Abstract: Provided is a gas turbine plant that enables active clearance control for ensuring tip clearance of first-stage turbine rotor blades required during start-up and for achieving the minimum tip clearance during load operation. In a gas turbine plant including a cooler in an air system used for cooling second-stage turbine stator blades, a first-stage segmented ring and a second-stage segmented ring that oppose tips of first-stage turbine rotor blades and second-stage turbine rotor blades are supported by the same blade ring member, and a cooling-air for the second-stage turbine stator blades forms a cooling air flow cooling the blade ring, to control thermal expansion of the blade ring and to control the clearance with respect to the tips.

Abstract: A latch assembly for securing a nacelle portion of a gas turbine engine includes first and second nacelle flow structures that define a portion of a bypass flowpath. A seal is engageable between the first and second nacelle flow structures. A latch is rotatable about a pivot between latched and unlatched positions. The latch maintains the seal in engagement with the first and second nacelle flow structures in the latched position. A method of opening a nacelle flow structure includes the steps of pivoting a latch from a latched position to an unlatched position, and unlatching a first nacelle flow structure relative to a second nacelle flow structure in response to the latch pivoting step.

Abstract: Apparatus for reducing air mass flow through the compressor in a single shaft gas turbine engine having an extended operating range including part load conditions, to provide low emissions combustion. The apparatus includes one or more nozzles positioned for injecting compressed air into the inlet region of the compressor. The nozzles are oriented to direct the compressed air tangentially to, and in the same angular direction as, the direction of rotation to create a swirl in the inlet air flow to the compressor inducer. The apparatus also includes conduits in flow communication between the compressor diffuser and the nozzles, one or more valves operatively connected to control the flow of compressed air from the diffuser to the nozzles, and a controller operatively connected to the valves to cause compressed air flow to the nozzles during operation at part load conditions.

Abstract: The present invention provides a variable pressure ratio gas turbine. In an embodiment, the engine is configured to selectively bypass all or a portion of a high pressure compressor and a high pressure turbine. In an embodiment, during bypass operation, all or a portion of the flow that would otherwise pass through the high pressure compressor and the high pressure turbine may be routed through a respective compressor bypass duct and turbine bypass duct.

Abstract: A turbocharger includes an annular bypass passage to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member. The turbine includes a nozzle having a vane assembly. In one embodiment the vane assembly has only fixed vanes. In another embodiment the vane assembly includes both fixed vanes and variable vanes, and the variable vanes are part of a rotor that rotates together with the rotary valve member.

Abstract: A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a divided volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines a pair of concentric annular bypass passages surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel as two separate bypass streams. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member.

Abstract: A linear actuator for a variable-geometry member of a turbocharger includes a piston/rod assembly that can axially translate and also pivot to a limited extent. A permanent magnet is mounted in a fixed position within the actuator. A non-magnetized flux carrier is mounted in the piston/rod assembly, and its movement alters the magnetic field of the magnet. A Halls effects sensor detects the magnetic field and the signals produced by the sensor are used for determining axial position of the piston/rod assembly.

Abstract: An inducer for a casing of a gas turbine system is disclosed. The inducer includes a plurality of orifices defined in the casing, the plurality of orifices disposed in an annular array about the casing, and a plurality of cartridges, each of the plurality of cartridges configured to mate with one of the plurality of orifices. Each of the plurality of cartridges includes an inlet and an outlet for flowing a cooling medium therethrough. The inducer further includes at least one flow modifier disposed in each of the plurality of cartridges for modifying the flow of the cooling medium through each of the plurality of cartridges. Each of the plurality of cartridges is independently removable from each of the plurality of orifices.

Abstract: A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines an annular bypass passage surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve includes a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member.

Abstract: A guide system for translating components of an aircraft engine nacelle includes a track assembly and a slider assembly. The track assembly includes a track guide member having a track channel. The slider assembly translatably engages the track assembly. The slider assembly includes a slider body configured to be received within the track channel. The slider assembly further includes a slider arm member pivotably coupled to the slider body with a hinge joint disposed within the track channel. The slider arm member extends from the body portion and outwardly of the track assembly. Associated apparatuses are also provided.

Abstract: A supersonic gas compressor with bleed gas collectors, and a method of starting the compressor. The compressor includes aerodynamic duct(s) situated for rotary movement in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. A convergent inlet is provided adjacent to a bleed gas collector, and during startup of the compressor, bypass gas is removed from the convergent inlet via the bleed gas collector, to enable supersonic shock stabilization. Once the oblique shocks are stabilized at a selected inlet relative Mach number and pressure ratio, the bleed of bypass gas from the convergent inlet via the bypass gas collectors is effectively eliminated.

Abstract: To solve the problems of compressor wheel blade flow separation causing surge type noises when a compressor return or recirculation valve is opened or closed, bypass airflow from a compressor recirculation valve is fed into an annular volume, defined between inner and outer walls or shaped as a radially expanded, axially flattened cylindrical space in the compressor inlet, so that the generally unidirectional radial flow from the compressor recirculation valve is re-directed and organized as it is turned from generally radial to generally axial, merging with the general inlet flow and presenting the compressor wheel with airflow of “circumferentially uniform” flow velocity.

Abstract: The present invention relates to a housing for a blade wheel of a turbo machine including a flow channel which is enclosed by a housing wall; a valve flap for selectively sealing or releasing a flow opening in the housing wall; and a shaft which is connected with the valve flap. The shaft is guided through an opening in the housing wall to the outside of the flow channel. The opening has an opening width which is larger than the largest diameter of the smallest projected area of the valve flap and of the part of the shaft protruding into the flow channel in the mounted state, and the opening is sealed in the mounted state by a cover through which the shaft extends.

Abstract: A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines an annular bypass passage surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member.

Abstract: A system (110) for controlling a pneumatic valve (112) of a turbine engine, such as a bleed valve, the system comprising a directional control valve (140) for controlling air under pressure connected between the valve (112) that is to be controlled, a controlling solenoid valve (118), and means (144) for taking off air at a pressure P1, the solenoid valve also including a first inlet (132) connected to a source of fluid at a pressure P2 that is independent of P1, the opening and closing of the pneumatic valve being controlled by a flow of the air at pressure P1 delivered by the directional control valve that is controlled by the fluid at pressure P2 delivered by the solenoid valve.

Abstract: A steam turbine and a start-up system for a steam turbine are disclosed comprising: a plurality of stages, a steam path through the plurality of stages, an inlet port for introducing steam to a first stage, an exhaust port at a last stage for allowing exhaust to exit the steam turbine, an admission port for allowing steam to enter the steam path at a location downstream from the inlet port, and a ventilator port for allowing steam to exit the steam path, the ventilator port located upstream of the admission port to create a reverse flow of steam towards the ventilator port from the admission port.

Abstract: A system for asymmetric flow extraction is described and claimed, the system comprising a flow path, a bleed slot in the flow path, a bleed cavity for receiving at least a portion of the fluid extracted from the flow path and a bleed passage in flow communication with the bleed slot and the bleed cavity wherein the bleed passage has at least one deflector having a shape such that the width of the bleed passage cross section varies in a direction normal to the direction of fluid flow in the bleed passage. In another embodiment, the deflector has an aerodynamic surface having a shape such that the flow passage between the aerodynamic surface and a surface located away from it has a cross sectional shape that is non-axisymmetric. In another embodiment, the bleed passage comprises an assembly of a plurality deflectors, arranged circumferentially.

Abstract: A gas turbine engine system includes a nacelle assembly, a core engine and a mixer disposed between the nacelle assembly and the core engine. The core engine includes a core passage and a core auxiliary duct passage. The core auxiliary duct passage includes an inlet for receiving a portion of a core airflow form the core engine and an outlet for discharging a portion of the core airflow received from the core engine.

Abstract: A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines an annular bypass passage surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member.

Abstract: A reconfigurable heat transfer system for a turbine inlet for a gas turbine engine is disclosed. The reconfigurable heat transfer system includes reconfigurable heat transfer components may be moved between a first position and a second position, wherein the second position allows a portion of or all of the air in the inlet to bypass the heat transfer components.

Abstract: A rotor wheel is provided and includes a body having first and second opposing faces and portions recessed from a plane of the first face to define therein an annular groove and a plurality of tributary grooves, the annular groove being receptive of fluid from an external source and formed to direct the fluid to flow along an annular flow path, and the plurality of tributary grooves being receptive of the fluid from the annular groove and respectively formed to direct the fluid to flow sequentially along radial and axial tributary flow paths while preventing inter-tributary groove fluid communication.

Abstract: A device is provided for pivoting at least one pivotable element in a gas turbine engine between a first and a second position in order to influence a gas flow in an annular gas duct in at least one of the positions. The device includes a moveable annular member which is arranged externally around the gas duct and is connected to the pivotable element in order to effect the pivoting of the pivotable element. The annular member is more specifically arranged to be displaced in a substantially axial direction and arranged to pivot the pivotable element when it is displaced axially.

Abstract: A gas turbine engine system is disclosed which includes a core passage and a bypass passage which can be configured as a fan bypass duct or a third stream bypass duct. The core passage and bypass passage are routed to flow through a nozzle before exiting overboard an aircraft. The nozzle includes moveable members capable of changing a configuration of the nozzle. In one form the moveable members are capable of changing throat areas for portions of the nozzle that receive working fluid from the core passage and the bypass passage. The bypass passage can include a branch. In one form the branch can include a heat exchanger. The bypass passage can also provide cooling to one or more portions of the nozzle, such as cooling to a deck of the nozzle.

Abstract: The present invention relates to a gas-turbine engine with at least one compressor and at least one bleed-air tapping device, which includes an annular duct in a radially outer wall of a flow duct, and with an annular closing element, which is arranged in the region of the annular duct and can be moved in a substantially axial direction from a closed position to an open position, with the closing element having an annular flow divider projection which in the open position projects in the flow duct.

Abstract: A waste gate arrangement for a turbine, particularly for an exhaust gas turbocharger, has a waste gate valve for bypassing exhaust gas past the turbine. A waste gate shaft has first and second bearing locations rotatably supporting the shaft. A lever arm is rotationally fixedly mounted on the waste gate shaft and configured for placing the shaft in rotation when a lever arm force is applied to the lever arm. A waste gate flap is fixed on the shaft and controls the amount of exhaust gas flowing through the valve, and disposed relative to the first and the second bearing locations such that a lever arm normal force resulting from the lever arm force when opening and/or closing the waste gate valve and an exhaust gas normal force acting on the waste gate flap have opposite force action directions at one or both bearing locations.

Abstract: A turbocharger for a use with a combustion engine is provided. The turbocharger may have a turbine housing with a first volute, a second volute, and a common outlet. The turbocharger may also have a turbine wheel disposed between the common outlet and the first and second volutes. The turbocharger may further have a first valve configured to selectively fluidly communicate the first volute with the second volute upstream of the turbine wheel, a second valve configured to selectively fluidly communicate the second volute with the common outlet to bypass the turbine wheel, and a common actuator configured to move the first and second valves.

Abstract: A gas turbine engine includes a fan, a bypass duct having a nozzle, through which fluid from the fan flows, and a variable area nozzle device located in the nozzle. The variable area nozzle device has an arcuate fairing having one end in slidable cooperation with the bypass duct. In a deployed position the area of the nozzle is reduced from that when stowed, thereby improving engine operability and efficiency.

Abstract: A gas-turbine compressor has a casing (1) in which a rotor hub (2) is rotatably borne, and a compressor duct (9) being disposed between the casing (1) and the rotor hub (2), in which at least one rotor (4), which is rotatable about a machine axis (5), and one stator (5) are arranged. Recesses (12) of a bleed-air tapping device (6) are provided in the casing (1), which—in at least one circumferential area (11)—are arranged circumferentially to each other recess (12) and include a circumferential leading edge (16) in the circumferential direction and a circumferential trailing edge (17), each of which includes an identical angle ?E with the surface (18) of the casing (1).

Abstract: The present invention relates to a two-spool gas turbine engine including an HP turbine stator ring and an exterior wall of the transition channel between the HP and LP stages, a first enclosure for controlling the stator ring, and a second enclosure for distributing air for blowing the exterior wall of the transition channel. The engine is characterized in that the two enclosures are placed in communication via an orifice controlled by a valve adapted to be open when the pressure P1 in the first enclosure is greater than the pressure P2 in the second enclosure, and closed when P1<P2.

Abstract: A turbocharger having a turbine with a wastegate, and a compressor including a compressor housing, a compressor wheel, and a wastegate actuator. The turbine wheel includes blades defining an inlet. The compressor housing has an inlet wall leading to the inlet, and a shroud wall surrounding the blades. The actuator includes a base that is integral with the inlet wall, and an electric motor that is attached to the base. The shroud wall forms a first port that is in direct fluid communication with the actuator chamber, and the inlet wall forms a second port that is in direct fluid communication with the actuator chamber. Air from the first port to passes through the actuator housing and out the second port. This airflow convectively cools the working components of the actuator, while the connection of the motor to the inlet wall conductively cools the motor.

Abstract: An actuator module for a gas turbine engine includes a multiple of actuators mounted within a common actuator housing.

Abstract: A method for providing a flow control system for an aircraft. A compressor is removed from an existing air cycle machine, along with compressor ducting that is connected to a primary stage outlet of the heat exchanger and a secondary stage inlet of the heat exchanger in the existing air cycle machine. A first connector duct is provided and connected to the primary stage outlet of the heat exchanger and the secondary stage inlet of the heat exchanger. The turbine is removed from the existing air cycle machine, and a second connector duct is provided and connected to the upstream turbine duct directly and the downstream turbine duct.

Abstract: An apparatus for controlling the temperature of a component, which is situated in use in a gas stream, provides a nozzle to create a jet of air at an angle to the gas stream, the jet being directed into the region of the stagnation point of the component so as to control the temperature of the component. The invention is particularly suited to preventing or reducing the formation of ice on vanes of gas turbine engines, but may also be applied to other components, and may equally be used in situations where a component is to be cooled rather than heated.

Abstract: A turbocharger includes a turbine wheel mounted within a turbine housing and connected to a compressor wheel by a shaft. The turbine housing defines an exhaust gas inlet connected to a divided volute that surrounds the turbine wheel, and an axial bore through which exhaust gas that has passed through the turbine wheel is discharged from the turbine housing. The turbine housing further defines a pair of concentric annular bypass passages surrounding the bore and arranged to allow exhaust gas to bypass the turbine wheel as two separate bypass streams. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member.

Abstract: A turbomachine, includes an annular flow duct, which downstream of at least one stage, is divided into an outer annular bypass duct and an inner annular core-flow duct via a concentrically arranged splitter, wherein the splitter is designed as an intermediate casing with at least one inner volume, through which fluid may be returned between core-flow stages.

Abstract: A method for assembling a rotary machine includes providing a first rotatable element. The method also includes coupling a second rotatable element to the first rotatable element. The first rotatable element and the second rotatable element at least partially define a cavity therein and at least one conduit extending substantially axially therebetween. Further, the method includes coupling a purge device including at least one radial channel defined therein and extending to the first rotatable element and to the second rotatable element such that the at least one radial channel is coupled in flow communication with the cavity and with the at least one axial conduit.

Abstract: A nacelle assembly for a turbine engine has a cowl. The cowl extends along an axis and has an exterior surface spaced from an interior surface. The interior surface forms an air inlet for directing airflow to the turbine engine. A turbulator for creating turbulence is disposed on one of the interior surface and the exterior surface.

Abstract: A gas turbine engine comprising a rotor and a stator which define first, second and third cavities; the rotor and stator define a seal therebetween and which is located for sealing between the second and third cavities, the rotor comprises an aperture through which a gas flow passes from the first cavity to the second cavity characterized in that the seal comprises a deflector that extends axially over at least a portion of the aperture to deflect at least a part of the gas towards the rotor.

Abstract: A bleed valve for an air plenum includes a valve body which defines a valve seat. A poppet is movable relative to the valve seat between an open position and a closed position. A spring biases the poppet to the open position and toward the air plenum.

Abstract: A core case section for a gas turbine engine a multitude of discreet radial extending 2.5 bleed ducts defined in part by a rear structural wall.

Abstract: A method of manufacturing a wind turbine rotor blade is provided. Anticipated primary load paths within the rotor blade are predicted. Fibers of reinforcing material are dispensed onto a mold, having an orientation pattern of the fibers which is selected in dependence on the predicting step. Resin is also dispensed into the mold. A wind turbine rotor blade is provided. The blade comprises fibers of reinforcing material which are embedded in resin. The fibers are short, say in the range of 5 to 200 mm, and are orientated in dependence on an anticipated structural loading pattern of the rotor blade.

Abstract: A turbocharger turbine which has a wastegate slide sleeve (8), which is provided in a wastegate arrangement (5) and which closes off the wastegate duct, as a shut-off element. The wastegate arrangement (5) comprises a bypass duct (6) which runs in the turbine housing (2); a wastegate duct (7) which runs in the turbine housing (2) to the turbine housing outlet (4) and which is connected via the bypass duct (6) to the turbine housing inlet (3); and a shut-off element (8) which is arranged in the turbine housing (2). The shut-off element (8) is provided to open and close the wastegate duct (7) and can be moved by means of an actuating device (9) into an open position and closed position.

Abstract: The present invention relates to a multi-stage turbocharger arrangement (1), having a high-pressure turbocharger (20) which has a turbine housing (26A), a bearing housing (27A), a compressor housing (28A); and having a low-pressure turbocharger (21) which has a turbine housing (26B), a bearing housing (27B), a compressor housing (28B); wherein the turbine housings (26A, 26B) are combined to form at least one turbine housing unit (26), and/or wherein the bearing housings (27A, 27B) are combined to form at least one bearing housing unit (27), and/or wherein the compressor housings (28A, 28B) are combined to form at least one compressor housing unit (28).

Abstract: A supersonic compressor includes a fluid inlet, a fluid outlet, a fluid conduit extending therebetween, and at least one supersonic compressor rotor disposed within the fluid conduit and including a fluid flow channel that includes a throat portion. The supersonic compressor also includes a fluid control device coupled in fluid communication with at least one fluid source and an inlet of the fluid flow channel. The fluid control device channels a first fluid to the fluid flow channel inlet. The first fluid has a first plurality of fluid properties that facilitate attainment of supersonic flow of the first fluid in the throat portion during a first operational mode. The fluid control device further channels a second fluid to the fluid flow channel inlet. The second fluid has a second plurality of fluid properties that permit maintenance of supersonic flow of the second fluid in the throat portion.

Abstract: A supersonic gas compressor. The compressor includes aerodynamic duct(s) situated on a rotor journaled in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. The convergent inlet is adjacent to a bleed air collector, and during acceleration of the rotor, bypass gas is removed from the convergent inlet via a collector to enable supersonic shock stabilization. Once the oblique shocks are stabilized at a selected inlet relative Mach number and pressure ratio, the bleed of bypass gas from the convergent inlet via the bypass gas collectors is eliminated.

Abstract: A turbomachine compressor, including an air bleed device including a duct having a suction end opening out into an outer casing of the compressor level with a rotor wheel and a stator stage of the compressor is disclosed. A screen sheet of annular shape is mounted radially inside the casing facing a portion of the suction end of the duct so as to make the bleeding of air uniform over 360° around the axis of the compressor.

Abstract: A gas turbine engine includes a bleed structure which includes a forward wall and a rear structural wall to define a deposit space downstream of the bleed structure for a hail event of a predetermined duration.

Abstract: The invention relates to a turbine engine that includes a spool supporting at least one of a compressor and a turbine. A turbofan is coupled to the spool The spool is arranged in a core nacelle, and the turbofan is arranged upstream from the core nacelle. A fan nacelle surrounds the turbofan and the core nacelle and provides a bypass flow path. A structure extends radially between the core and fan nacelles to support the core nacelle relative to the fan nacelle. Surfaces are supported relative to the fixed structure and are moveable between closed and open positions to selectively obstruct bypass flow through the bypass flow path, thereby changing the effective area of the exit nozzle. A change in the effective area of the nozzle exit can be used to improve the efficiency and operation of the turbine engine.

Abstract: A gas turbine engine bleed air system includes one or more fuel-actuated bleed air supply valves and, in some cases, a pneumatically actuated overpressure valve. Each fuel-actuated bleed air supply valve is mounted on a bleed air supply conduit and is coupled to a source of pressurized aircraft fuel. Each fuel-actuated bleed air supply valve is responsive to the pressurized aircraft fuel to move to a plurality of valve positions and to regulate compressed air pressure in the bleed air supply conduit, downstream of the fuel-actuated bleed air supply valve. The pneumatically actuated overpressure valve is mounted on the bleed air conduit downstream of each of the fuel-actuated bleed air valves and pneumatically regulates or shuts off pressure independent of fuel pressure or electrical signals.

Abstract: A turbocharger with an exhaust gas-driven turbine includes a variable nozzle formed by a stator supporting fixed vanes and defining bypass openings, and a rotor supporting movable vanes and defining bypass channels. Each fixed vane overlaps with a movable vane by a varying extent dependent on rotational position of the rotor. In a fully open position of the rotor, the movable vanes have a maximum extent of overlap with the fixed vanes, and the bypass channels align with the bypass openings so that some of the exhaust gas flows through the aligned bypass openings and channels, bypassing the turbine wheel.