Auxiliary power unit with intercooler

Patent metadata

Field	Value
Publication number	US-11584539-B2
Application number	US-202016891187-A
Country	US
Kind code	B2
Filing date	Jun 3, 2020
Priority date	Jun 25, 2015
Publication date	Feb 21, 2023
Grant date	Feb 21, 2023

Abstract

An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

First claim

The invention claimed is:

1. A method of providing compressed air and electrical power to an aircraft, the method comprising:
flowing compressed air from an outlet of a compressor of an auxiliary power unit through an intercooler;
flowing compressed air from the intercooler simultaneously to an inlet of an engine core of the auxiliary power unit and through a bleed conduit in communication with a pneumatic system of the aircraft, the engine core including an internal combustion engine having at least one combustion chamber of varying volume;
driving at least one generator providing electrical power to the aircraft with a turbine section of the auxiliary power unit including compounding power from the turbine section with power from the engine core, the turbine section including a first stage turbine and a second stage turbine, and
flowing excess compressed air from the outlet of the compressor to an inlet of the second stage turbine through a flow path separate from the engine core, the flow path bypassing the first stage turbine, the first stage turbine having at least one rotor engaged on a turbine shaft in driving engagement with a shaft of the engine core, the second stage turbine having at least one rotor engaged on the turbine shaft.

2. The method as defined in claim 1 , further comprising driving the compressor with the engine core of the auxiliary power unit.

3. The method as defined in claim 1 , wherein driving the at least one generator includes driving the at least one generator through a gearbox.

4. The method as defined in claim 1 , further comprising mechanically coupling the engine core and the turbine section of the auxiliary power unit.

5. The method as defined in claim 1 , further comprising pressure regulating compressed air in the bleed conduit upstream of the pneumatic system.

6. The method as defined in claim 1 , further comprising extracting energy from engine core exhaust gas impulse via turbine work produced by the auxiliary power unit.

7. The method as defined in claim 1 , further comprising discharging engine core exhaust gas through the turbine section of the auxiliary power unit in serial flow communication therewith.

8. The method as defined in claim 1 , further comprising bypassing compressed air upstream of the intercooler to the engine core.

9. The method as defined in claim 1 , further comprising circulating coolant between the intercooler and a liquid cooling system of the auxiliary power unit through a cooling conduit.

10. The method as defined in claim 1 , further comprising diverting compressed air from the intercooler and recovering energy from waste heat of the auxiliary power unit with said compressed air.

11. A method of operating an auxiliary power unit for providing compressed air to a pneumatic system of an aircraft, comprising:
compressing air via a compressor of the auxiliary power unit;
cooling the compressed air via an intercooler;
feeding a first portion of the cooled compressed air to an engine core of the auxiliary power unit and a second portion of the cooled compressed air to the pneumatic system of the aircraft through a bleed conduit in communication therewith, the engine core including an internal combustion engine having at least one combustion chamber of varying volume;
driving at least one generator providing electrical power to the aircraft with a turbine section of the auxiliary power unit including compounding power from the turbine section with power from the engine core, the turbine section including a first stage turbine and a second stage turbine; and
flowing excess compressed air from the compressor to an inlet of the second stage turbine through a flow path separate from the engine core, the flow path bypassing the first stage turbine, the first stage turbine having at least one rotor engaged on a turbine shaft in driving engagement with a shaft of the engine core, the second stage turbine having at least one rotor engaged on the turbine shaft.

12. The method as defined in claim 11 , further comprising driving the compressor with the engine core of the auxiliary power unit.

13. The method as defined in claim 11 , further comprising pressure regulating the second portion of the cooled compressed air upstream of the pneumatic system in the bleed conduit.

14. The method as defined in claim 11 , further comprising bypassing part of the compressed air upstream of the intercooler to the engine core.

15. The method as defined in claim 11 , further comprising diverting a third portion of the cooled compressed air from the intercooler and recovering energy from waste heat of the auxiliary power unit therewith.

16. The method as defined in claim 11 , further comprising recovering energy from exhaust gas of the engine core through the turbine section in serial flow communication with the engine core.

17. The method as defined in claim 11 , further comprising circulating coolant between the intercooler and a liquid cooling system of the auxiliary power unit through a cooling conduit.

Assignees

• Pratt & Whiiney Canada Corp
• Pratt & Whitney Canada

Inventors

• Ullyott Richard
• Jones Anthony
• Julien Andre
• Thomassin Jean

Classifications

• Y02T10/12

  Improving ICE efficiencies · CPC title

• F01D17/20

  Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted (sensing elements alone F01D17/02; final actuators alone F01D17/10) · CPC title

• F02C7/16

  characterised by cooling medium · CPC title

• F02B33/40

  of non-positive-displacement type · CPC title

• F02B55/00

  Internal-combustion aspects of rotary pistons; Outer members for co-operation with rotary pistons · CPC title