Abstract: A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor is at a lower temperature and pressure than that encountered from the high pressure compressor. The turbo compressor increases the pressure of airflow and provides that airflow into the main bleed air passage to be communicated to systems utilizing the bleed air.

Abstract: A process for manufacturing a turbine engine component includes the steps of: providing a powder containing gamma titanium aluminide; and forming a turbine engine component from said powder using a direct metal laser sintering technique.

Abstract: An assembly is provided for mounting a turbofan engine to a pylon. The turbofan engine includes a fan section and an engine core. The mounting assembly includes a fan case, a first mount and a second mount. The fan case is configured to house the fan section of the turbofan engine. The first mount is connected to the fan case, and configured to mount the fan case to the pylon. The second mount is connected to the fan case, and configured to mount the fan case to the pylon.

Abstract: A gas turbine engine comprises a core engine, a fan, a bypass duct and a clutch. The fan is driven by the core engine. The bypass duct is configured to receive airflow from the fan. The clutch links the core engine and the fan. The core comprises a reverse-flow, two-spool gas generator in one embodiment. In another embodiment, the fan is driven by a free turbine aerodynamically powered by the core engine. In one embodiment, the clutch includes reverse gearing to reverse rotational output of the fan. In one embodiment, the clutch and reverse gearing are implemented in an epicyclic gear system.

Abstract: A system is provided for a turbine engine. The system includes a rotor assembly and a monitoring system. The rotor assembly includes a plurality of rotor blades connected to a shaft. The monitoring system includes a processing system. This processing system is adapted to receive blade data indicative of a rotational position of at least a first of the rotor blades. The processing system is also adapted to process shaft data with the blade data to provide torque data indicative of a torque to which at least a portion of the rotor assembly is being subjected, where the shaft data is indicative of a rotational position of the shaft.

Abstract: A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct.

Abstract: An air-oil cooler (AOC) for a gas turbine engine is disclosed. The AOC may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A gas turbine engine comprising an AOC is disclosed. The AOC of the engine may comprise an oil inlet, an oil outlet, and heat exchange elements between the oil inlet and the oil outlet. The AOC of the engine may be longitudinally positioned between a fan and a V-groove of the engine and radially spaced between a low pressure compressor and a low pressure compressor panel. A method of operating an AOC for use on a gas turbine engine is also disclosed.

Abstract: A system is provided for a turbine engine. The system includes a rotor assembly and a monitoring system. The rotor assembly includes a plurality of rotor blades connected to a shaft. The monitoring system includes a processing system. This processing system is adapted to receive blade data indicative of a rotational position of at least a first of the rotor blades. The processing system is also adapted to process shaft data with the blade data to provide torque data indicative of a torque to which at least a portion of the rotor assembly is being subjected, where the shaft data is indicative of a rotational position of the shaft.

Abstract: A system, which may be used as a propulsion system, includes a propulsor section having a fluid operated device or free turbine, a fluid source such as a gas generator for creating an exhaust gas, and a fluid passageway for delivering the exhaust gas to the fluid operated device or free turbine. The fluid operated device may be used to drive a rotary device such as a fan.

Abstract: A fan rotor includes a rotor body with at least one slot receiving a fan blade. The fan blade has an outer surface, at least at some areas, formed of a first material and an airfoil extending from a dovetail. The dovetail is received in the slot. A spacer is positioned radially inwardly of the dovetail biasing the fan blade against the slot. The spacer includes a grounding element, which is in contact with a portion of the dovetail formed of a second material that is more electrically conductive than the first material. The grounding element is in contact with a rotating element that rotates with the rotor. The rotating element is formed of a third material. The first material is less electrically conductive than the third material. The grounding and rotating elements form a ground path from the portion of the dovetail into the rotor.

Abstract: A process for manufacturing a turbine engine component includes the steps of: providing a powder containing gamma titanium aluminide; and forming a turbine engine component from said powder using a direct metal laser sintering technique.

Abstract: A gas turbine engine comprises a core engine, a fan, a bypass duct and a clutch. The fan is driven by the core engine. The bypass duct is configured to receive airflow from the fan. The clutch links the core engine and the fan. The core comprises a reverse-flow, two-spool gas generator in one embodiment. In another embodiment, the fan is driven by a free turbine aerodynamically powered by the core engine. In one embodiment, the clutch includes reverse gearing to reverse rotational output of the fan. In one embodiment, the clutch and reverse gearing are implemented in an epicyclic gear system.

Abstract: A thermal system for a gas turbine engine includes a bypass flow duct and a compressor flow duct which meets with the bypass flow duct at an intersection. A valve is located within the intersection and is movable between a first position and a second position. First position is operable to selectively communicate fan bypass flow from the bypass flow duct and block the compressor flow duct. The second position is operable to selectively block the bypass flow duct and communicate bleed flow through the compressor flow duct.

Abstract: A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis and a plurality of helical ribs adjacent to the fan blade containment section.

Abstract: An integrated thermal system for a gas turbine engine includes an Air-Oil Cooler and an Air-Air PreCooler within a housing, the Air-Air PreCooler downstream of the Air-Oil Cooler.

Abstract: A fan case of a gas turbine engine includes a fan blade containment section defined about an engine axis, a thrust reverser cascade section downstream of the blade containment section and a Fan Exit Guide Vane section downstream of the thrust reverser cascade section.

Abstract: A gas turbine engine includes a first and second pump driven by a spool. An Air-Oil Cooler downstream of the first pump. An air-air precooler is downstream of the second pump, the air-air precooler downstream of the Air-Oil Cooler.

Abstract: A gas turbine engine includes a constant speed transmission driven by a spool. The constant speed transmission drives a first pump and a second pump. In a further non-limiting example, the first pump is driven by a first drive shaft which is driven by the constant speed transmission and the second pump is driven by a second drive shaft which is driven by the first shaft through a gearbox to provide a constant speed ratio between the first shaft and the second shaft.

Abstract: An assembly is provided for mounting a turbofan engine to a pylon. The turbofan engine includes a fan section and an engine core. The mounting assembly includes a fan case, a first mount and a second mount. The fan case is configured to house the fan section of the turbofan engine. The first mount is connected to the fan case, and configured to mount the fan case to the pylon. The second mount is connected to the fan case, and configured to mount the fan case to the pylon.

Abstract: A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor is at a lower temperature and pressure than that encountered from the high pressure compressor. The turbo compressor increases the pressure of airflow and provides that airflow into the main bleed air passage to be communicated to systems utilizing the bleed air.