying a solution or suspension (23, 440) into the combustor section via the fuel nozzles or additional nozzles (26, 26A, 26B) of the gas turbine engine, if any. The solution or suspension has a binder selected from gadolinium and gadolinium compounds.
C04B 35/00 - Shaped ceramic products characterised by their compositionCeramic compositionsProcessing powders of inorganic compounds preparatory to the manufacturing of ceramic products
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
A defect depth estimation system includes a training system and an imaging system that performs defect depth estimation from a monocular 2D image without using a depth sensor. The training system repeatedly receives a first type of image having a defect, and a second type of image that captures the target object having the defect and provides ground truth data indicating an actual depth of the defect. The training system transforms the first domain and the second domain into a target third domain that reduces a domain gap and trains a machine learning model to learn the actual depth of the defect using the target third domain. The imaging system receives a 2D test image in the first forma and uses the trained machine learning model to determine an estimation of the actual depth of the actual defect and to output estimated the estimation of the actual depth.
A high-entropy alloy includes a single-phase, face centered cubic structure composition containing between 43.0 and 49.9 at% nickel, between 16.0 and 26.0 at% chromium, between 6.5 and 16.5 at% iron, between 1.5 and 4.5 at% molybdenum, between 2.0 and 7.5 at% aluminum and between 6.5 and 11.0 at% cobalt. Such compositions are good replacements for more expensive nickel-based alloys and have good strength and corrosion resistance properties.
Embodiments of the present disclosure generally relate to aircraft engines and, more particularly, to detecting defects in aircraft engines using visual neuromorphic sensors. In some embodiments, an event associated with a portion of an aircraft engine may be identified based on a change on a visual data characteristic from a visual neuromorphic sensor. In response to identifying the event associated with the portion of the aircraft engine, synchronous data from a synchronous data collection sensor coupled to the aircraft engine may be retrieved for a predetermined period of time, and a defect associated with the aircraft engine detected based on the identified event and the synchronous data. Other embodiments may be disclosed or claimed.
A plating method includes: providing a nickel-containing plating solution; immersing a metallic substrate in the plating solution; and applying a voltage between the substrate and an anode to apply a plating. The providing comprises blending chromium powder with a precursor of the plating solution so that the plating solution is a Cr-containing plating solution. The as-applied plating forms a layer containing chromium particles from the powder.
A test system (20) has: a base (30); first and second support posts (40A, 40B) extending upward from the base; and a crosshead (44) receiving the first and second support posts. The crosshead is movable along a vertical range of motion relative to the first and second support posts and lockable to the first and second support posts within that range of motion. An actuator (70) provides a vertical force between the base and the locked crosshead. The vertical force is converted to a horizontal force on a specimen (26).
An apparatus with a communication system includes a method of operating the communication system. The communication system includes first device at a first location, a radio frequency transceiver at the first device, a waveguide extending between the first device to a second device at a second location, and a processor. The processor is configured to transmit a first radio frequency signal through the waveguide toward the second location, receive a second radio frequency signal in response to the first radio frequency signal, determine a presence of a fault in the waveguide from the second radio frequency signal, and transmit a third radio frequency signal via the radio frequency transceiver outside of the waveguide when the presence of the fault is determined.
A wall assembly (60) for use in a combustor (56) of a gas turbine engine, the wall assembly (60) including: a support shell (68, 70); a liner panel (72, 74); and an annular grommet (115) extending from the liner panel (72, 74) the annular grommet (115) defining a dilution passage (116) and the annular grommet (115) extends through an opening (117) in the support shell (68, 70) when the support shell (68, 70) and the liner panel (72, 74) are secured to each other, the annular grommet (115) having a top portion (119) that defines a portion of a periphery of the opening (117); and a backstop (121) extending from the top portion (119) of the annular grommet (115), the backstop (121) defining another portion of the periphery of the dilution passage (116) and the backstop (121) extending through and above the opening (117) in the support shell (68, 70) when the liner panel (72, 74) is secured to the support shell (68, 70).
An apparatus (50) for repairing a defective area in a polyimide composite (54) component includes a flexible film (56) enclosure for covering the defective area (52) of the polyimide composite component; a seal (62) around a perimeter of the film; a resin injection assembly (60) for injecting resin between the flexible film enclosure and the defective area of the component; and a vacuum source (58) for drawing vacuum between the flexible film enclosure and the component. A method is also disclosed.
B29C 73/02 - Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass using liquid or paste-like material
A coated article (20) has: a substrate (22); a bond coat (26) deposited on the substrate; and a mixed stabilizer layer (30) positioned over the bond coat. The mixed stabilizer has matrix oxide(s) of one or more matrix tetravalent elements and stabilizer oxides of at least two stabilizer trivalent elements. The matrix elements are selected from a first group consisting of Zr, Hf, Ti, and Ce. The stabilizer elements are selected from a second group consisting of La, Ce, Pr, Nd, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Y, and Sc.
A turbine vane assembly for a gas turbine engine is disclosed herein. The turbine vane assembly includes a turbine vane including a leading edge, a pressure edge, a suction edge, and a trailing edge, a core defined by the turbine vane, an outer platform end wall connected to the turbine vane, the outer platform end wall defining an interior space, the interior space being in fluid communication with the core, and a plurality of cooling holes formed in the turbine vane, the plurality of cooling holes being in fluid communication with the core.
A method of additive manufacturing of a component is provided and includes building up the component to have a first uppermost layer and a foundation to have a second uppermost layer below the first uppermost layer, evacuating powder from around the component and the foundation to expose the second uppermost layer, disposing, on the second uppermost layer, a forged flange having an upper surface coplanar with the first uppermost layer, backfilling powder about the component and the forged flange and completing a building up of the component by building up on the forged flange.
B33Y 80/00 - Products made by additive manufacturing
B22F 7/08 - 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 with one or more parts not made from powder
An aircraft propulsion system includes a core engine that includes a core flow path where a core airflow is compressed in a compressor section, communicated to a combustor section, mixed with fuel and ignited to generate a gas flow that is expanded through a turbine section for powering a primary propulsor. The aircraft propulsion system further includes a tap that is at a location upstream of the combustor section where a bleed airflow is drawn, a heat exchanger where the bleed airflow is heated by the gas flow, a power turbine through which heated bleed airflow is expanded to generate a work output, and a secondary propulsor that is driven by the work output that is generated by the power turbine.
F02C 6/18 - Plural gas-turbine plantsCombinations of gas-turbine plants with other apparatusAdaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
B64D 27/02 - Aircraft characterised by the type or position of power plants
B64D 27/12 - Aircraft characterised by the type or position of power plants of gas-turbine type within, or attached to, wings
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
F02K 3/02 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
patents
