Patent US3802193A successfully refreshed from Google Patents.
US3802193A
Expired / Lapsed
US
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Barrier ring injector
Assignee: United States Department of the Air Force
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Filing: 1972-11-29
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Granted: 1974-04-09
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Expires: 1992-11-29
Abstract
Abstract A rocket engine injector device including three flanged concentric annular members and a manifold ring assembled to provide the high injection density required for barrier cooling. The barrier ring assembly includes an inner oxidizer metering ring serving as an oxidizer feed and a second ring for feeding oxidizer and metering fuel positioned around the inner ring. A third ring is fitted over the second ring for feeding fuel thereto. A fourth ring positioned around the third ring serves as a propellant manifold for barrier cooling the injector assembly.
Inventors
- 👤 K Wong
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-09 00:54
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/42; F02K9/44; F02K9/52
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
198 words
A barrier ring injector for supplying propellant to a rocket engine having a combustion chamber said injector comprising a first annular member having an outwardly extending flange attached to the upper edge thereof, means on the outer surface of said first annular member for metering the flow of propellant thereover, a second annular member positioned in close contact around said first annular member, a flange extending outwardly from the upper edge of said second annular member for feeding propellant to the outer surface of said first annular ring, means on the outer surface of said secoNd annular member for metering the flow of propellant thereover, the propellant flowing over the surface of said first and second annular members being mixed upon exit therefrom, a third annular member positioned in close contact around said second annular member, said third annular member having a flange extending outwardly from the upper edge thereof for feeding propellant to the outer surface of said second annular member, and a fourth annular member positioned around the outer edges of the flanges on said first, second and third annular members, said fourth annular member having means attached thereto for feeding propellant to said annular members.
Claim 2
Dependent Claim
198 words
A barrier ring injector for supplying propellant to a rocket engine having a combustion chamber said injector comprising a first annular member having an outwardly extending flange attached to the upper edge thereof, means on the outer surface of said first annular member for metering the flow of propellant thereover, a second annular member positioned in close contact around said first annular member, a flange extending outwardly from the upper edge of said second annular member for feeding propellant to the outer surface of said first annular ring, means on the outer surface of said secoNd annular member for metering the flow of propellant thereover, the propellant flowing over the surface of said first and second annular members being mixed upon exit therefrom, a third annular member positioned in close contact around said second annular member, said third annular member having a flange extending outwardly from the upper edge thereof for feeding propellant to the outer surface of said second annular member, and a fourth annular member positioned around the outer edges of the flanges on said first, second and third annular members, said fourth annular member having means attached thereto for feeding propellant to said annular members.
Claim 3
Dependent Claim
43 words
The propellant injector defined in claim 1 wherein the means on the outer surface of said first annular member for metering the flow of propellant thereover includes a deep-etched pattern of flow passages terminating at the lower edge of said first annular member.
Claim 4
Dependent Claim
23 words
The propellant injector defined in claim 2 wherein the propellant flowing through the passages in said first annular ring is an oxidizer agent.
Claim 5
Dependent Claim
43 words
The propellant injector defined in claim 1 wherein the means on the outer surface of said second annular member for metering the flow of propellant thereover includes a deep-etched pattern of flow passages terminating at the lower edge of said second annular member.
Claim 6
Dependent Claim
23 words
The propellant injector defined in claim 4 wherein the propellant flowing through the passages in said second annular ring is a fuel agent.
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) | 1977-04-08 | 1977-10-08 | 1978-04-09 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-04-08 | 1981-10-08 | 1982-04-09 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-04-08 | 1985-10-08 | 1986-04-09 | $7700.00 | Window Closed / Lapsed |