US3568703A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Supersonic jet engine inlet flueric bypass control
Assignee: Scientific Design LLC
•
Filing: 1969-04-07
•
Granted: 1971-03-09
•
Expires: 1989-04-07
Abstract
Abstract A flueric system for controlling the position of the normal shock wave in a turbojet diffuser is disclosed. Control is accomplished without the use of mechanically moving parts by providing an exhaust tube for reducing the pressure downstream of the normal shock. A fluid feedback path which is responsive to a pressure differential on opposing sides of the shock wave produces a fluid control signal which is capable of deflecting fluid away from the exhaust tube and thereby effectively closing off the exhaust tube whenever the shock wave has relocated itself in a stable position.
Inventors
- 👤 Raymond W Warren
- 👤 Allen B Holmes
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 13:07
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/04; F02C7/057; F15; F15C; F15C1/00; F15C1/002; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10T; Y10T137/00; Y10T137/0318; Y10T137/0324; Y10T137/0368; Y10T137/206; Y10T137/2273
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
50 words
A control system for improving the operating efficiency of a turbojet diffuser having an intake means and a minimum throat region, comprising: a. a pressure reducing means for reducing the pressure in said throat region; and b. a flueric control means for controlling the operation of said pressure reducing means.
Claim 2
Dependent Claim
50 words
A control system for improving the operating efficiency of a turbojet diffuser having an intake means and a minimum throat region, comprising: a. a pressure reducing means for reducing the pressure in said throat region; and b. a flueric control means for controlling the operation of said pressure reducing means.
Claim 3
Dependent Claim
47 words
The system of claim 1 wherein the pressure reducing means comprises an exhaust tube in fluid communication with said throat region and said control means comprises a control nozzle for directing control fluid into said throat region and blocking the flow of fluid into said exhaust tube.
Claim 4
Dependent Claim
33 words
The system of claim 2 further comprising a fluid feedback path connected between said fluid control nozzle and a point downstream of said throat region for supplying control fluid to said control nozzle.
Claim 5
Dependent Claim
38 words
The system of claim 3 wherein the junction of said exhaust tube and said control nozzle defines an interaction region, said interaction region being in fluid communication with said throat region, said control nozzle and said exhaust tube.
Claim 6
Dependent Claim
22 words
The combination defined in claim 4 further comprising a plurality of individual control systems spaced along the length of said turbojet diffuser.
Claim 7
Dependent Claim
35 words
The combination of claim 5 wherein the interaction regions of said control systems lie in a plane which is at an oblique angle with respect to the direction of fluid flow in said turbojet diffuser.
Claim 8
Dependent Claim
120 words
In the operation of a turbojet diffuser having an intake means and a throat region, the method of controlling the position of the normal shock wave comprising the steps of: a. exhausting a portion of the fluid through an exhaust tube located downstream of said normal shock wave to reduce the fluid pressure in the downstream region; b. sensing a fluid pressure differential between an upstream region and a downstream region of said shock wave; c. deriving a fluid control signal in response to said fluid pressure differential; and d. deflecting fluid away from said exhaust tube whenever said fluid control signal exceeds a minimum value, whereby said exhaust tube is effectively closed in response to said fluid control signal.
Claim 9
Dependent Claim
120 words
In the operation of a turbojet diffuser having an intake means and a throat region, the method of controlling the position of the normal shock wave comprising the steps of: a. exhausting a portion of the fluid through an exhaust tube located downstream of said normal shock wave to reduce the fluid pressure in the downstream region; b. sensing a fluid pressure differential between an upstream region and a downstream region of said shock wave; c. deriving a fluid control signal in response to said fluid pressure differential; and d. deflecting fluid away from said exhaust tube whenever said fluid control signal exceeds a minimum value, whereby said exhaust tube is effectively closed in response to said fluid control signal.
Claim 10
Dependent Claim
48 words
The method of claim 7 wherein the step of deriving a fluid control signal comprises the steps of: a. diverting a small portion of fluid from a region downstream of said shock wave, and b. feeding back said diverted fluid to a region upstream of said shock wave.
References Cited (Backward Citations)
CA493723A
Cited
US2948148A
Cited
US3111931A
Cited
US3068880A
Cited
US3204652A
Cited
US3212515A
Cited
US3348766A
Cited
US3460554A
Cited
US3452707A
Cited
US3472255A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1974-03-08 | 1974-09-07 | 1975-03-09 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-03-08 | 1978-09-07 | 1979-03-09 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-03-08 | 1982-09-07 | 1983-03-09 | $7700.00 | Window Closed / Lapsed |