Bi-modal turbine assembly and starter / drive turbine system employing the same

• US 8,291,715 B2
• Filed: 06/11/2008
• Issued: 10/23/2012
• Est. Priority Date: 06/11/2008
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Libera, Tony, Zeiner, Peter
• Primary Examiner(s): Kim, Ted
• Application Number:
  US12/137,303
• Publication Number:
  US 20090314002A1
• Time in Patent Office: 1,595 Days
• Field of Search: 60/391.83, 608/02, 607/87, 607/88
• US Class Current: 60/788
• 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: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F05D 2260/85 Starting
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A bi-modal turbine assembly is provided for use in conjunction with a gas turbine engine. In one embodiment, the bi-modal turbine assembly includes a housing assembly having a flow passage therethrough, a turbine wheel rotatably mounted in the housing assembly and positioned so as to be driven by pressurized air flowing through the flow passage, an output shaft rotatably mounted in the housing assembly, and first and second gear trains disposed in the housing assembly. A switching device is also disposed in the housing assembly and configured to mechanically couple: (i) the first gear train between the turbine wheel and the output shaft in a first operational mode, and (ii) the second gear train between the turbine wheel and the output shaft in a second operational mode.

Claims

1. A bi-modal turbine assembly for use in conjunction with a gas turbine engine, the bi-modal turbine assembly comprising:

a housing assembly having a flow passage therethrough;

a turbine wheel rotatably mounted in the housing assembly and positioned so as to be driven by pressurized air flowing through the flow passage;

an output shaft rotatably mounted in the housing assembly;

a first gear train disposed in the housing assembly and having a first gear ratio selected such that the bi-modal turbine assembly produces peak output power between a first engine speed generally indicative of engine lightoff and a second engine speed generally indicative of flight idle;

a second gear train disposed in the housing assembly and having a second gear ratio less than the first gear ratio and selected such that the bi-modal turbine assembly produces peak output power between the second engine speed generally indicative of flight idle and a third engine speed generally indicative of engine cruise; and

a switching device disposed in the housing assembly and configured to mechanically couple;

(i) the first gear train between the turbine wheel and the output shaft in a first operational mode, and (ii) the second gear train between the turbine wheel and the output shaft in a second operational mode.

2. A bi-modal turbine assembly according to claim 1 wherein the switching device comprises:

a clutch mechanically coupled to the output shaft;

an actuator operatively coupled to the clutch and configured to cause the clutch to mechanically engage;

(i) the first gear train in the first operational mode, and (ii) the second gear train in the second operational mode.

3. A bi-modal turbine assembly for use in conjunction with a gas turbine engine, the bi-modal turbine assembly comprising:

a housing assembly having a flow passage therethrough;

a turbine wheel rotatably mounted in the housing assembly and positioned so as to be driven by pressurized air flowing through the flow passage;

an output shaft rotatably mounted in the housing assembly;

a first gear train disposed in the housing assembly and having a first gear ratio selected such that the bi-modal turbine assembly produces peak output power between approximately 10% and approximately 50% of the maximum speed of the gas turbine engine;

a second gear train disposed in the housing assembly and having a second gear ratio less than the first gear ratio and selected such that the bi-modal turbine assembly produces peak output power between approximately 60% and approximately 100% of the maximum speed of the gas turbine engine; and

a switching device disposed in the housing assembly and configured to mechanically couple;

(i) the first gear train between the turbine wheel and the output shaft in a first operational mode, and (ii) the second gear train between the turbine wheel and the output shaft in a second operational mode.

4. A bi-modal turbine assembly according to claim 3 wherein the second gear ratio is selected such that the bi-modal turbine assembly produces peak output power between approximately 70% and approximately 90% of the maximum speed of the gas turbine engine.

5. A starter/drive turbine (SDT) system for use in conjunction with a gas turbine engine deployed on an aircraft, the SDT system comprising:

a bi-modal turbine assembly, comprising;

a housing assembly having a flow passage therethrough;

a turbine wheel rotatably mounted in the housing assembly and positioned so as to be driven by pressurized air flowing through the flow passage;

an output shaft rotatably mounted in the housing assembly;

a first gear train disposed in the housing assembly;

a second gear train disposed in the housing assembly; and

a switching device disposed in the housing assembly and configured to selectively couple the first gear train and the second gear train between the turbine wheel and the output shaft;

a controller operatively coupled to the switching device and configured to cause the switching device to mechanically couple;

(i) the first gear train between the turbine wheel and the output shaft in a Start Mode, and (ii) the second gear train between the turbine wheel and the output shaft in an Energy Conservation Mode; and

a sensor configured to monitor a characteristic indicative of the speed of the gas turbine engine, the controller operatively coupled to the sensor and configured to transition from Start Mode to Energy Conservation Mode when the speed of the gas turbine engine exceeds a predetermined engine speed threshold between approximately 50% and approximately 100% of the maximum speed of the gas turbine engine.

6. An SDT system according to claim 5 further comprising a flow control valve fluidly coupled to the flow passage and operatively coupled to the controller.

7. An SDT system according to claim 5 further comprising a bleed air flow passage fluidly coupled between the gas turbine engine and the flow passage.

8. An SDT system according to claim 5 wherein the controller is configured to transition from Start Mode to Energy Conservation Mode after main engine start of the gas turbine engine.

9. An SDT system according to claim 5 wherein the controller is configured to operate in Energy Conservation Mode during flight idle.

10. An SDT system according to claim 5 wherein the first gear train has a first gear ratio selected such that the bi-modal turbine assembly produces peak output power between approximately 10% and approximately 50% of the maximum speed of the gas turbine engine.

11. An SDT system according to claim 10 wherein the second gear train has a second gear ratio selected such that the bi-modal turbine assembly produces peak output power between approximately 60% and approximately 100% of the maximum speed of the gas turbine engine.