Aircraft auxiliary power unit

Patent metadata

Field	Value
Publication number	US-12017790-B2
Application number	US-202017061079-A
Country	US
Kind code	B2
Filing date	Oct 1, 2020
Priority date	Oct 23, 2019
Publication date	Jun 25, 2024
Grant date	Jun 25, 2024

Abstract

An auxiliary power unit ( 10 ) for an aircraft ( 1 ) comprises a gas turbine engine comprising an engine core ( 12 ). The engine core comprises a core compressor ( 14 ) and core turbine ( 18 ) coupled by a core shaft ( 24 ). The auxiliary power unit further comprises a load spool comprising a load compressor ( 30 ), a load turbine ( 20 ) and a permanent magnet electric machine ( 28 ), each being coupled by a load shaft ( 26 ). The load shaft ( 26 ) and core shaft ( 24 ) are configured to rotate independently of one another.

First claim

The invention claimed is:

1. An auxiliary power unit for an aircraft comprising;
a gas turbine engine comprising an engine core comprising a core compressor and core turbine coupled by a core shaft;
a load spool comprising a load compressor, a load turbine and a permanent magnet electric machine, each being coupled by a load shaft; and
circuitry, wherein:
the load shaft and core shaft are configured to rotate independently of one another, and
the electric machine includes a power electronics unit coupled to the electric machine such that the circuitry is configured to cause the gas turbine engine to operate:
(i) with the gas turbine engine running and with compressed air from the engine core not being prevented from entering the load turbine, and
(ii) with the gas turbine engine not running, the electric machine being configured to operate as a motor configured to drive the load compressor to provide compressed air to the aircraft, and uncompressed air being prevented from entering the load turbine from the engine core by way of closure of a valve.

2. An auxiliary power unit according to claim 1 , wherein the permanent magnet electric machine is directly coupled to the load turbine by the load shaft, such that the load turbine and electric machine rotate at the same speed.

3. An auxiliary power unit according to claim 1 , wherein the power electronics unit comprises a first AC to DC converter configured to convert AC electrical power output from the electric machine to DC electrical power.

4. An auxiliary power unit according to claim 3 , wherein the first AC to DC converter is bi-directional, and is configured to convert DC electrical power to AC electrical output to the electric machine.

5. An auxiliary power unit according to claim 3 , wherein the power electronics unit comprises a DC to DC voltage converter configured to convert DC voltage output from the first AC to DC converter to a different voltage.

6. An auxiliary power unit according to claim 5 , wherein the voltage converter is configured to output DC power at 24 Volts.

7. An auxiliary power unit according to claim 3 , wherein the power electronics unit comprises a first DC to AC converter configured to convert DC electrical power output from the first AC to DC converter to AC electrical power.

8. An auxiliary power unit according to claim 7 , wherein the first DC to AC converter is configured to output AC electrical power at 115 Volts RMS, and is configured to output AC electrical power at 400 Hz.

9. An auxiliary power unit according to 7 , wherein the first DC to AC converter is bi-directional, and is configured to convert AC electrical power to DC electrical power.

10. An auxiliary power unit according to claim 1 , wherein the core compressor comprises an axial compressor section upstream of a centrifugal compressor, each coupled to the core shaft.

11. An auxiliary power unit according to claim 1 , wherein the load compressor comprises variable inlet guide vanes.

12. An auxiliary power unit according to claim 1 , wherein the gas turbine engine comprises an accessory drive coupled to the core shaft.

13. An auxiliary power unit according to claim 1 , wherein the gas turbine engine comprises a clutch configured to selectively couple the core shaft and load shaft.

14. An aircraft comprising a main propulsive gas turbine engine and an auxiliary power unit according to claim 1 .

15. An auxiliary power unit according to claim 1 , wherein the motor drives both the load compressor and the load turbine when the gas turbine is not running.

Assignees

• Rolls Royce Plc
• Rolls Royce Corp

Inventors

• Swain Daniel
• Stieger Rory D
• Taylor Mark D

Classifications

• H02J2105/32

  for aircrafts · CPC title

• B64F1/34

  for starting propulsion plant · CPC title

• B64D41/00 Primary

  Power installations for auxiliary purposes · CPC title

• H02J4/00 Primary

  Circuit arrangements for mains or distribution networks not specified as AC or DC; Circuit arrangements for mains or distribution networks combining AC and DC sections or sub-networks (arrangements using intermediate DC-AC-DC conversion H02J1/002; arrangements using high-voltage DC [HVDC] links H02J3/36) · CPC title

• F05D2220/50

  for auxiliary power units (APU's) · CPC title