US3667233A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Dual mode supersonic combustion ramjet engine
Assignee: United States Department of the Air Force
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Filing: 1969-11-14
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Granted: 1972-06-06
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Expires: 1989-11-14
Abstract
Abstract A supersonic ramjet engine having a fixed-geometry combustion chamber. The ramjet engine is operated in the subsonic mode by injecting fuel in fuel injectors located in a uniform crosssection portion of the combustion chamber and in the supersonic mode by injecting fuel in fuel injectors located upstream of the subsonic injectors in an adjacent expanding portion of the combustion chamber.
Inventors
- 👤 Edward T Curran
- 👤 Frank D Stull
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 15:52
CPC Classifications
F; F02; F02K; F02K7/00; F02K7/10; F02K7/14
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
87 words
A supersonic combustion ramjet engine, comprising: a combustion chamber having an inlet cowl section; a first combustion section having a substantially uniform cross section along its length; a second combustion section diverging in the direction of flow between the inlet and the uniform section and a divergent exit section; a first means for selectively directing a flow of fuel into said first combustion section; a second means for selectively directing a flow of fuel into the second combustion section and flameholder means in said first combustion section.
Claim 2
Dependent Claim
87 words
A supersonic combustion ramjet engine, comprising: a combustion chamber having an inlet cowl section; a first combustion section having a substantially uniform cross section along its length; a second combustion section diverging in the direction of flow between the inlet and the uniform section and a divergent exit section; a first means for selectively directing a flow of fuel into said first combustion section; a second means for selectively directing a flow of fuel into the second combustion section and flameholder means in said first combustion section.
Claim 3
Dependent Claim
40 words
The device as recited in claim 1 wherein said combustion chamber is formed by three substantially straight wall members having streamlined inlet and outlet portions and a fourth chamber shaping wall member providing the different sections of the combustion chamber.
Claim 4
Dependent Claim
39 words
The device as recited in claim 1 wherein said combustion chamber is formed of a substantially uniform annular member having streamlined inlet and outlet portions and a central body means for forming the different sections of the combustion chamber.
Claim 5
Dependent Claim
89 words
The device as recited in claim 1 wherein said means for directing a flow of fuel into said second combustion section includes a plurality of nozzles adjacent the upstream end of the second combustion section and means for providing a low velocity fuel spray from said nozzles and wherein said means for directing a fuel flow into said first combustion section includes a plurality of nozzles adjacent said first nozzles and means for providing a high velocity fuel spray through the second combustion section into the first combustion section.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-06-06 | 1975-12-06 | 1976-06-06 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-06-06 | 1979-12-06 | 1980-06-06 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-06-06 | 1983-12-06 | 1984-06-06 | $7700.00 | Window Closed / Lapsed |