Rotor noise suppression

Patent metadata

Field	Value
Publication number	US-9650962-B2
Application number	US-201314143343-A
Country	US
Kind code	B2
Filing date	Dec 30, 2013
Priority date	Mar 8, 2013
Publication date	May 16, 2017
Grant date	May 16, 2017

Abstract

An apparatus is disclosed that includes a gas turbine engine including a first rotor blade axially adjacent a second rotor blade and an aperture formed in one of the first rotor blade and the second rotor blade and structured to emit a fluid therefrom. A fluid source is in flow communication with the aperture and configured to flow the fluid through the aperture.

First claim

What is claimed is:

1. An apparatus, comprising:
an internal combustion engine configured to produce an exhaust gas as a result of a combustion process involving a fuel;
a first airfoil member located upstream of a second airfoil member wherein the first and second airfoil members are driven by work produced from the internal combustion engine;
an aperture disposed in at least one of the first airfoil member and the second airfoil member and structured to flow the exhaust gas;
an auxiliary exhaust flowpath extending from the internal combustion engine and arranged to convey the exhaust gas, the auxiliary exhaust flowpath operable to provide the exhaust gas to the aperture disposed in at least one of the first airfoil member and the second airfoil member; and
an exhaust exit structured to flow exhaust gas, the exhaust exit located aft of the first airfoil member and the second airfoil member.

2. The apparatus of claim 1 , wherein the first airfoil member is a first rotatable blade and the second airfoil member is a second rotatable blade, wherein the first rotatable blade is positioned upstream of the second rotatable blade, and wherein the internal combustion engine is a gas turbine engine.

3. The apparatus of claim 2 , wherein the aperture is disposed near a trailing edge portion of the first rotatable blade and wherein the aperture is disposed at a point of intersection of a mean camber line and a trailing edge of the first airfoil member.

4. The apparatus of claim 3 , wherein the aperture includes a series of apertures along the trailing edge portion, each aperture having a radial relation to each of the other apertures.

5. The apparatus of claim 2 , wherein the first rotatable blade is a first open rotor, the second rotatable blade is a second open rotor, and wherein the exhaust gas is a flow of products of combustion extracted from the gas turbine engine downstream of a combustor of the gas turbine engine.

6. The apparatus of claim 5 , wherein the first open rotor rotates contra to the second open rotor.

7. The apparatus of claim 5 , wherein the gas turbine engine includes an internal flow between a turbine and an exhaust opening, and wherein the auxiliary exhaust flowpath includes an upstream portion located between a turbine stage of the turbine and the exhaust opening.

8. The apparatus of claim 7 , which further includes a flow regulator in fluid communication with the auxiliary exhaust flowpath.

9. An apparatus, comprising:
a gas turbine engine structured to produce work through the expansion of an exhaust fluid flow to drive a rotor system having a plurality of rotor blades, the rotor system including a first rotor blade positioned immediately upstream of a second rotor blade such that a flow path between the first rotor blade is unobstructed from the second rotor blade, wherein one of the first rotor blade and the second rotor blade is structured to receive a portion of the exhaust fluid flow and eject the portion of exhaust flow to a working fluid stream that is accelerated by rotation of the first rotor blade or second rotor blade, wherein the gas turbine engine further includes an exhaust exit located aft of the first rotor blade and the second rotor blade and the exhaust exit is structured to flow exhaust gas therethrough.

10. The apparatus of claim 9 , wherein the first rotor blade includes an aperture through which the exhaust fluid flow is ejected.

11. The apparatus of claim 10 , wherein the aperture is disposed near a trailing edge of the first rotor blade.

12. The apparatus of claim 11 , wherein the first rotor blade is structured to rotate in a direction opposite the second rotor blade, and wherein the exhaust fluid flow is extracted from the gas turbine engine.

13. The apparatus of claim 11 , wherein the first rotor blade includes a plurality of first rotor blades each including an aperture disposed near a trailing edge portion, the apertures associated with each of the plurality of rotor blades structured to eject the exhaust fluid flow.

14. The apparatus of claim 13 , wherein the aperture associated with each of the plurality of first rotor blades includes a plurality of apertures, each aperture of the plurality of apertures located at a different radial position relative to each of the other apertures.

15. A method, comprising:
operating a gas turbine engine to compress a fluid, combust a mixture of the fluid and a fuel, and discharge the fluid forming an exhaust gas from the gas turbine engine through an opening downstream of a turbine;
providing power from the gas turbine engine to drive a pair of a first rotatable blade and a second rotatable blade to produce a motive force;
diverting a portion of the exhaust gas away from the opening to a flow channel in the first rotatable blade;
flowing the exhaust gas from the flow channel through an aperture in the first rotatable blade; and
flowing a portion of the exhaust gas through an exhaust exit located aft of the first rotatable blade and the second rotatable blade.

16. The method of claim 15 , which further includes altering a velocity gradient of an airflow upstream of the second rotatable blade as a result of the flowing.

17. The method of claim 16 , which further includes regulating the amount of exhaust gas flowing through the aperture.

18. The method of claim 16 , wherein diverting a portion of exhaust gas from a gas turbine engine further includes diverting a portion of exhaust gas downstream of a final turbine stage, and wherein the flowing exhaust gas through the aperture includes flowing exhaust gas through a plurality of apertures arranged along a span of the first rotatable blade.

19. The method of claim 18 , which further includes rotating the second rotatable blade in a direction opposing the rotation of the first rotatable blade.

Assignees

• Rolls Royce Corp

Inventors

• Karam Michael Abraham

Classifications

• B64C2230/28

  at propeller or rotor blades · CPC title

• F01D5/142

  of the blades of successive rotor or stator blade-rows · CPC title

• B64C2230/14

  achieving noise reductions · CPC title

• B64D2027/005

  Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR] · CPC title

• F02C3/067

  having counter-rotating rotors (F02C3/073 takes precedence) · CPC title