Passive bypass for mitigation of inlet buzz in supersonic or hypersonic air-breathing engines

Patent metadata

Field	Value
Publication number	US-12221925-B1
Application number	US-202418635986-A
Country	US
Kind code	B1
Filing date	Apr 15, 2024
Priority date	Apr 15, 2024
Publication date	Feb 11, 2025
Grant date	Feb 11, 2025

Abstract

A passive bypass for an inlet to a supersonic or hypersonic air-breathing engine allows airflow in the inlet to exit through the cowling when the inlet supplies more airflow than the air-breathing engine demands. The air-breathing engine may be the only form of propulsion or a secondary form of propulsion to reach higher speeds. The passive bypass includes a plurality of lower channels in the cowling that are operatively coupled to the inlet diffuser at an inner surface of the cowling and swept forward towards the throat, a plenum in the cowling operatively coupled to the plurality of lower openings and a plurality of upper channels in the cowling that are operatively coupled to the plenum and swept back away from the throat to an outer surface of the cowling. A serpentine path through the plurality of lower openings, the plenum and the plurality of upper openings allows airflow in the inlet to exit through the cowling when the inlet supplies more airflow than the air-breathing engine demands.

First claim

I claim:

1. A passive bypass for an inlet to an air-breathing engine, said inlet defined as a void space between a flight vehicle body and a cowling, said inlet including a throat and a diffuser configured to supply airflow to the engine, said passive bypass comprising:
a plurality of lower channels in the cowling and operatively coupled to the diffuser at an inner surface of the cowling and swept forward towards the throat;
a plenum in the cowling operatively coupled to the plurality of lower openings; and
a plurality of upper channels in the cowling and operatively coupled to the plenum and swept back away from the throat to an outer surface of the cowling,
wherein a serpentine path through the plurality of lower openings, the plenum and the plurality of upper openings allows airflow in the inlet to exit through the cowling when the inlet supplies more airflow than the air-breathing engine demands.

2. The passive bypass of claim 1 , wherein the inlet's void space is 2D or 3D.

3. The passive bypass of claim 1 , wherein the inlet is unshrouded.

4. The passive bypass of claim 1 , wherein the plurality of lower channels are swept forward at an angle greater than 90 degrees with respect to the airflow in the inlet.

5. The passive bypass of claim 1 , wherein the plenum is configured to cause the airflow from the plurality of lower openings to decelerate and flow in a counter-clockwise direction.

6. The passive bypass of claim 1 , wherein the plurality of upper channels are swept backward at an angle greater than 90 degrees with respect to the airflow in the inlet.

7. The passive bypass of claim 1 , wherein the number of lower channels is less than the number of upper channels and the area of an individual lower channel is less than the area of an individual upper channel.

8. A passive bypass for an inlet to an air-breathing engine, said inlet defined as a void space between a flight vehicle body and a cowling, said inlet including a throat and a diffuser configured to supply airflow to the engine, said passive bypass comprising:
a plurality of lower channels in the cowling and operatively coupled to the diffuser at an inner surface of the cowling and swept forward towards the throat;
a plenum in the cowling operatively coupled to the plurality of lower openings; and
a plurality of upper channels in the cowling and operatively coupled to the plenum and swept back away from the throat to an outer surface of the cowling;
wherein when the air-breathing engine is off, supersonic airflow into the inlet produces a shock wave that is established in the diffuser, wherein all subsequent airflow entering the inlet is diverted forward through the lower openings into the plenum where the pressure is reduced and then directed aft out of the plurality of upper openings into the atmosphere,
wherein when the air-breathing engine is on, a serpentine path through the plurality of lower openings, the plenum and the plurality of upper openings limits the amount of airflow that leaks out of the cowling.

9. The passive bypass of claim 8 , further comprising:
a flight vehicle that includes a booster engine configured to get the flight vehicle up to a supersonic speed at which the air-breathing engine is turned on.

10. The passive bypass of claim 9 , further comprising:
a combustion chamber that includes a booster propellant and an air-breathing propellant; and
a port cover positioned aft of the inlet diffuser and at an opening to the combustion chamber;
wherein the port cover is in a closed position to allow the booster propellant to combust and boost the flight vehicle up to speed,
wherein once at speed the port cover is moved to an open position to allow supersonic airflow to flow through the opening into the combustion chamber to combust with the air-breathing propellant to increase the speed of the flight vehicle.

11. The passive bypass of claim 8 , wherein the plurality of lower channels are swept forward at an angle greater than 90 degrees with respect to the airflow in the inlet.

12. The passive bypass of claim 8 , wherein the plenum is configured to cause the airflow from the plurality of lower openings to decelerate and flow in a counter-clockwise direction.

13. The passive bypass of claim 8 , wherein the plurality of upper channels are swept backward at an angle greater than 90 degrees with respect to the airflow in the inlet.

14. The passive bypass of claim 8 , wherein the number of lower channels is less than the number of upper channels and the area of an individual lower channel is less than the area of an individual upper channel.

15. A passive bypass for an inlet to an air-breathing engine, said inlet defined as a void space between a flight vehicle body and a cowling, said inlet including a throat and a diffuser configured to supply airflow to the engine, said passive bypass comprising:
a plurality of lower channels in the cowling and operatively coupled to the diffuser at an inner surface of the cowling and swept forward towards the throat;
a plenum in the cowling operatively coupled to the plurality of lower openings; and
a plurality of upper channels in the cowling and operatively coupled to the plenum and swept back away from the throat to an outer surface of the cowling;
wherein when the air-breathing engine is on,
during normal operation, supersonic airflow into the inlet produces a shock wave that is established in the diffuser aft of the passive bypass such that an amount of airflow that leaks out through the passive bypass is limited,
wherein if the shock wave is disturbed and moves forward toward the throat, airflow entering the inlet is diverted forward through the lower openings into the plenum where the pressure is reduced and then directed aft out of the plurality of upper openings into the atmosphere to prevent the shock wave from reaching the throat.

16. The passive bypass of claim 15 , further comprising:
a flight vehicle that includes only the air-breathing engine as a source of propulsion.

17. The passive bypass of claim 16 , wherein the air-breathing engine is a gas turbine engine.

18. The passive bypass of claim 15 , wherein the plurality of lower channels are swept forward at an angle greater than 90 degrees with respect to the airflow in the inlet, the plenum is configured to cause the airflow from the plurality of lower openings to decelerate and flow in a counter-clockwise direction, and the plurality of upper channels are swept backward at an angle greater than 90 degrees with respect to the airflow in the inlet.

19. The passive bypass of claim 15 , wherein the number of lower channels is less than the number of upper channels and the area of an individual lower channel is less than the area of an individual upper channel.

Assignees

• Raytheon Co

Inventors

• O'Brien Timothy

Classifications

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F05D2220/80

  in supersonic vehicles excluding hypersonic vehicles or ram, scram or rocket propulsion · CPC title

• F05D2260/606

  Bypassing the fluid · CPC title

• F05D2220/10

  in ram-jet engines or ram-jet driven vehicles · CPC title

• F02C7/042

  having variable geometry · CPC title