Compact compound engine package

• US 7,654,087 B2
• Filed: 08/23/2005
• Issued: 02/02/2010
• Est. Priority Date: 02/24/2003
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Original Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Inventors: Ullyott, Richard
• Primary Examiner(s): Cuff; Michael
• Assistant Examiner(s): SUNG, GERALD LUTHER
• Application Number:
  US11/208,637
• Publication Number:
  US 20070240427A1
• Time in Patent Office: 1,624 Days
• Field of Search: 60/391.82, 60/390.5, 607/16, 607/23, 608/01, 605/97, 606/051, 605/98, 606/07, 60/393.4, 60/393.5, 606/24, 418/13, 418/219, 123/241, 123/243, 746/65.C
• US Class Current: 60/624
• CPC Class Codes: F01D 25/12 Cooling
• CPC Class Codes: F01D 25/26 Double casings; Measures against temperature strain in casings
• CPC Class Codes: F02C 5/06 the working fluid being generated in an internal-combustion gas generated of the positive-displacement type having essentially no mechanical power output internal-combustion engines with prolonged expansion using exhaust gas turbines F02B
• CPC Class Codes: F02C 7/12 Cooling of plants of component parts, see the relevant subclasses, e.g. F01D; cooling of engines in general F01P
• CPC Class Codes: F02C 7/18 the medium being gaseous, e.g. air F02C7/125 takes precedence
• CPC Class Codes: F05D 2250/314 the axes being inclined in relation to each other
• CPC Class Codes: F05D 2260/20 Heat transfer, e.g. cooling
• CPC Class Codes: Y02T 10/12 Improving ICE efficiencies
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 74/1906 Nonparallel

Abstract

A compound cycle engine (10) comprises a compressor (19) and a turbine section (16 & 20), and at least one cycle topping device (12) cooperating with the turbine section (16 & 20) to provide power. The cycle topping device (12) has an output shaft (26) extending at an angle to the turbine shaft (28). Angled gearing (34) is provided for connecting the gas turbine shaft (28) and the cycle topping device (12).

Claims

1. A compound cycle engine comprising a gas turbine engine including an engine casing housing a compressor and a turbine section mounted for rotation about a central axis, said turbine section having a turbine shaft coaxial to the central axis located between a front of the engine casing and a rear turbine exhaust plane, the engine casing having top, bottom and lateral side extending axially between the front of the engine casing and the exhaust plane, and at least one rotary cycle topping device providing an input to said turbine section and cooperating therewith to provide shaft horsepower, the at least one rotary cycle topping device being located on one of the lateral sides of the engine casing between the front face and are rear face of the engine casing, said at least one rotary cycle topping device having an output shaft located between the top and bottom side of the engine casing at an angle comprised between about 45 degrees to about 90 degrees to the turbine shaft, and wherein a bevel gearbox mounted to the engine casing mechanically links the turbine shaft and the output shaft of the at least one rotary cycle topping device together wherein said bevel gearbox includes first and second bevel gears respectively rigidly mounted to said rotary cycle topping device output shaft and said turbine shaft, and wherein a third bevel gear is mounted to said output shaft for meshing engagement with a fourth bevel gear associated to a load to be driven.

2. A compound cycle engine as defined in claim 1, wherein said output shaft extends at 90 degrees to said turbine shaft.

3. A compound cycle engine as defined in claim 1, wherein two rotary cycle topping devices are disposed at the front of the engine casing on opposed sides of the bevel gearbox and oriented at about 90 degrees with respect to the turbine shaft.

4. A compound cycle engine as defined in claim 3, wherein a frontal air intake is defined between said two rotary cycle topping devices, said frontal air intake being provided at the top side of the engine casing and including a cooling air inlet and an engine air inlet, the cooling air inlet being located at a higher elevation than the engine air inlet.

5. A compound cycle engine as defined in claim 1, wherein said turbine section includes a free turbine, and wherein said at least one rotary cycle topping device includes a rotary combustion engine fed with compressed air from said compressor section.

6. A compound cycle engine as defined in claim 5, wherein said rotary combustion engine is a sliding vane internal combustion engine.

7. A compound cycle engine as defined in claim 1, wherein said at least one rotary cycle topping device is fed with pressurized air from said compressor section, and wherein valve means is provided for selectively bypassing said at least one rotary cycle topping device.

8. A compound cycle engine as defined in claim 1, wherein said turbine shaft and said output shaft of the at least one rotary cycle topping device commonly drive a load selected from a group consisting of at least one of a propeller, a generator a helicopter rotor, a starter, an oil pump, a fuel pump, a cooling fan, and a load compressor.

9. A compound cycle engine as defined in claim 1, wherein the at least one rotary cycle topping device comprises a rotary combustion engine, and wherein a cooling airflow device is integrated to said output shaft.

10. A compound cycle engine as defined in claim 9, wherein said rotary combustion engine has a casing, said casing defining a plurality of passages through which a coolant is circulated to pick up excess heat from the rotary combustion engine, and wherein a cooling fan forces air through a heat exchanger to extract heat from the coolant as it flows through the heat exchanger.

11. A compound cycle engine as defined in claim 10, wherein said heat exchanger has a toroidal shape and surrounds the cooling fan inlet.

12. An aircraft engine comprising a gas turbine engine having a casing housing a compressor section and a turbine section mounted for rotation about a central axis located between a front of the casing and a rear turbine exhaust plane, the casing having top, bottom and lateral sides extending axially between the front of the casing and the exhaust plane, the compressor and turbine sections being turbocompounded with a pair of cycle topping devices disposed on lateral sides of the casing between the front of the casing and the exhaust plane thereof, the turbine section having a turbine shaft coaxial to said central axis and mechanically linked to respective output shafts of the rotary cycle topping devices through bevel gearing to provide a common output, the output shafts located between the top and bottom sides of the casing of the turbine engine at an angle tote turbine shaft comprised between about 45 degrees to about 90 degrees wherein said bevel gearing includes first and second bevel gears respectively rigidly mounted to said rotary cycle topping device output shafts and said turbine shaft, and wherein a third bevel gear is mounted to said output shaft for meshing engagement with a fourth bevel gear associated to a load to be driven.

13. An aircraft engine as defined in claim 12, wherein said rotary cycle topping devices are mounted on opposed sides of said turbine shaft.

14. An aircraft engine as defined in claim 12, wherein the output shafts are oriented at an angle of about 90 degrees to said turbine shaft.

15. An aircraft engine as defined in claim 12, wherein said turbine section includes a free turbine, and wherein each of said rotary cycle topping devices includes a rotary combustion engine turbocharged with pressurized air from said compressor section.

16. An aircraft engine as defined in claim 15, wherein each of said rotary combustion engines includes a sliding vane internal combustion engine.

17. An aircraft engine as defined in claim 12, wherein said rotary cycle topping devices are fed with pressurized air from said compressor section, and wherein valve means is provided for selectively bypassing said rotary cycle topping devices.

18. An aircraft engine as defined in claim 12, wherein said turbine shaft and said output shafts of the rotary cycle topping devices commonly drive a load selected from a group consisting of a propeller, a generator a helicopter rotor, a starter, an oil pump, a fuel pump, a cooling fan, and a load compressor.