Abstract: A mounting system for mounting an air-cooled device to a mount, the device having a mounting flange and a cooling air outlet radially inward of an outer periphery of the device, the mounting flange adapted to cooperate with the mount, where the mounting system has a cooling air exhaust collection shroud adapted to surround the device and at least a portion of the mount, the shroud having a discharge outlet.

Abstract: A method and apparatus for cooling a fluid in a bypass gas turbine engine involves directing the fluid to the bypass duct of the engine to allow for heat exchange from the fluid to bypass air passing through the bypass air duct.

Abstract: A mounting system for mounting an air-cooled device to a mount, the device having a mounting flange and a cooling air outlet radially inward of an outer periphery of the device, the mounting flange adapted to cooperate with the mount, where the mounting system has a cooling air exhaust collection shroud adapted to surround the device and at least a portion of the mount, the shroud having a discharge outlet.

Abstract: The present invention includes a rotor assembly comprising a shaft, a first component coaxially attached to the shaft for performing a first function in the rotor assembly and acting as a first counterbalance weight, and a second component coaxially attached to the shaft for performing a second function in the rotor assembly and acting as a second counterbalance weight, whereby the first and second counterbalance weights combine to balance the rotor assembly. The present invention also includes a method of balancing a rotor assembly having a shaft and a residual imbalance, the method comprising the steps of coaxially attaching a first component performing a first function and having a first counterbalance weight integral therewith onto the shaft, and coaxially attaching a second component performing a second function and having a second counterbalance weight integral therewith onto the shaft, so that the first and second components counter the residual imbalance.

Abstract: The present invention includes a rotor assembly comprising a shaft, a first component coaxially attached to the shaft for performing a first function in the rotor assembly and acting as a first counterbalance weight, and a second component coaxially attached to the shaft for performing a second function in the rotor assembly and acting as a second counterbalance weight, whereby the first and second counterbalance weights combine to balance the rotor assembly. The present invention also includes a method of balancing a rotor assembly having a shaft and a residual imbalance, the method comprising the steps of coaxially attaching a first component performing a first function and having a first counterbalance weight integral therewith onto the shaft, and coaxially attaching a second component performing a second function and having a second counterbalance weight integral therewith onto the shaft, so that the first and second components counter the residual imbalance.

Abstract: A bypass duct sealing grommet, for sealing between an opening in a gas turbine engine bypass duct wall and the external surface of a projection extending through the opening, where the grommet has an annular body with a central aperture having an interior periphery adapted to sealingly engage the external surface of the projection. A first flange and second flanges define an external slot about an exterior periphery of the body adapted to receive and seal the bypass duct wall between the flanges.

Abstract: In a gas turbine engine, a fuel inlet tube comprising a body, a channel defined in the body and in fluid communication with a manifold, and a side inlet in fluid communication with the channel, such that fuel entering the side inlet is delivered to the manifold through the channel with a pressure generally directed along a radial axis of the body. Also, a fuel inlet tube comprising a heat shield surrounding at least part of a body, a chamber defined between the heat shield and the body and in fluid communication with fuel leak sources, a drain channel defined in the body in fluid communication with the chamber, and a drain hole defined in the body in fluid communication with the drain channel, such that a leak produces fuel received in the chamber and safely directed through the channel and the hole to allow detection of the leak.

Abstract: The present invention includes a gas turbine engine exhaust centerbody comprising a forward portion having at least one flap at a downstream end thereof to induce a local low pressure zone in the exhaust gas flow without significantly impeding it, a tailcone partially inserted into the forward portion so that at least part of the at least one flap overlaps a portion of the tailcone, a centerbody cavity containing gas at a pressure higher than the local low pressure, and at least one opening between the forward portion and the tailcone adjacent to and upstream of one of the local low pressure zones and providing fluid communication between the cavity and the exhaust gas flow. A ventilation flow out of the centerbody cavity through each opening is induced by a positive difference between the pressure of the gas in the centerbody cavity and the low pressure of the adjacent zone.

Abstract: A multi-position pressurized fluid actuator is mounted for movement in a casing. The actuator includes at least one selectively openable opening at a location corresponding to an intermediate position through which pressurized fluid can be selectively bled from the actuator to permit the actuator to remain in the intermediate position.

Abstract: A mounting system, for installing a starter-generator to an accessory housing, where the starter-generator has a mounting end with a connecting flange and a cooling air outlet radially inward of a peripheral starter-generator housing edge, and where the accessory housing has a matching connecting flange radially inward of a peripheral accessory housing edge. The mounting system includes a cooling air outlet collection shroud enveloping the peripheral starter-generator housing edge and the peripheral accessory housing edge, the shroud having a discharge outlet. A V-band clamp releasably secures the connecting flanges together and is enveloped within the shroud in a compact mounting system that collects and discharges the exhausted cooling air.

Abstract: A pneumatically operated compressor bleed valve communicating between a compressor housing and a bypass duct of a gas turbine engine. The valve has an annular piston slidably mounted within an annular chamber concentric the longitudinal engine axis. An annular valve plug on the piston and an annular valve seat on the compressor housing defining a valve seal interface. A control air pressure conduit communicates between a portion of the annular chamber bounded by the piston and a source of control air pressure. Guide bearings mounted to the periphery of the piston and the housing have a helical guide surface concentric the engine axis.

Abstract: A mounting system, for installing a starter-generator to an accessory housing, where the starter-generator has a mounting end with a connecting flange and a cooling air outlet radially inward of a peripheral starter-generator housing edge, and where the accessory housing has a matching connecting flange radially inward of a peripheral accessory housing edge. The mounting system includes a cooling air outlet collection shroud enveloping the peripheral starter-generator housing edge and the peripheral accessory housing edge, the shroud having a discharge outlet. A V-band clamp releasably secures the connecting flanges together and is enveloped within the shroud in a compact mounting system that collects and discharges the exhausted cooling air.

Abstract: A bypass duct sealing grommet, for sealing between an opening in a gas turbine engine bypass duct wall and the external surface of a projection extending through the opening. Conventionally, the intersection between the projection and the sheet metal bypass duct requires accurate fitting and welding, but cannot then accommodate thermal expansion and contraction. The grommet enables an oversized opening for relative thermal motion and simplifies manufacture. The grommet has an annular body with a central aperture adapted to seal against the external surface of the projection and two flanges defining an external slot about an exterior periphery of the body to contain and seal the bypass duct wall between the flanges.

Abstract: A pneumatically operated compressor bleed valve communicating between a compressor housing and a bypass duct of a gas turbine engine. The valve has an annular piston slidably mounted within an annular chamber concentric the longitudinal engine axis. An annular valve plug on the piston and an annular valve seat on the compressor housing defining a valve seal interface. A control air pressure conduit communicates between a portion of the annular chamber bounded by the piston and a source of control air pressure. Guide bearings mounted to the periphery of the piston and the housing have a helical guide surface concentric the engine axis.

Abstract: A method and apparatus carrying the method for sealing a radial gap between coaxial inner and outer rotating shafts of a gas turbine engine includes using a radial seal as a main seal to seal the gap for a normal engine operation condition, and using an axial seal as a back-up seal for a double seal of the gap. The radial seal provides a seal which meets relatively restrictive leakage requirements for the normal engine operation condition and the axial seal provides a back-up seal which meets less restrictive leakage requirements but is much more tolerant of radial displacement and vibration between the coaxial inner and outer rotating shafts. Thus, an engine operable condition is ensured under abnormal conditions, such as bird strikes, in which the coaxial relationship between the inner and outer rotating shafts are affected by unbalancing forces caused by the bird strike, thereby causing a failure of the radial seal.

Abstract: A method and apparatus carrying the method for sealing a radial gap between coaxial inner and outer rotating shafts of a gas turbine engine includes using a radial seal as a main seal to seal the gap for a normal engine operation condition, and using an axial seal as a back-up seal for a double seal of the gap. The radial seal provides a seal which meets relatively restrictive leakage requirements for the normal engine operation condition and the axial seal provides a back-up seal which meets less restrictive leakage requirements but is much more tolerant of radial displacement and vibration between the coaxial inner and outer rotating shafts. Thus, an engine operable condition is ensured under abnormal conditions, such as bird strikes, in which the coaxial relationship between the inner and outer rotating shafts are affected by unbalancing forces caused by the bird strike, thereby causing a failure of the radial seal.

Abstract: A bleed valve for a gas turbine engine having a housing of two segments and which form a gas flow path through the compressor, in which a first segment is movable from the second segment thereby creating an opening between the two segments. The moveable segment having one or more arms with rollers attached thereto where the stationary segment has paths on which the rollers travel, as the moveable segment is caused to move away from the stationary segment thereby opening the valve.

Abstract: A small gas turbine engine including a power turbine shaft and a gearbox input shaft co-axially aligned one with the other and mounted in three bearings. The power turbine shaft is provided with a male conical surface while the gearbox input shaft is hollow and includes a female conical surface adapted to mate with the male conical surface of the power turbine shaft. The power turbine shaft also includes an axial projection being threaded and inserted within the hollow portion of the gearbox input shaft. A nut having a shoulder is threaded onto the threaded projection of the power turbine shaft and engages a shoulder provided within the hollow gearbox input shaft such that torsion applied to the nut will force axial engagement of the conical surfaces. A complementary spline section may be provided, on the one hand, between the nut engaging shoulder and the female conical section on the gearbox input shaft. The complete coupling is within the diameter of the two co-axial shafts.