Engine power extraction control system

• US 7,285,871 B2
• Filed: 07/15/2005
• Issued: 10/23/2007
• Est. Priority Date: 08/25/2004
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Derouineau, Jean-Luc
• Primary Examiner(s): Waks; Joseph
• Application Number:
  US11/182,550
• Publication Number:
  US 20060042252A1
• Time in Patent Office: 830 Days
• Field of Search: 290/52
• US Class Current: 290/52
• CPC Class Codes: F02C 9/26 Control of fuel supply F02C9/48 takes precedence; fuel valves F02C7/232
• CPC Class Codes: F05D 2220/76 an electrical generator
• CPC Class Codes: F05D 2270/05 to affect the output of the engine

Abstract

An engine power extraction control system controls the main propulsion engines and the electrical machines that are coupled thereto to supply an appropriate amount of aircraft thrust and electrical energy to the aircraft. The engines and electrical machines are also controlled so that the propulsion thrust that is generated is split between the various turbines in the main propulsion engines to maintain an adequate surge margin and to minimize residual thrust generation.

Claims

1. An engine power extraction control system for an aircraft, comprising:

a gas turbine engine including at least a high pressure turbine and a low pressure turbine, each turbine adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy;

a first generator coupled to receive at least a portion of the rotational energy generated by the high pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a second generator coupled to receive at least a portion of the rotational energy generated by the low pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a first generator control unit electrically coupled to the first generator, the first generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the first generator, whereby rotational energy extraction from the high pressure turbine, by the first generator, is controlled;

a second generator control unit electrically coupled to the second generator, the second generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the second generator, whereby rotational energy extraction from the low pressure turbine, by the second generator, is controlled; and

an engine power extraction control circuit adapted to receive aircraft operational data representative of aircraft thrust and electrical load requirements and operable, upon receipt thereof, to supply the generator commands to the first and second generator control units.

2. The system of claim 1, wherein:

the first generator is a starter-generator that is configured to selectively operate in either (i) a motor mode, in which electrical energy is converted to rotational energy and supplied to the high pressure turbine or (ii) a generator mode, in which the rotational energy supplied thereto from the high pressure turbine is converted to electrical energy; and

the first generator control unit is further operable to selectively configure the starter-generator to operate in either the motor mode or the generator mode.

3. The system of claim 1, wherein the gas turbine engine further includes an intermediate pressure turbine that is adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy, and wherein the system further comprises:

a third generator coupled to receive at least a portion of the rotational energy generated by the intermediate pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a third generator control unit electrically coupled to the third generator, the third generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the third generator, whereby rotational energy extraction from the intermediate pressure turbine, by the third generator, is controlled,

wherein the engine power extraction control circuit is further operable to supply the generator commands to the third generator control unit.

4. The system of claim 1, further comprising:

a second gas turbine engine including at least a high pressure turbine and a low pressure turbine, each turbine adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy;

a third generator coupled to receive at least a portion of the rotational energy generated by the second gas turbine engine high pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a fourth generator coupled to receive at least a portion of the rotational energy generated by the second gas turbine engine low pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a third generator control unit electrically coupled to the third generator, the third generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the third generator;

a fourth generator control unit electrically coupled to the fourth generator, the fourth generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the fourth generator; and

a second engine power extraction control circuit adapted to receive the aircraft operational data and operable, upon receipt thereof, to supply the generator commands to the third and fourth generator control units.

5. The system of claim 4, wherein:

the first and third generators are each starter-generators that are configured to selectively operate in either (i) a motor mode, whereby electrical energy is converted to rotational energy and supplied to the high pressure turbine or (ii) a generator mode, whereby the rotational energy supplied thereto from the high pressure turbine is converted to electrical energy; and

the first and third generator control units are further operable to selectively configure the first and third starter-generators, respectively, to operate in either the motor mode or the generator mode.

6. The system of claim 4, wherein the first and second gas turbine engines each further include an intermediate pressure turbine that is adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy, and wherein the system further comprises:

a fifth generator coupled to receive at least a portion of the rotational energy generated by the first gas turbine engine intermediate pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a sixth generator coupled to receive at least a portion of the rotational energy generated by the second gas turbine engine intermediate pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a fifth generator control unit electrically coupled to the fifth generator, the fifth generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the fifth generator, whereby rotational energy extraction from the first gas turbine engine intermediate pressure turbine, by the fifth generator, is controlled;

a sixth generator control unit electrically coupled to the sixth generator, the sixth generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the sixth generator, whereby rotational energy extraction from the second gas turbine engine intermediate pressure turbine, by the sixth generator, is controlled,

wherein the engine power extraction control circuit is further operable to supply the generator commands to the fifth and sixth generator control units.

7. The system of claim 1, wherein the engine power extraction control circuit is further operable to supply auxiliary power unit (APU) starter-generator commands, and wherein the system further comprises:

an APU including;

an APU turbine adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy;

an APU starter-generator coupled to the turbine and configured to selectively operate in either (i) a motor mode, in which electrical energy is converted to rotational energy and supplied to the turbine or (ii) a generator mode, in which the rotational energy generated by the turbine is converted to electrical energy; and

a starter-generator control unit electrically coupled to the APU starter-generator, the APU starter generator coupled to receive the APU starter-generator commands and operable, in response thereto, to (i) selectively configure the APU starter-generator to operate in either the motor mode or the generator mode and (ii) when configuring the APU starter-generator to operate in the generator mode, control the electrical energy generated thereby.

8. The system of claim 7, wherein the engine power extraction control circuit is further operable to supply APU turbine commands, and wherein the system further comprises:

an APU controller electrically coupled to the APU turbine, the APU controller coupled to receive the APU turbine commands and operable, upon receipt thereof, to control the rotational energy generated by the APU turbine.

9. The system of claim 1, wherein the aircraft operational data include engine thrust setting, high pressure turbine rotational speed, low pressure turbine rotational speed, aircraft altitude, aircraft speed, aircraft electrical system configuration, and aircraft electrical system load.

10. An engine power extraction control system for an aircraft, comprising:

a left-side gas turbine engine including at least a high pressure turbine and a low pressure turbine, each turbine adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy;

a right-side gas turbine engine including at least a high pressure turbine and a low pressure turbine, each turbine adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy;

a first left-side generator coupled to receive at least a portion of the rotational energy generated by the left-side gas turbine engine high pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a second left-side generator coupled to receive at least a portion of the rotational energy generated by the left-side gas turbine engine low pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a first right-side generator coupled to receive at least a portion of the rotational energy generated by the right-side gas turbine engine high pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a second right-side generator coupled to receive at least a portion of the rotational energy generated by the right-side gas turbine engine low pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a first left-side generator control unit electrically coupled to the first left-side generator, the first left-side generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the first left-side generator, whereby rotational energy extraction from the left-side gas turbine engine high pressure turbine, by the first left-side generator, is controlled;

a second left-side generator control unit electrically coupled to the second left-side generator, the second left-side generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the second left-side generator, whereby rotational energy extraction from the left-side gas turbine engine low pressure turbine, by the second left-side generator, is controlled;

a first right-side generator control unit electrically coupled to the first right-side generator, the first right-side generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the first right-side generator, whereby rotational energy extraction from the right-side gas turbine engine high pressure turbine, by the first right-side generator, is controlled;

a second right-side generator control unit electrically coupled to the second right-side generator, the second right-side generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the second right-side generator, whereby rotational energy extraction from the right-side gas turbine engine low pressure turbine, by the second right-side generator, is controlled; and

an engine power extraction control circuit adapted to receive aircraft operational data representative of aircraft thrust and electrical load requirements and operable, upon receipt thereof, to supply the generator commands to the left-side first and second generator control units and to the right-side first and second generator control units.

11. The system of claim 10, wherein the left-side and right-side gas turbine engines each further include an intermediate pressure turbine that is adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy, and wherein the system further comprises:

a third left-side generator coupled to receive at least a portion of the rotational energy generated by the left-side gas turbine engine intermediate pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a third right-side generator coupled to receive at least a portion of the rotational energy generated by the right-side gas turbine engine intermediate pressure turbine and operable, upon receipt thereof, to generate electrical energy;

a third left-side generator control unit electrically coupled to the third left-side generator, the third left-side generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the third left-side generator, whereby rotational energy extraction from the left-side gas turbine engine intermediate pressure turbine, by the third left-side generator, is controlled;

a third right-side generator control unit electrically coupled to the third right-side generator, the third right-side generator control unit coupled to receive generator commands and operable, upon receipt thereof, to control the electrical energy generated by the third right-side generator, whereby rotational energy extraction from the right-side gas turbine engine intermediate pressure turbine, by the third right-side generator, is controlled,

wherein the engine power extraction control circuit is further operable to supply the generator commands to the third left-side and third right-side generator control units.

12. The system of claim 10, wherein the engine power extraction control circuit is further operable to supply auxiliary power unit (APU) starter-generator commands, and wherein the system further comprises:

an APU including;

an APU turbine adapted to receive a flow of combusted gas and operable, upon receipt thereof, to generate rotational energy;

an APU starter-generator coupled to the turbine and configured to selectively operate in either (i) a motor mode, in which electrical energy is converted to rotational energy and supplied to the turbine or (ii) a generator mode, in which the rotational energy generated by the turbine is converted to electrical energy; and

a starter-generator control unit electrically coupled to the APU starter-generator, the APU starter generator coupled to receive the APU starter-generator commands and operable, in response thereto, to (i) selectively configure the APU starter-generator to operate in either the motor mode or the generator mode and (ii) when configuring the APU starter-generator to operate in the generator mode, control the electrical energy generated thereby.

13. The system of claim 11, wherein the engine power extraction control circuit is further operable to supply APU turbine commands, and wherein the system further comprises:

an APU controller electrically coupled to the APU turbine, the APU controller coupled to receive the APU turbine commands and operable, upon receipt thereof, to control the rotational energy generated by the APU turbine.

14. The system of claim 10, wherein:

the first left-side generator is a starter-generator that is configured to selectively operate in either (i) a motor mode, in which electrical energy is converted to rotational energy and supplied to the left-side gas turbine engine high pressure turbine or (ii) a generator mode, in which the rotational energy supplied thereto from the left-side gas turbine high pressure turbine is converted to electrical energy;

the first right-side generator is a starter-generator that is configured to selectively operate in either (i) a motor mode, in which electrical energy is converted to rotational energy and supplied to the right-side gas turbine engine high pressure turbine or (ii) a generator mode, in which the rotational energy supplied thereto from the right-side gas turbine high pressure turbine is converted to electrical energy;

the first left-side generator control unit is further operable to selectively configure the first left-side generator to operate in either the motor mode or the generator mode; and

the first right-side generator control unit is further operable to selectively configure the first right-side generator to operate in either the motor mode or the generator mode.

15. The system of claim 10, wherein the aircraft operational data include engine thrust setting, high pressure turbine rotational speed, low pressure turbine rotational speed, aircraft altitude, aircraft speed, aircraft electrical system configuration, and aircraft electrical system load.

16. In an aircraft having a gas turbine engine that includes at least a high pressure turbine and a low pressure turbine each operable to generate rotational energy, a method of controlling rotational energy extracted from each turbine, comprising the steps of:

converting an amount of the rotational energy generated by the high pressure turbine into electrical energy;

converting an amount of the rotational energy generated by the low pressure turbine into electrical energy;

determining a plurality of aircraft operational parameters; and

based on the determined aircraft operational parameters;

(i) controlling the amount of rotational energy generated the high pressure turbine that is converted into electrical energy, to thereby control the rotational energy extracted from the high pressure turbine, and

(ii) controlling the amount of rotational energy generated the low pressure turbine that is converted into electrical energy, to thereby control the rotational energy extracted from the low pressure turbine.

17. The method of claim 16, further comprising:

controlling the amount of rotational energy generated by the high pressure turbine and the low pressure turbine, based at least in part on the determined aircraft operational parameters.

18. The method of claim 16, wherein the gas turbine engine further includes an intermediate pressure turbine that is operable to generate rotational energy, and wherein the method further comprises:

converting an amount of the rotational energy generated by the high pressure turbine into electrical energy; and

based on the determined aircraft operational parameters, controlling the amount of rotational energy generated the intermediate pressure turbine that is converted into electrical energy, to thereby control the rotational energy extracted from the intermediate pressure turbine.

19. The method of claim 16, wherein the aircraft operational parameters include engine thrust setting, high pressure turbine rotational speed, low pressure turbine rotational speed, aircraft altitude, aircraft speed, aircraft electrical system configuration, and aircraft electrical system load.