TURBINE DRIVE SYSTEM WITH LOCK-UP CLUTCH AND METHOD

• US 20090288421A1
• Filed: 05/21/2008
• Published: 11/26/2009
• Est. Priority Date: 05/21/2008
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Zeiner, Peter Kenneth, Libera, Tony, Langston, Todd
• Granted Patent: US 8,146,370 B2
• Time in Patent Office: Days
• US Class Current: 60/792
• CPC Class Codes: F02C 3/10 with another turbine driving an output shaft but not driving the compressor
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• 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: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A pneumatically driven turbine drive system is coupled to a gas turbine engine that includes low and high pressure compressors, low and high pressure turbines, a lock-up clutch, and at least one engine accessory driven by the high pressure compressor. The pneumatically driven turbine drive system selectively bleeds air discharged from the high pressure compressor and supplies it to an air turbine that is coupled to the at least one engine accessory. Thus, the system selectively reduces the power extracted from the high pressure compressor and is capable of supplying power back to the engine core. This, coupled with the bleed air that is diverted from the high pressure turbine and the low pressure turbine, allows the high pressure spool and the low pressure spool to run at lower speeds when high engine thrust is not needed or desired, but when the at least one engine accessory is still needed.

Claims

1. A gas turbine engine including a turbine drive system, comprising:

an engine case;

a low pressure compressor, a high pressure compressor, a high pressure turbine and a low pressure turbine disposed in flow series within the engine case, the high pressure compressor and the high pressure turbine mounted on a high pressure spool and the low pressure compressor and the low pressure turbine mounted on a low pressure spool, each spool rotationally mounted within the engine case;

at least one engine accessory having an input shaft coupled to the high pressure spool to receive a drive force therefrom;

a bleed air conduit having an inlet port, an outlet port, and a flow passage therebetween, the bleed air conduit inlet port fluidly coupled to the high pressure compressor to receive a flow of bleed air from the high pressure compressor;

a flow control valve mounted on the bleed air conduit and selectively movable between at least a closed position, in which the bleed air conduit inlet port is fluidly isolated from the bleed air conduit outlet port, and an open position, in which the bleed air conduit inlet port is in fluid communication with the bleed air conduit outlet port;

an air turbine having a fluid inlet and a rotationally mounted air turbine output shaft, the air turbine fluid inlet in fluid communication with the bleed air conduit outlet port to receive bleed air therefrom when the flow control valve is in the open position, the air turbine output shaft coupled to the at least one engine accessory; and

a lock-up clutch coupled between the air turbine output shaft and the at least one engine accessory and movable between (i) an engage position, in which the air turbine output shaft is coupled to the at least one engine accessory in a first rotational direction and a second rotational direction opposite the first rotational direction, and (ii) a disengage position, in which the air turbine output shaft is not coupled to the at least one engine accessory.

2. They system of claim 1, wherein the at least one engine accessory is a generator and an engine pump.

3. The system of claim 2, further comprising:

one or more gears coupled between the high pressure spool and the at least one engine accessory.

4. The system of claim 3, further comprising:

one or more gears coupled between the air turbine output shaft and the at least one engine accessory.

5. The system of claim 2, further comprising:

one or more gears coupled between the air turbine output shaft and a core of the gas turbine engine.

6. The system of claim 5, further comprising:

a fan case at least partially surrounding the engine case and spaced apart therefrom to form an air bypass section;

a fan coupled to the low pressure spool and configured, upon rotation thereof, to supply a flow of fan bypass air through the air bypass flow passage;

7. The system of claim 2, wherein the at least one engine accessory is a generator configured, upon receipt of the drive force, to generate electrical power.

8. They system of claim 7, wherein the generator is coupled to a core of the gas turbine engine to provide the electrical power thereto.

9. The system of claim 2, further comprising:

a control circuit adapted to receive one or more sensor signals representative of one or more engine parameters and operable, in response thereto, to supply one or more valve position command signals; and

a valve actuator coupled to the flow control valve, the valve actuator coupled to receive the one or more valve position command signals and operable, in response thereto, to selectively move the flow control valve to a commanded position, to thereby control the flow of bleed air to the air turbine.

10. A gas turbine engine including a turbine drive system, comprising:

an engine case;

a low pressure compressor, a high pressure compressor, a high pressure turbine and a low pressure turbine disposed in flow series within the engine case, the high pressure turbine and the high pressure compressor mounted on a high pressure spool, and the low pressure compressor and the low pressure turbine mounted on a low pressure spool, each spool rotationally mounted within the engine case;

an engine accessory gearbox having an input shaft coupled to the high pressure spool to receive a drive force therefrom and operable, upon receipt of the drive force;

at least one engine accessory having an input shaft coupled to the engine accessory gearbox to receive the drive force therefrom and operable, upon receipt of the drive force;

a bleed air conduit having an inlet port, an outlet port, and a flow passage therebetween, the bleed air conduit inlet port fluidly coupled to the high pressure compressor to receive a flow of bleed air from the high pressure compressor;

a flow control valve mounted on the bleed air conduit and selectively movable between at least a closed position, in which the bleed air conduit inlet port is fluidly isolated from the bleed air conduit outlet port, and an open position, in which the bleed air conduit inlet port is in fluid communication with the bleed air conduit outlet port;

an air turbine having a fluid inlet and a rotationally mounted output shaft, the air turbine fluid inlet in fluid communication with the bleed air conduit outlet port to receive bleed air therefrom when the flow control valve is in the open position, the air turbine output shaft coupled to the at least one engine accessory; and

a lock-up clutch coupled between the air turbine output shaft and the engine accessory gearbox and movable between (i) an engage position, in which the air turbine output shaft is coupled to the engine accessory gearbox, and (ii) a disengage position, in which the air turbine output shaft is not coupled to the engine accessory gearbox.

11. The system of claim 10, wherein the at least one engine accessory is a generator or an engine pump.

12. The system of claim 11, further comprising:

one or more gears coupled between the high pressure spool and the at least one engine accessory.

13. The system of 2claim 11, further comprising:

one or more gears coupled between the air turbine output shaft and the at least one engine accessory.

14. The system of claim 11, further comprising:

fan case at least partially surrounding the engine case and spaced apart therefrom to form an air bypass section;

a fan coupled to the low pressure spool and configured, upon rotation thereof, to supply a flow of fan bypass air through the air bypass flow passage;

15. The system of claim 11, further comprising:

a control circuit adapted to receive one or more sensor signals representative of one or more engine parameters and operable, in response thereto, to supply one or more flow control valve position command signals; and

a valve actuator coupled to the flow control valve, the valve actuator coupled to receive the flow control valve position command signals and operable, in response thereto, to selectively move the flow control valve to a commanded position, to thereby control the flow of bleed air to the air turbine.

16. The system of claim 15, wherein:

the control circuit is further operable, in response to the sensor signals, to supply one or more lock-up clutch command signals.

17. The system of claim 16, wherein:

the lock-up clutch is coupled to the control circuit to receive the one or more lock-up clutch command signals and operable, in response thereto, to move between the engage and disengage positions, in which the air turbine output shaft is coupled to the at least one engine accessory, and (ii) a disengage position, in which the air turbine output shaft is not coupled to the at least one engine accessory.

18. In a gas turbine engine system including a low pressure compressor, a high pressure compressor, a high pressure turbine, a low pressure turbine, and at least one engine accessory coupled to the high pressure compressor to receive a drive force therefrom, a method of providing a pneumatically driven turbine drive system to the high pressure compressor, comprising the steps of:

determining an operational state of the gas turbine engine system; and

selectively supplying air discharged from the high pressure compressor to an air turbine that is coupled to the at least one engine accessory based at least in part on the determined operational state, whereby the air turbine rotates and supplies the drive force to the at least one engine accessory in addition to that provided by the high pressure compressor.

19. The method of claim 18, wherein:

the at least one engine accessory is a generator or an engine pump.

20. The method of claim 19, further comprising:

sensing one or more operational parameters of the gas turbine engine system;

determining the operational state of the gas turbine engine system based at least in part on the sensed operational parameters; and

selectively coupling and decoupling the air turbine to and from, respectively, the at least one engine accessory via a lock-up clutch.