Flight vehicle engine with finned inlet

Patent metadata

Field	Value
Publication number	US-11204000-B2
Application number	US-201715468441-A
Country	US
Kind code	B2
Filing date	Mar 24, 2017
Priority date	Mar 24, 2017
Publication date	Dec 21, 2021
Grant date	Dec 21, 2021

Abstract

An air inlet for a flight vehicle engine includes at least one fin, at least partially upstream of a throat of the engine. The fin protrudes into a flow channel, extending beyond a boundary layer into the main airstream in the inlet. The fin causes mixing in the flow, bringing high-momentum flow into areas of the flow channel containing low-momentum flow by aggregating the boundary layer and causing it to lift from the surface. The fin may have a width and/or height that varies along its length in the flow direction, which may allow it to shape the flow around it in predictable ways, without resulting in excessive drag.

First claim

What is claimed is:

1. A flight vehicle comprising:
a fuselage; and
an engine mechanically coupled to the fuselage;
wherein the engine includes:
an air inlet;
an isolator downstream of the air inlet; and
a combustor downstream of the isolator;

wherein the air inlet compresses incoming airflow through a flow channel defined by the air inlet, down to a throat of minimum cross-section area;
wherein the air inlet includes a fin protruding into the flow channel and extending from a leading edge of a top surface of an inner wall of the air inlet that defines the flow channel, with at least part of the fin upstream of the throat;
wherein the fin protrudes into the flow channel to a maximum height of at least a boundary layer thickness and at most three times the boundary layer thickness of the airflow at a location of the fin, along the inner wall of the inlet; and
wherein the fin has a spine and curved walls on either side of the spine, with the maximum height of the fin at the spine.

2. The flight vehicle of claim 1 , wherein all of the fin is upstream of the throat.

3. The flight vehicle of claim 1 , wherein the fin extends into the throat.

4. The flight vehicle of claim 1 , wherein there is only a single fin in the inlet.

5. The flight vehicle of claim 1 , wherein there are a plurality of the fin in the inlet.

6. The flight vehicle of claim 5 , wherein the plurality of the fin include a pair of the fin side by side on the inner wall.

7. The flight vehicle of claim 5 , wherein there are no more than three of the fin in the inlet.

8. The flight vehicle of claim 1 , wherein the fin creates vortices that cause local flow mixing around the fin.

9. The flight vehicle of claim 8 , wherein the local flow mixing causes mixing between a flow in a boundary layer along the inner wall of the inlet, and a flow outside of the boundary layer, further away from the inner wall.

10. The flight vehicle of claim 1 , wherein the inlet is rectangular or super-elliptical in cross-section.

11. The flight vehicle of claim 10 , wherein the fin is located on a face of the inner wall of the inlet that is between two other inner walls of the inlet.

12. The flight vehicle of claim 1 , wherein the fin has a triangular cross section shape, in a direction perpendicular to a flow direction through the inlet.

13. The flight vehicle of claim 1 , wherein a height of the fin varies over a length of the fin.

14. The flight vehicle of claim 13 , wherein the height of the fin varies more slowly in an upstream part of the fin that is upstream of the maximum height, than in a downstream part of the fin that is downstream of the maximum height.

15. The flight vehicle of claim 1 , wherein the engine is a supersonic engine.

16. The flight vehicle of claim 1 , wherein the curved walls are steeper close to the spine, and flatten out away from the spine.

17. The flight vehicle of claim 1 , wherein the fin protrudes into the flow channel to the maximum height of at least twice the boundary layer thickness of the airflow at the location of the fin, along the inner wall of the inlet.

18. The flight vehicle of claim 1 , wherein the maximum height of the fin and a maximum width of the fin both occur in a downstream half of the fin.

19. The flight vehicle of claim 1 , wherein the fin causes a boundary layer to aggregate and then separate from the inner wall as a counter-rotating vortex pair.

20. The flight vehicle of claim 1 , wherein the spine is centered along a center width of the air inlet.

21. The flight vehicle of claim 1 , wherein the inner wall of the air inlet includes a bottom surface opposite the top surface and the bottom surface includes a V-shaped cut out.

Assignees

• Raytheon Co

Inventors

• O'Brien Timothy F
• Malo-Molina Faure
• Conners Timothy Raymond

Classifications

• F02K7/00

  Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof (rocket-engine plants F02K9/00) · CPC title

• B64C2230/26

  by using rib lets or hydrophobic surfaces · CPC title

• F05D2250/51

  Inlet · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• B64C30/00 Primary

  Supersonic type aircraft · CPC title