Propulsion system using large scale vortex generators for flow redistribution and supersonic aircraft equipped with the propulsion system

Patent metadata

Field	Value
Publication number	US-10981659-B2
Application number	US-201815863306-A
Country	US
Kind code	B2
Filing date	Jan 5, 2018
Priority date	Feb 14, 2013
Publication date	Apr 20, 2021
Grant date	Apr 20, 2021

Abstract

An arrangement for use with a propulsion system for a supersonic aircraft includes a center body configured for coupling to an inlet and to support a boundary layer formed when the supersonic aircraft is flown at a predetermined altitude supersonic speed. The arrangement further includes a first vortex generator disposed on the center body. The first vortex generator extends a first height above the center body. The arrangement still further includes a second vortex generator disposed on the center body. The second vortex generator extends a second height above the center body, the second height being greater than the first height. The first height and the second height are greater than approximately seventy-five percent of a thickness of the boundary layer proximate a location of the first vortex generator and the second vortex generator, respectively, when the aircraft if flown at the predetermined altitude and the predetermined speed.

First claim

What is claimed is:

1. An arrangement for use with a propulsion system for a supersonic aircraft, the arrangement comprising:
a center body configured for coupling to an inlet and to support a boundary layer formed when the supersonic aircraft is flown at a predetermined altitude and a predetermined speed greater than Mach 1;
a first vortex generator disposed on the center body, the first vortex generator extending a first height above the center body; and
a second vortex generator disposed on the center body, said second vortex generator extending a second height above the center body, the second height being greater than the first height,
wherein said first height and said second height are greater than approximately seventy-five percent of a thickness of the boundary layer proximate a location of the first vortex generator and the second vortex generator, respectively, when the aircraft is flown at the predetermined altitude and the predetermined speed.

2. The arrangement of claim 1 , wherein one of the first height and the second height are greater than 100% of the thickness of the boundary layer.

3. The arrangement of claim 1 , wherein one of the first height and the second height are greater than one hundred and twenty percent of the thickness of the boundary layer.

4. The arrangement of claim 1 , wherein the first height and the second height are greater than one hundred and twenty-five percent of the thickness of the boundary layer.

5. The arrangement of claim 1 , wherein the first vortex generator and the second vortex generator are disposed circumferentially about the center body.

6. The arrangement of claim 1 , wherein the second vortex generator forms a first generator pair with the first vortex generator.

7. The arrangement of claim 1 , wherein the first vortex generator has a substantially rectangular shape.

8. The arrangement of claim 1 , wherein the first vortex generator has an aspect ratio of approximately 2.

9. A propulsion system for a supersonic aircraft, the propulsion system comprising:
a plurality of vortex generators positioned upstream of an engine of the propulsion system, each vortex generator of the plurality of vortex generators having a height such that when the supersonic aircraft is flown at a predetermined altitude and at a predetermined cruise speed, the predetermined cruise speed being greater than Mach 1, the plurality of vortex generators create a plurality of vortices that propagate at least partially outside of a boundary layer formed proximate a surface of a supersonic inlet, the plurality of vortices causing a high-velocity portion of the airflow to move towards the engine core and a low-velocity portion of the airflow to move towards the engine bypass prior to the airflow reaching a face of the engine, the plurality of vortex generators being disposed aft of a terminal shock formed when the supersonic aircraft is flown at the predetermined cruise speed, and each vortex generator of the plurality of vortex generators having a height greater than a thickness of the boundary layer at the location of each vortex generator of the plurality of vortex generators.

10. The propulsion system of claim 9 , wherein the height of each vortex generator of the plurality of vortex generators does not exceed one hundred and twenty-five percent of the thickness of the boundary layer at the location of each vortex generator of the plurality of vortex generators.

11. The propulsion system of claim 9 , wherein the plurality of vortex generators are arranged circumferentially about the surface of the supersonic inlet.

12. The propulsion system of claim 9 , wherein the plurality of vortex generators are arranged circumferentially about an inner surface of a shroud of the propulsion system.

13. The propulsion system of claim 9 , wherein the plurality of vortex generators are arranged circumferentially about both the surface of the supersonic inlet and an inner surface of a shroud of the propulsion system.

14. The propulsion system of claim 9 , wherein the plurality of vortex generators are arranged in pairs of vortex generators.

15. The propulsion system of claim 14 , wherein each vortex generator of each pair of vortex generators is oriented with respect to the airflow so as to have an angle of attack.

16. The propulsion system of claim 15 , wherein the angle of attack is between sixteen degrees and twenty-four degrees.

17. The propulsion system of claim 15 , wherein each vortex generator of each pair of vortex generators is oriented at opposite angles of attack to each other.

18. The propulsion system of claim 9 , wherein the plurality of vortex generators are arranged such that the vortices generate both an up-wash and a downwash.

19. The propulsion system of claim 9 , wherein the predetermined altitude comprises a predetermined cruise altitude.

20. A propulsion system for a supersonic aircraft, the propulsion system comprising:
a plurality of vortex generators positioned upstream of an engine of the propulsion system, each vortex generator of the plurality of vortex generators having a height such that when the supersonic aircraft is flown at a predetermined altitude and at a predetermined cruise speed, the predetermined cruise speed being greater than Mach 1, the plurality of vortex generators create a plurality of vortices that propagate at least partially outside of a boundary layer formed proximate a surface of a supersonic inlet, the plurality of vortices causing a high-velocity portion of the airflow to move towards the surface and a low-velocity portion of the airflow to move away from the surface prior to the airflow reaching a face of the engine, the plurality of vortex generators being disposed aft of a terminal shock formed when the supersonic aircraft is flown at the predetermined cruise speed, and each vortex generator of the plurality of vortex generators having a height greater than a thickness of the boundary layer at the location of each vortex generator of the plurality of vortex generators.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Rybalko Michael
• Conners Timothy R
• Wayman Thomas R

Classifications

• B64D27/02

  Aircraft characterised by the type or position of power plants · CPC title

• B64C30/00

  Supersonic type aircraft · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• F05D2210/33

  Turbulent flow · CPC title

• B64D29/00 Primary

  Power-plant nacelles, fairings or cowlings · CPC title