Operation of aircraft engines during transient conditions

• US 10,196,923 B2
• Filed: 08/28/2014
• Issued: 02/05/2019
• Est. Priority Date: 08/28/2014
• Status: Active Grant

• Current Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Pratt & Whitney Canada Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Thomassin, Jean
• Primary Examiner(s): Edgar, Richard A
• Assistant Examiner(s): White, Alexander
• Application Number:
  US14/471,130
• Publication Number:
  US 20160061053A1
• Time in Patent Office: 1,622 Days
• CPC Class Codes: F01D 17/06 responsive to speed
• CPC Class Codes: F02C 3/10 with another turbine driving an output shaft but not driving the compressor
• CPC Class Codes: F02C 6/14 Gas-turbine plants having means for storing energy, e.g. for meeting peak loads
• CPC Class Codes: F02C 7/32 Arrangement, mounting, or driving, of auxiliaries
• CPC Class Codes: F05D 2220/50 for auxiliary power units (APU's)

Abstract

Aircraft engines and methods for operating such aircraft engines during transient conditions are described. An exemplary method comprises identifying a transient condition of the aircraft engine and at least partially absorbing the transient condition using an electrical system of the aircraft. When the transient condition requires acceleration of the engine, absorbing the transient condition may comprise transferring power from the electrical system to the high-pressure spool of the engine. When the transient condition requires deceleration of the engine, absorbing the transient condition may comprise transferring power from the high-pressure spool to the electrical system.

Claims

1. A method for operating an aircraft engine during a transient condition of the aircraft engine, the aircraft engine including a turbine having at least a high-pressure turbine spool and a low-pressure turbine spool, the method comprising:

identifying a transient condition of the aircraft engine during operation of the aircraft engine requiring one of an increase or decrease in rotational speed of the high-pressure spool, the identification of the transient condition comprising detecting an actuation of a throttle lever associated with the aircraft engine;

conditioned upon the transient condition requiring an increase in rotational speed of the high-pressure spool, providing power from a source of power separate from the aircraft engine to the high-pressure spool to at least partially accelerate the high-pressure spool during the transient condition, the source of power being part of an electrical system of an aircraft; and

conditioned upon the transient condition requiring a decrease in rotational speed of the high-pressure spool, drawing power from the high-pressure spool to the electrical system to at least partially decelerate the high-pressure spool during the transient condition.

2. The method as defined in claim 1, wherein the step of providing power comprises transferring power from an auxiliary power unit to the high-pressure spool.

3. The method as defined in claim 1, wherein the step of providing power comprises:

converting mechanical power from a source of mechanical power separate from the aircraft engine into electrical power; and

using the electrical power to drive an electric motor coupled to the high-pressure spool.

4. The method as defined in claim 3, wherein the source of mechanical power comprises an auxiliary power unit.

5. The method as defined in claim 1, wherein drawing power from the aircraft engine comprises connecting an electrical load to an electric machine coupled to the high-pressure spool and operating the electric machine as a generator.

6. The method as defined in claim 1, wherein the source of power comprises a battery.

7. The method as defined in claim 1, comprising disconnecting an electrical load from an electric generator coupled to the high-pressure spool conditioned upon the transient condition comprising a required increase in rotational speed of the high-pressure spool.

8. The method as defined in claim 7, wherein the source of power comprises an auxiliary power unit.

9. An aircraft engine comprising:

a high-pressure spool;

a low-pressure spool configured for rotation separate from the high-pressure spool; and

a controller configured to, during operation of the aircraft engine, identify a transient condition of the aircraft engine based on an actuation of a throttle lever associated with the aircraft engine and command;

conditioned upon the transient condition requiring an increase in rotational speed of the high-pressure spool, injection of power into the aircraft engine by transferring power from a source of power separate from the aircraft engine to the high-pressure spool to at least assist in achieving the required increase in rotational speed of the high-pressure spool during the transient condition, the source of power being part of an electrical system of an aircraft; and

conditioned upon the transient condition requiring a decrease in rotational speed of the high-pressure spool, drawing of power from the aircraft engine by transferring power from the high-pressure spool to the electrical system to at least assist in achieving the required decrease in rotational speed of the high-pressure spool during the transient condition.

10. The aircraft engine as defined in claim 9, wherein the source of power comprises at least one of a battery and an auxiliary power unit.

11. The aircraft engine as defined in claim 9, wherein the controller is configured to control an amount of power injected into or drawn from the aircraft engine based on the transient condition.

12. A method for operating an aircraft engine during a transient condition of the aircraft engine, the aircraft engine comprising a gas turbine having a high-pressure spool and a low-pressure spool, the method comprising:

identifying a transient condition of the aircraft engine during operation of the aircraft engine, the identification of the transient condition comprising detecting an actuation of a throttle lever associated with the aircraft engine; and

at least partially absorbing the transient condition of the aircraft engine using an electrical system of an aircraft by injecting power into the aircraft engine by transferring power from a source of power separate from the aircraft engine and part of the electrical system to the high-pressure spool.

13. The method as defined in claim 12, wherein injecting power into the aircraft engine comprises transferring power from an auxiliary power unit to the high-pressure spool.

14. The method as defined in claim 12, wherein injecting power into the aircraft engine comprises:

converting mechanical power from a source of mechanical power separate from the aircraft engine into electrical power; and

using the electrical power to drive an electric motor coupled to the high-pressure spool of the aircraft engine.

15. The method as defined in claim 12, wherein drawing power from the aircraft engine comprises connecting an electrical load to an electric machine coupled to the high-pressure spool and operating the electric machine as a generator.

16. The method as defined in claim 12, comprising controlling an amount of power injected into or drawn from the aircraft engine based on the transient condition.

17. The method as defined in claim 12, wherein the transient condition comprises a condition other than starting the aircraft engine.