Pre-cooler inlet ducts that utilize active flow-control and systems and methods including the same

Patent metadata

Field	Value
Publication number	US-10316753-B2
Application number	US-201414491778-A
Country	US
Kind code	B2
Filing date	Sep 19, 2014
Priority date	Sep 19, 2014
Publication date	Jun 11, 2019
Grant date	Jun 11, 2019

Abstract

Pre-cooler inlet ducts that utilize active flow-control and systems and methods including the same are disclosed herein. The systems include a pre-cooler inlet duct for a jet engine that is configured to receive a pre-cooler air stream and to direct the pre-cooler air stream into a heat exchanger. The pre-cooler inlet duct includes a flow-directing surface, which defines at least a portion of the pre-cooler inlet duct, and an active flow-control device. The active flow-control device is located to modify a boundary layer fluid flow within a boundary layer adjacent the flow-directing surface to resist separation of the boundary layer from the flow-directing surface when the pre-cooler air stream flows through the pre-cooler inlet duct. The methods include methods of resisting boundary layer separation in the pre-cooler inlet duct by flowing the pre-cooler air stream across the flow-directing surface and modifying the boundary layer with the active flow-control device.

First claim

The invention claimed is:

1. A jet engine, comprising:
a nacelle including an inlet configured to receive an air stream;
a compressor positioned within the nacelle and configured to receive the air stream and to pressurize the air stream to generate a compressed air stream;
a pre-cooler inlet duct positioned within the nacelle and configured to receive a portion of the compressed air stream as a pre-cooler air stream; and
a heat exchanger positioned within the nacelle and configured to receive the pre-cooler air stream, wherein the pre-cooler inlet duct is configured to direct the pre-cooler air stream into the heat exchanger; and
further wherein the pre-cooler inlet duct includes;
(i) a flow-directing surface that defines at least a portion of the pre-cooler inlet duct and is shaped to direct the pre-cooler air stream into the heat exchanger; and
(ii) an active flow-control device located to modify a boundary layer fluid flow within a boundary layer adjacent the flow-directing surface to resist separation of the boundary layer from the flow-directing surface when the pre-cooler air stream flows through the pre-cooler inlet duct, wherein the active flow-control device is configured to inject a flow-control fluid stream into the boundary layer through an injection orifice that is defined by the flow-directing surface, wherein the injection orifice is configured to inject the flow-control fluid stream at an injection angle that periodically varies between a lower angle limit and an upper angle limit, and further wherein the lower angle limit and the upper angle limit are defined in a plane that is parallel to a surface normal direction of the flow-directing surface;
and wherein the injection angle contains a first directional component that is parallel to a circumferential direction of the jet engine, and a second directional component that is parallel to a longitudinal axis of the jet engine.

2. The jet engine of claim 1 , wherein the compressor provides the portion of the compressed air stream that comprises the pre-cooler air stream to the pre-cooler inlet duct at an average flow speed of at least 100 meters/second (m/s) and less than 350 m/s, and further wherein the active flow control device resists separation of the boundary layer from the flow-directing surface.

3. The jet engine of claim 1 , wherein the active flow-control device is configured to continuously inject the flow-control fluid stream into the boundary layer when the pre-cooler air stream is flowing through the pre-cooler inlet duct.

4. The jet engine of claim 1 , wherein the active flow-control device is configured to intermittently inject the flow-control fluid stream into the boundary layer when the pre-cooler air stream is flowing through the pre-cooler inlet duct.

5. The jet engine of claim 1 , wherein the active flow-control device is configured to inject a plurality of flow-control fluid streams into the boundary layer.

6. The jet engine of claim 5 , wherein the active flow-control device is configured to vary which of the plurality of flow-control fluid streams is being injected into the boundary layer at a given point in time.

7. The jet engine of claim 1 , wherein the active flow-control device includes a vortex generator configured to generate a vortex within the boundary layer.

8. The jet engine of claim 1 , wherein the active flow-control device comprises a suction assembly configured to remove a suction stream from the boundary layer.

9. An aircraft, comprising:
an airframe; and
the jet engine of claim 1 , wherein the jet engine is operatively attached to the airframe.

10. The jet engine of claim 1 , wherein the plane that is parallel to the surface normal direction of the flow-directing surface also is parallel to a flow direction of the pre-cooler air stream.

11. A method of resisting boundary layer separation from a flow-directing surface of a pre-cooler inlet duct of a jet engine, the method comprising:
receiving an air stream with an inlet of a nacelle of the jet engine;
compressing the air stream with a compressor of the jet engine to pressurize the air stream and generate a compressed air stream;
flowing a portion of the compressed air stream, as a pre-cooler air stream, across the flow-directing surface of the pre-cooler inlet duct and through the pre-cooler inlet duct, wherein the flowing includes generating a boundary layer adjacent the flow-directing surface, and further wherein the boundary layer includes a boundary layer fluid flow; and
modifying the boundary layer fluid flow with an active flow-control device to resist separation of the boundary layer from the flow-directing surface of the pre-cooler inlet duct, wherein the modifying includes injecting a flow-control fluid stream into the boundary layer through an injection orifice that is defined by the flow-directing surface, wherein the injection orifice is configured to inject the flow-control fluid stream at an injection angle, wherein the injecting includes periodically varying the injection angle between a lower angle limit and an upper angle limit, and further wherein the lower angle limit and the upper angle limit are defined in a plane that is parallel to a surface normal direction of the flow-directing surface;
and wherein the injection angle contains a first directional component that is parallel to a circumferential direction of the jet engine, and a second directional component that is parallel to a longitudinal axis of the jet engine.

12. The method of claim 11 , wherein the injecting includes at least one of:
(i) continuously injecting the flow-control fluid stream while the pre-cooler air stream is flowing through the pre-cooler inlet duct; and
(ii) intermittently injecting the flow-control fluid stream while the pre-cooler air stream is flowing through the pre-cooler inlet duct.

13. The method of claim 11 , wherein the method further includes directing a compressed air stream through the injection orifice to generate the flow-control fluid stream.

14. The method of claim 11 , wherein the injecting includes injecting a plurality of flow-control fluid streams into the boundary layer, and further wherein the injecting includes varying which of the plurality of flow-control fluid streams is being injected into the boundary layer at a given point in time.

15. The method of claim 11 , wherein the modifying includes at least one of:
(i) generating a vortex within the boundary layer with a vortex generator; and
(ii) removing a suction stream from the boundary layer with a suction assembly.

16. The method of claim 11 , wherein:
(i) the flowing includes flowing the pre-cooler inlet stream at an average flow speed of at least 100 meters/second (m/s) and less than 350 m/s; and
(ii) the modifying includes resisting separation of the boundary layer from the flow-directing surface.

17. The method of claim 11 , wherein the plane that is parallel to the surface normal direction of the flow-directing surface also is parallel to a flow direction of the pre-cooler air stream.

Assignees

• Boeing Co

Inventors

• Packard Nathan O
• Willie Robert H
• Tretow Paul R

Classifications

• F05D2210/30

  Flow characteristics · CPC title

• F02C9/16

  Control of working fluid flow (F02C9/48 takes precedence; control of air-intake flow F02C7/057) · CPC title

• F01D25/125

  of bearings · CPC title

• F05D2270/17

  to control boundary layer · CPC title

• B64D2033/0286

  for turbofan engines · CPC title