Apparatus, method and system for gas turbine engine noise reduction

• US 7,159,383 B2
• Filed: 10/02/2001
• Issued: 01/09/2007
• Est. Priority Date: 10/02/2000
• Status: Expired due to Term

• Current Assignee: ROHR Incorporated (Rtx Corporation)
• Original Assignee: ROHR Incorporated (Rtx Corporation)
• Inventors: Barton, legal representative, Whitmire, Julia K., Barton, deceased, Brice, David C.
• Primary Examiner(s): Rodriguez; William H.
• Application Number:
  US10/343,566
• Publication Number:
  US 20040237501A1
• Time in Patent Office: 1,925 Days
• Field of Search: 60/204,208,211,230,231,770,226.1,262,263,264,226.3 239/265.11,265.19,265.23,265.17,265.29,265.31 181/213,220
• US Class Current: 60/226.1
• CPC Class Codes: B64D 33/06 Silencing exhaust or propulsion jets ground installations B64F
• CPC Class Codes: F02K 1/34 for attenuating noise
• CPC Class Codes: F02K 1/386 mixing devices in the jet pipe, e.g. for mixing primary and secondary flow

Abstract

An apparatus for reducing gas turbine engine noise, such as noise generated by an aircraft gas turbine engine, comprises at least one and preferably a plurality of gas injectors for injecting gas such as high pressure engine bleed air, diverted core air, air obtained from a pressurized storage container or air obtained from a synthetic jet actuator into the area proximate to one or more engine nozzle portions, thereby disrupting the noise-generating gas streams generated by the engine exhaust and the travel of the airplane through the air. The apparatus is particularly useful for reducing engine noise during the takeoff period of aircraft flight.

Claims

1. An apparatus for reducing noise generated by an aircraft gas turbine engine having an engine core with a longitudinal centerline, a core nozzle having an exit plane and fan nozzle having an exit plane, wherein a fan air stream flows between the fan nozzle and the core nozzle and a core air stream flows between the core nozzle and the engine core when the aircraft is in flight, the apparatus comprises at least one gas injector for injecting gas into the fan air stream proximate to the fan nozzle exit plane toward the engine core longitudinal centerline, into the core air stream proximate to the core nozzle exit plane toward the engine core longitudinal centerline, or combination thereof, and the at least one gas injector has a plurality of gas exit ports having a shape which may be slotted ports, circular ports or a combination of slotted ports and circular ports.

2. The apparatus of claim 1, in which the at least one gas injector is crescent-shaped.

3. The apparatus of claim 1, in which the at least one gas injector is located on the fan flow side of the engine nozzle portion exit plane.

4. The apparatus of claim 1, in which the engine has a core side and the at least one gas injector is located on the core side of the engine.

5. The apparatus of claim 1, in which the core nozzle, fan nozzle, or combination thereof comprises flutes for directing the gas.

6. The apparatus of claim 1, in which the engine has a core cowl, and the gas is injected under the cowl.

7. The apparatus of claim 1, in which the gas injected by the at least one gas injector is engine bleed air.

8. The apparatus of claim 1, in which the gas injected by the at least one gas injector is diverted engine core air.

9. The apparatus of claim 1, in which the gas injected by the at least one gas injector is air obtained from a pressurized storage container.

10. The apparatus of claim 1, in which at least one synthetic jet actuator is used to inject gas into the fan air stream proximate to the fan nozzle exit plane toward the engine core longitudinal centerline, into the core air stream proximate to the core nozzle exit plane toward the engine core longitudinal centerline, or combination thereof.

11. The apparatus of claim 10, in which the at least one synthetic jet actuator is used to inject gas into an area proximate to the core air stream.

12. The apparatus of claim 10, in which the at least one synthetic jet actuator is used to inject gas into an area proximate to the fan air stream.

13. The apparatus of claim 10, in which at least a first synthetic jet actuator is used to inject gas into an area proximate to the fan air stream, and at least a second synthetic jet actuator is used to inject gas into an area proximate to the core air stream.

14. A method for reducing noise generated by an aircraft gas turbine engine, the method comprising:

(a) providing an apparatus for reducing noise generated by the gas turbine engine, the engine having an engine core with a longitudinal centerline, a core nozzle having an exit plane and fan nozzle having an exit plane, wherein a fan air stream flows between the fan nozzle and the core nozzle and a core air stream flows between the core nozzle and the engine core when the aircraft is in flight, the apparatus comprising at least one gas injector for injecting gas into the fan air stream proximate to the fan nozzle exit plane toward the engine core longitudinal centerline, into the core air stream proximate to the core nozzle exit plane toward the engine core longitudinal centerline, or combination thereof, and the at least one gas injector having a plurality of gas exit ports having a shape which may be slotted ports, circular ports or a combination of slotted ports and circular ports;

(b) introducing air into the apparatus during a takeoff portion of aircraft flight.

15. The method of claim 14, in which the introduction of air into the apparatus is halted during a cruise portion of the aircraft flight.

16. A system for reducing noise generated by an aircraft gas turbine engine, the system comprising:

(a) a source of gas;

(b) an apparatus for reducing noise generated by the gas turbine engine, the engine having an engine core with a longitudinal centerline, a core nozzle having an exit plane and fan nozzle having an exit plane, wherein a fan air stream flows between the fan nozzle and the core nozzle and a core air stream flows between the core nozzle and the engine core when the aircraft is in flight, the apparatus comprising at least one gas injector for injecting gas into the fan air stream proximate to the fan nozzle exit plane toward the engine core longitudinal centerline, into the core air stream proximate to the core nozzle exit plane toward the engine core longitudinal centerline, or combination thereof, and the at least one gas injector having a plurality of gas exit ports having a shape which may be slotted ports, circular ports or a combination of slotted ports and circular ports.

17. An apparatus for reducing noise generated by an aircraft gas turbine engine, the engine having an engine core with a longitudinal centerline, a core nozzle having an exit plane and fan nozzle having an exit plane, wherein a fan air stream flows between the fan nozzle and the core nozzle and a core air stream flows between the core nozzle and the engine core when the aircraft is in flight, the apparatus comprises at least one gas injector for injecting gas into the fan air stream proximate to the fan nozzle exit plane toward the engine core longitudinal centerline, into the core air stream proximate to the core nozzle exit plane toward the engine core longitudinal centerline, or combination thereof, and the at least one gas injector comprises a gas delivery tube which has a plurality of gas exit ports having a shape which may be slotted ports, circular ports or a combination of slotted ports and circular ports, the engine has an inner barrel, and the tube is circumferentially located around an outer surface of the inner barrel.