A power takeoff and gearbox system of a multi-spool gas turbine engine includes a high rotor towershaft operably connected to and driven by a first spool of the gas turbine engine, a first gearbox operably connected to the high rotor towershaft, a low rotor towershaft operably connected to and driven by a second spool of the gas turbine engine, and a second gearbox operably connected to the low rotor towershaft. The high rotor towershaft is located at a first case of the gas turbine engine and the low rotor towershaft is located at a second case of the gas turbine engine axially forward of the first case.

A rotary valve system includes a first body having a first plurality of fluid channels. The first fluid channels have a common first inlet to receive a fluid and a first outlet. The system includes a second body coupled to the first body. The second body has a second plurality of fluid channels. The second fluid channels have a second inlet and a second outlet. The system includes a plate assembly having a plate coupled between the first body and the second body. The plate is movable between at least a first, open position in which the first outlet of at least one of the first fluid channels is in fluid communication with the second inlet of at least one of the second fluid channels and a second, closed position in which the second inlet of each of the second fluid channels is substantially completely obstructed by the plate.

An aircraft system includes a turbine engine having a compressor, a combustor having an inlet and an outlet, and a turbine having an inlet portion and an outlet portion. An auxiliary power unit (APU) is operatively connected to the turbine engine. The APU includes a compressor portion, a generator, and a turbine portion. The compressor portion is operatively connected to the turbine portion through the generator. A source of cryogenic fluid is operatively connected to the turbine engine and the APU. A heat exchange member includes an inlet section operatively connected to the source of cryogenic fluid, a first outlet section operatively connected to the turbine engine and a second outlet section operatively connected to the compressor portion.

A mixer is mounted in an aircraft. A rear end part of a cylindrical portion of the mixer is divided by a guide vane into a plurality of divided tubular portions. In the plurality of divided tubular portions, a notch nozzle is formed on an outer wall of the cylindrical portion. A plurality of guide holes are formed to extend from the outer wall of the cylindrical portion to a rear end surface of the guide vane.

An air turbine starter that includes a housing. The housing can circumscribe a turbine coupled that is coupled to a gear train in a gear box via a drive shaft. The gear train can couple to an output shaft via at least a carrier. The air turbine starter can include at least a first bearing assembly and a second bearing assembly to rotatably support the drive shaft and the output shaft.

A gas turbine engine with an accessory gearbox. The accessory gearbox has a gear shaft rotatable about a gear shaft axis. The gear shaft has a first end drivingly engaged to a first accessory and a second end drivingly engaged to a second accessory. The gearbox has a spline made of a polymer material and rotatably coupled to one of the first and second ends of the gear shaft, and to a corresponding one of a first and second accessory shafts of the first and second accessories. The spline is rotatable about the gear shaft axis.

A frame for a heat engine, the frame including an inner wall extended from an inlet end to an outlet end, the inner wall forming at least in part a core flowpath, the inner wall comprising a plenum formed between an outer portion of the inner wall and an inner portion of the inner wall, wherein a cavity is formed inward of the inner portion of the inner wall, and wherein the inner wall includes a first plenum opening providing fluid communication between the cavity and the plenum, and wherein the inner wall comprises a second plenum opening providing fluid communication between the plenum and the core flowpath.

A turbine engine includes integrated electric machines in the compressor section and the turbine section to supplement power produced from fuel with electric power. The example compressor section includes a compressor electric motor that is coupled to a compressor generator. The example turbine section includes a turbine electric motor that is coupled to the geared architecture to supplement power driving the fan section. A turbine generator provides electric power to the turbine electric motor.

A standpipe assembly configured to connect to a starter that includes a housing is described herein. The standpipe assembly includes: a standpipe having first and second openings at opposite ends of a hollow passageway, wherein the standpipe, upon being connected to the starter, is oriented within the housing so that the standpipe drains oil through the standpipe when oil in the housing reaches an overfill level, and is oriented in parallel to internal oil flow in the starter to inhibit interference with the internal oil flow during operation of the starter; and an attachment portion, wherein the attachment portion is structured to attach the standpipe assembly to the housing of the starter and prevent movement of the standpipe assembly with respect to the housing of the starter.

A system and method for diagnosing load compressor health state for an auxiliary power unit that includes a power compressor, a combustor, a power turbine, and a load compressor is provided. The auxiliary power unit is operated and bleed air is discharged from the load compressor at a bleed air pressure. Using a pressure sensor, the bleed air pressure discharged from the load compressor is sensed and supplied to a processor. In the processor, power compressor health state is diagnosed based solely on the sensed bleed air pressure.