Auxiliary power unit with intercooler

• US 10,710,738 B2
• Filed: 06/25/2015
• Issued: 07/14/2020
• Est. Priority Date: 06/25/2015
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Ullyott, Richard, Jones, Anthony, Julien, Andre, Thomassin, Jean
• Primary Examiner(s): Chau, Alain
• Application Number:
  US14/750,179
• Publication Number:
  US 20160376021A1
• Time in Patent Office: 1,846 Days
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• CPC Class Codes: B64D 2013/0611 combined with auxiliary power units (APU's)
• CPC Class Codes: B64D 2013/0618 with arrangements for reducing or managing bleed air, using another air source, e.g. ram air
• CPC Class Codes: B64D 2041/002 Mounting arrangements for auxiliary power units (APU's)
• CPC Class Codes: B64D 33/08 of power plant cooling systems cooling of internal-combustion engines per se F01P; cooling of gas-turbine plants or jet-propulsion plants per se F02C, F02K
• CPC Class Codes: B64D 41/00 Power installations for auxiliary purposes
• CPC Class Codes: F01C 1/22 of internal-axis type with equidirectional movement of co-operating members at the points of engagement, or with one of the co-operating members being stationary, the inner member having more teeth or tooth- equivalents than the outer member
• CPC Class Codes: F01C 11/008 and of complementary function, e.g. internal combustion engine with supercharger
• CPC Class Codes: F01C 21/008 Driving elements, brakes, couplings, transmissions specially adapted for rotary or oscillating-piston machines or engines brakes, couplings, transmissions per se F16, B60
• CPC Class Codes: F01C 21/06 Heating; Cooling of machines or engines in general F01P; Heat insulation heat insulation in general F16L
• CPC Class Codes: F01D 17/20 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 Class Codes: F01D 25/18 Lubricating arrangements of machines or engines in general F01M
• CPC Class Codes: F02B 33/40 of non-positive-displacement type
• CPC Class Codes: F02B 41/10 in exhaust turbines use of exhaust turbines for charging F02B37/00
• CPC Class Codes: F02B 55/00 Internal-combustion aspects of rotary pistons; Outer members for co-operation with rotary pistons
• CPC Class Codes: F02B 63/042 Rotating electric generators
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 7/06 Arrangements of bearings bearings F16C; Lubricating of turbo machines F01D25/18; of machines or engines in general F01M
• CPC Class Codes: F02C 7/16 characterised by cooling medium
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F02C 7/36 : Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F02C 9/18 : by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages F02C3/113 takes precedence
• CPC Class Codes: F05D 2220/50 : for auxiliary power units (APU's)
• CPC Class Codes: F05D 2220/76 : an electrical generator
• CPC Class Codes: F05D 2260/211 : by intercooling, e.g. during a compression cycle
• CPC Class Codes: Y02T 10/12 : Improving ICE efficiencies
• CPC Class Codes: Y02T 50/40 : Weight reduction
• CPC Class Codes: Y02T 50/50 : On board measures aiming to increase energy efficiency

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.

Claims

1. An auxiliary power unit for an aircraft, comprising:

a compressor;

an intercooler including at least one first conduit in heat exchange relationship with at least one second conduit, the at least one first conduit having an inlet in fluid communication with an outlet of the compressor, the at least one second conduit being configured for circulation of a coolant therethrough;

an engine core including at least one internal combustion engine having at least one combustion chamber of varying volume; and

wherein an outlet of the at least one first conduit of the intercooler is in fluid communication with an inlet of the engine core and with a bleed conduit having an end configured for connection with a pneumatic system of the aircraft, the bleed conduit in fluid communication with the outlet of the at least one first conduit of the intercooler at a location between the intercooler and the inlet of the engine core, the bleed conduit having a bleed air valve selectively opening and closing the fluid communication between the outlet of the at least one first conduit of the intercooler and the end of the bleed conduit configured for connection to the pneumatic system;

wherein the auxiliary power unit is configured to flow compressed air from the intercooler simultaneously to the inlet of the engine core and through the bleed conduit in communication with the pneumatic system of the aircraft.

2. The auxiliary power unit as defined in claim 1, further comprising a bypass conduit in fluid communication with the outlet of the compressor at a location upstream of the intercooler, the bypass conduit in fluid communication with the inlet of the engine core and the bleed conduit at a location downstream of the intercooler, and further comprising a bypass valve for regulating a flow through the bypass conduit.

3. The auxiliary power unit as defined in claim 1, wherein the intercooler is a first intercooler, the auxiliary power unit further comprising:

a second intercooler including at least one third conduit in heat exchange relationship with at least one fourth conduit configured for circulation of a coolant therethrough;

the at least one third conduit having an inlet in fluid communication with the outlet of the at least one first conduit of the first intercooler;

the inlet of the engine core being in fluid communication with the outlet of the at least one first conduit of the first intercooler through the at least one third conduit of the second intercooler; and

the bleed conduit being in fluid communication with the outlet of the at least one first conduit of the first intercooler upstream of the second intercooler.

4. The auxiliary power unit as defined in claim 3, further comprising:

a first bypass conduit in fluid communication between the outlet of the compressor and the bleed conduit, the first bypass conduit in parallel with the first intercooler;

a first bypass valve for regulating a flow through the first bypass conduit;

a second bypass conduit in fluid communication between the outlet of the compressor and the inlet of the engine core, the second bypass conduit in parallel with the second intercooler; and

a second bypass valve for regulating a flow through the second bypass conduit.

5. The auxiliary power unit as defined in claim 4, wherein the second bypass conduit is in fluid communication with the outlet of the compressor at a location upstream of the first intercooler.

6. The auxiliary power unit as defined in claim 4, wherein the second bypass conduit is in fluid communication with the outlet of the compressor through communication with a conduit extending between the outlet of the at least one conduit of the first intercooler and the inlet of the at least one third conduit of the second intercooler.

7. The auxiliary power unit as defined in claim 1, wherein the at least one internal combustion engine includes at least one rotary internal combustion engine each including a rotor sealingly and rotationally received within a respective internal cavity to provide a plurality of the combustion chambers in the form of rotating chambers of variable volume in the respective internal cavity, the rotor having three apex portions separating the rotating chambers and mounted for eccentric revolutions within the respective internal cavity, the respective internal cavity having an epitrochoid shape with two lobes.

8. The auxiliary power unit as defined in claim 1, further comprising a turbine section having an inlet in fluid communication with an outlet of the engine core, the turbine section having a turbine shaft drivingly engaged to a shaft of the engine core for compounding power with the engine core.

9. The auxiliary power unit as defined in claim 8, wherein the turbine section includes a first stage turbine having an inlet in fluid communication with the outlet of the engine core, and a second stage turbine having an inlet in fluid communication with an outlet of the first stage turbine, the second stage turbine having a higher reaction ratio than that of the first stage turbine.

10. The auxiliary power unit as defined in claim 1, further comprising variable inlet guide vanes, a variable diffuser or a combination thereof at an inlet of the compressor.

11. An auxiliary power unit for an aircraft, comprising:

a compressor;

an intercooler including at least one first conduit in heat exchange relationship with at least one second conduit, the at least one second conduit being configured for circulation of a coolant therethrough;

an engine core including at least one internal combustion engine in driving engagement with a common shaft and having at least one combustion chamber of varying volume, the engine core having an inlet in fluid communication with an outlet of the compressor through the at least one first conduit of the intercooler;

a generator in driving engagement with the common shaft to provide electrical power for the aircraft;

a bleed conduit having an end configured for connection to a pneumatic system of the aircraft, the bleed conduit being in fluid communication with the outlet of the compressor through the at least one first conduit of the intercooler, the fluid communication between the outlet of the compressor and the bleed conduit located upstream of the engine core and configured to communicate with the pneumatic system separately from an exhaust flow of the engine core; and

a bleed air valve downstream of the intercooler configured for selectively opening and closing the fluid communication between the outlet of the compressor and the end of the bleed conduit configured for connection to the pneumatic system of the aircraft.

12. The auxiliary power unit as defined in claim 11, further comprising a bypass conduit providing a fluid communication between the outlet of the compressor and the inlet of the engine core, the bypass conduit in parallel with the intercooler, the bypass conduit also providing a fluid communication between the outlet of the compressor and the bleed conduit in parallel with the intercooler, and a bypass valve regulating a flow of the compressed air through the bypass conduit.

13. The auxiliary power unit as defined in claim 11, wherein the intercooler is a first intercooler, the auxiliary power unit further comprising:

a second intercooler including at least one third conduit in heat exchange relationship with at least one fourth conduit configured for circulation of a coolant therethrough;

the at least one third conduit having an inlet in fluid communication with the outlet of the at least one first conduit of the first intercooler;

the inlet of the engine core being in fluid communication with the outlet of the compressor through the at least one first conduit of the first intercooler and through the at least one third conduit of the second intercooler; and

the bleed conduit being in fluid communication with the outlet of the compressor through a connection with a conduit extending between the at least one first conduit of the first intercooler and the at least one third conduit of the second intercooler.

14. The auxiliary power unit as defined in claim 13, further comprising:

a first bypass conduit providing a fluid communication between the outlet of the compressor and the bleed conduit, the first bypass conduit in parallel with the first intercooler;

a first bypass valve regulating a flow through the first bypass conduit;

a second bypass conduit providing a fluid communication between the outlet of the compressor and the inlet of the engine core, the second bypass conduit in parallel with the second intercooler; and

a second bypass valve regulating a flow through the second bypass conduit.

15. The auxiliary power unit as defined in claim 11, wherein the at least one internal combustion engine includes at least one rotary internal combustion engine each including a rotor sealingly and rotationally received within a respective internal cavity to provide a plurality of the combustion chambers in the form of rotating chambers of variable volume in the respective internal cavity, the rotor having three apex portions separating the rotating chambers and mounted for eccentric revolutions within the respective internal cavity, the respective internal cavity having an epitrochoid shape with two lobes.

16. The auxiliary power unit as defined in claim 11, further comprising a turbine section having an inlet in fluid communication with an outlet of the engine core, the turbine section having a turbine shaft drivingly engaged to a shaft of the engine core for compounding power with the engine core.

17. The auxiliary power unit as defined in claim 16, wherein the turbine section includes a first stage turbine having an inlet in fluid communication with the outlet of the engine core, and a second stage turbine having an inlet in fluid communication with an outlet of the first stage turbine, the second stage turbine having a higher reaction ratio than that of the first stage turbine.