Reducing an acoustic signature of a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10731570-B2
Application number	US-201715609875-A
Country	US
Kind code	B2
Filing date	May 31, 2017
Priority date	May 31, 2017
Publication date	Aug 4, 2020
Grant date	Aug 4, 2020

Abstract

Herein provided are methods and systems for reducing an acoustic signature of a gas turbine engine. An acceleration command for the engine is received. In response to receiving the acceleration command: a fuel flow to the engine is increased for a first predetermined time period; subsequent to the first predetermined time period, the fuel flow to the engine is reduced for a second predetermined time period; and subsequent to the second predetermined time period, the fuel flow to the engine is increased for a third time period.

First claim

The invention claimed is:

1. A method for reducing an acoustic signature of a gas turbine engine, comprising:
receiving an acceleration command for the gas turbine engine indicative of an acceleration from a ground idle state to a ground taxi state; and
in response to receiving the acceleration command:
increasing a fuel flow to the gas turbine engine for a first predetermined time period;
subsequent to the first predetermined time period, reducing the fuel flow to the gas turbine engine for a second predetermined time period; and
subsequent to the second predetermined time period, increasing the fuel flow to the gas turbine engine for a third time period.

2. The method of claim 1 , wherein the acceleration command is a first acceleration command, further comprising, in response to receiving a second acceleration command indicative of an acceleration from a ground idle state to a takeoff state, increasing the fuel flow to the gas turbine engine in accordance with a predetermined acceleration schedule.

3. The method of claim 1 , wherein reducing the fuel flow to the gas engine comprises substantially cutting off the fuel flow.

4. The method of claim 1 , wherein increasing the fuel flow to the gas turbine engine for the first predetermined time period comprises increasing the fuel flow to a first level, and wherein increasing the fuel flow to the gas turbine engine for the third time period comprises increasing the fuel flow to the first level.

5. The method of claim 1 , wherein increasing the fuel flow to the gas turbine engine for the first predetermined time period comprises increasing the fuel flow to a first level, and wherein increasing the fuel flow to the gas turbine engine for the third time period comprises increasing the fuel flow to a second level different from the first level.

6. The method of claim 5 , wherein the first level is less than the second level.

7. The method of claim 1 , wherein the second predetermined time period is of a shorter duration than the first predetermined time period.

8. The method of claim 1 , wherein the third time period lasts until receipt of a subsequent acceleration command.

9. A system for reducing an acoustic signature of a gas turbine gas turbine engine, comprising:
a processing unit; and
a non-transitory computer-readable memory communicatively coupled to the processing unit and comprising computer-readable program instructions executable by the processing unit for:
receiving an acceleration command for the gas turbine engine indicative of an acceleration from a ground idle state to a ground taxi state; and
in response to receiving the acceleration command:
increasing a fuel flow to the gas turbine engine for a first predetermined time period;
subsequent to the first predetermined time period, reducing the fuel flow to the gas turbine engine for a second predetermined time period; and
subsequent to the second predetermined time period, increasing the fuel flow to the gas turbine engine for a third time period.

10. The system of claim 9 , wherein the acceleration command is a first acceleration command, the computer-readable program instructions being further executable for, in response to receiving a second acceleration command indicative of an acceleration from a ground idle state to a takeoff state, increasing the fuel flow to the gas turbine engine in accordance with a predetermined acceleration schedule.

11. The system of claim 9 , wherein reducing the fuel flow to the gas turbine engine comprises substantially cutting off the fuel flow.

12. The system of claim 9 , wherein increasing the fuel flow to the gas turbine engine for the first predetermined time period comprises increasing the fuel flow to a first level, and wherein increasing the fuel flow to the gas turbine engine for the third time period comprises increasing the fuel flow to the first level.

13. The system of claim 9 , wherein increasing the fuel flow to the gas turbine engine for the first predetermined time period comprises increasing the fuel flow to a first level, and wherein increasing the fuel flow to the gas turbine engine for the third time period comprises increasing the fuel flow to a second level different from the first level.

14. The system of claim 13 , wherein the first level is less than the second level.

15. The system of claim 9 , wherein the second predetermined time period is of a shorter duration than the first predetermined time period.

16. The system of claim 9 , wherein the third time period lasts until receipt of a subsequent acceleration command.

17. A system for reducing an acoustic signature of a gas turbine gas turbine engine, comprising:
at least one fuel flow valve configured for regulating a rate of fuel flow to the gas turbine engine; and
a fuel flow control system communicatively coupled to the at least one fuel flow valve for controlling operation thereof by:
causing the at least one fuel flow valve to increase the fuel flow rate for a first predetermined time period in response to receiving an acceleration command indicative of an acceleration from a ground idle state to a ground taxi state;
subsequent to the first predetermined time period, causing the at least one fuel flow valve to reduce the fuel flow rate for a second predetermined time period; and
subsequent to the second predetermined time period, causing the at least one fuel flow valve to increase the fuel flow rate for a third time period.

Assignees

• Pratt & Whitney Canada

Inventors

• Joshi Ninad
• Meslioui Sid-Ali
• Yee Tony

Classifications

• B64D31/06

  actuated automatically · CPC title

• F02C9/44 Primary

  responsive to the speed of aircraft, e.g. Mach number control, optimisation of fuel consumption · CPC title

• F02C9/26 Primary

  Control of fuel supply (F02C9/48 takes precedence; fuel valves F02C7/232) · CPC title

• F05D2270/08

  to produce clean exhaust gases · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title