DUAL-USE AIR TURBINE SYSTEM FOR A GAS TURBINE ENGINE

• US 20170327235A1
• Filed: 05/13/2016
• Published: 11/16/2017
• Est. Priority Date: 05/13/2016
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Feulner, Matthew R.
• Granted Patent: US 10,457,401 B2
• Time in Patent Office: Days
• CPC Class Codes: B64D 13/06 the air being conditioned pressurising B64D13/02
• CPC Class Codes: B64D 13/08 the air being heated or cooled
• CPC Class Codes: B64D 15/04 Hot gas application
• 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 2013/0648 with energy recovery means, e.g. using turbines
• CPC Class Codes: B64F 1/34 for starting propulsion plant
• CPC Class Codes: F02C 1/02 the working fluid being an unheated pressurised gas
• CPC Class Codes: F02C 3/04 having a turbine driving a compressor power transmission arrangements F02C7/36; control of working fluid flow F02C9/16
• CPC Class Codes: F02C 6/08 the gas being bled from the gas-turbine compressor
• CPC Class Codes: F02C 7/277 the starter being a separate turbine
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2250/90 Variable geometry
• CPC Class Codes: F05D 2260/4031 as in toothed gearing
• CPC Class Codes: F05D 2260/606 Bypassing the fluid
• CPC Class Codes: F05D 2260/85 Starting
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

A dual-use air turbine system for a gas turbine engine of an aircraft is provided. The dual-use air turbine system includes a variable area air turbine mechanically linked to a spool of the gas turbine engine through a multi-speed gear set. The dual-use air turbine system also includes a plurality of valves in pneumatic ducting operable to direct an engine start air flow through an inlet of the variable area air turbine and drive rotation of the spool during an engine start mode of operation. The valves are further operable to direct an engine bleed air flow from a compressor section of the gas turbine engine through the inlet of the variable area air turbine and drive rotation of the spool during an environmental control system active mode of operation.

Claims

1. A dual-use air turbine system for a gas turbine engine of an aircraft, the dual-use air turbine system comprising:

a variable area air turbine mechanically linked to a spool of the gas turbine engine through a multi-speed gear set; and

a plurality of valves in pneumatic ducting operable to direct an engine start air flow through an inlet of the variable area air turbine and drive rotation of the spool during an engine start mode of operation, wherein the valves are further operable to direct an engine bleed air flow from a compressor section of the gas turbine engine through the inlet of the variable area air turbine and drive rotation of the spool during an environmental control system active mode of operation.

2. The dual-use air turbine system as in claim 1, wherein the valves comprise a first check valve and a high pressure shutoff valve, and the engine bleed air flow is provided from a lower pressure tap of the compressor section by the first check valve or a higher pressure tap of the compressor section by the high pressure shut-off valve.

3. The dual-use air turbine system as in claim 2, wherein the first check valve is opened during a high power condition of the gas turbine engine and the high pressure shut-off valve is opened during an engine idle condition of the gas turbine engine.

4. The dual-use air turbine system as in claim 2, wherein the valves further comprise a main valve located upstream of the inlet of the variable area air turbine, a starter air valve located downstream of an outlet of the variable area air turbine, and a second check valve located between the outlet of the variable area air turbine and the main valve.

5. The dual-use air turbine system as in claim 4, wherein the main valve and the starter air valve are opened during the engine start mode of operation to establish a flow path from aircraft ducting through the main valve, the variable area air turbine, the starter air valve, and an exhaust port.

6. The dual-use air turbine system as in claim 4, wherein the starter air valve is opened during an environmental control system off mode of operation to establish a flow path for the engine bleed air flow through the variable area air turbine, the starter air valve, and an exhaust port.

7. The dual-use air turbine system as in claim 4, wherein the main valve is opened during the environmental control system active mode of operation at a minimum pressure engine idle condition to establish a flow path for the engine bleed air flow through the main valve to aircraft ducting.

8. The dual-use air turbine system as in claim 4, wherein the main valve is closed and the second check valve is opened during the environmental control system active mode of operation at an engine off idle condition and at a high power condition to establish a flow path for the engine bleed air flow through the variable area air turbine and the second check valve to aircraft ducting.

9. The dual-use air turbine system as in claim 4, wherein the main valve is opened and the second check valve is opened during the environmental control system active mode of operation with wing anti-ice on to establish a flow path for the engine bleed air flow to aircraft ducting through the variable area air turbine and the main valve.

10. The dual-use air turbine system as in claim 1, further comprising a clutch to selectively engage the variable area air turbine to drive rotation of the spool.

11. A method of using a dual-use air turbine system for a gas turbine engine of an aircraft, the method comprising:

controlling a plurality of valves in pneumatic ducting to direct an engine start air flow through an inlet of a variable area air turbine and drive rotation of a spool of the gas turbine engine during an engine start mode of operation; and

directing an engine bleed air flow from a compressor section of the gas turbine engine through the inlet of the variable area air turbine to drive rotation of the spool during an environmental control system active mode of operation, wherein the variable area air turbine is mechanically linked to the spool of the gas turbine engine through a multi-speed gear set.

12. The method as in claim 11, wherein the valves comprise a first check valve and a high pressure shutoff valve, and the engine bleed air flow is provided from a lower pressure tap of the compressor section by the first check valve or a higher pressure tap of the compressor section by the high pressure shut-off valve.

13. The method as in claim 12, wherein the first check valve is opened during a high power condition of the gas turbine engine and the high pressure shut-off valve is opened during an engine idle condition of the gas turbine engine.

14. The method as in claim 12, wherein the valves further comprise a main valve located upstream of the inlet of the variable area air turbine, a starter air valve located downstream of an outlet of the variable area air turbine, and a second check valve located between the outlet of the variable area air turbine and the main valve.

15. The method as in claim 14, wherein the main valve and the starter air valve are opened during the engine start mode of operation to establish a flow path from aircraft ducting through the main valve, the variable area air turbine, the starter air valve, and an exhaust port.

16. The method as in claim 14, wherein the starter air valve is opened during an environmental control system off mode of operation to establish a flow path for the engine bleed air flow through the variable area air turbine, the starter air valve, and an exhaust port.

17. The method as in claim 14, wherein the main valve is opened during the environmental control system active mode of operation at a minimum pressure engine idle condition to establish a flow path for the engine bleed air flow through the main valve to aircraft ducting.

18. The method as in claim 14, wherein the main valve is closed and the second check valve is opened during the environmental control system active mode of operation at an engine off idle condition and at a high power condition to establish a flow path for the engine bleed air flow through the variable area air turbine and the second check valve to aircraft ducting.

19. The method as in claim 14, wherein the main valve is opened and the second check valve is opened during the environmental control system active mode of operation with wing anti-ice on to establish a flow path for the engine bleed air flow to aircraft ducting through the variable area air turbine and the main valve.

20. The method as in claim 11, further comprising selectively engaging the variable area air turbine to drive rotation of the spool.