High-speed jet noise reduction via fluidic injection

• US 8,640,820 B2
• Filed: 01/11/2012
• Issued: 02/04/2014
• Est. Priority Date: 01/11/2012
• Status: Expired due to Fees

• Current Assignee: Polytechnic Institute Of New York University (New York University)
• Original Assignee: Polytechnic Institute Of New York University (New York University)
• Inventors: Kalkhoran, Iraj M., Caeti, Ryan B.
• Primary Examiner(s): Phillips, Forrest M
• Application Number:
  US13/348,077
• Publication Number:
  US 20130175353A1
• Time in Patent Office: 755 Days
• Field of Search: 181/220, 181/213, 415/119
• US Class Current: 181/213
• CPC Class Codes: F02K 1/34 for attenuating noise

Abstract

A noise reducer for reducing engine noise of a jet engine having a central axis and a main exhaust nozzle. The noise reducer includes a tubular member having ports at a distal end and is aligned along the central axis. The ports are located in the exhaust stream of the engine outside the main exhaust nozzle. A gaseous flow is injected into the exhaust stream from the ports in an angled direction with respect to the central axis.

Claims

1. A noise reducer for reducing engine noise of a jet engine having a central axis and a main exhaust nozzle, the noise reducer comprising:

a tubular member disposed within the jet engine and having a plurality of ports at a distal end of the tubular member,

wherein the tubular member is aligned along the central axis, and the ports are disposed in the exhaust stream outside the main exhaust nozzle,

wherein the tubular member has an aspect ratio of between 0 and 0.25, the aspect ratio being defined as a ratio of a cross-section area of the tubular member to a cross-section area of the main exhaust nozzle; and

wherein a gaseous flow is injected into the exhaust stream through the plurality of ports in an angled direction with respect to the central axis.

2. The noise reducer according to claim 1, wherein the jet engine is operated at a supersonic speed.

3. The noise reducer according to claim 1, wherein the gaseous flow includes air.

4. The noise reducer according to claim 1, wherein said tubular member has an effective length between the main exhaust nozzle and the ports set to be between 0.5 times the diameter of the main exhaust nozzle and 3.0 times the diameter of the main exhaust nozzle.

5. The noise reducer according to claim 4, wherein the effective length is 2.5 times the diameter of the main exhaust nozzle.

6. The noise reducer according to claim 1, wherein the jet engine is operated at a supersonic speed, and the gaseous flow exhibits a mass flow rate between about 1.6 percent and 7 percent of the mass flow rate of the exhaust stream.

7. The noise reducer according to claim 6, wherein the mass flow rate is about 7 percent of the mass flow rate of the exhaust stream.

8. The noise reducer according to claim 1, wherein the gaseous flow is injected into the exhaust stream at a sonic speed.

9. The noise reducer according to claim 1, wherein the jet engine is operated at a subsonic speed.

10. The noise reducer according to claim 1, wherein the jet engine is operated at a sonic speed.

11. The noise reducer according to claim 1, wherein the gaseous flow is injected into the exhaust stream through the plurality of ports in a direction substantially perpendicular to the central axis.

12. A method for reducing noise in a jet engine generating an exhaust stream, comprising:

introducing a central axis-aligned tubular structural member in the exhaust stream exiting a main exhaust nozzle of the jet engine, the tubular member having an aspect ratio of between 0 and 0.25, with the aspect ratio being defined as a ratio of a cross-section area of the tubular member to a cross-section area of the main exhaust nozzle; and

injecting a flow of gas at an end of the structural member in an angled direction with respect to the central axis of the jet engine.

13. The method according to claim 12, further comprising:

setting an effective length of the structural member between the distal end of structural member and the main exhaust nozzle.

14. The method according to claim 12, further comprising:

setting a ratio of the mass flow rate of the gaseous flow to the exhaust stream.

15. The method according to claim 12, wherein the flow of gas is injected in a direction substantially perpendicular to the central axis of the jet engine.