Patent US3802192A successfully refreshed from Google Patents.
US3802192A
Expired / Lapsed
US
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Integral rocket-ramjet with combustor plenum chamber
Assignee: United States Department of the Air Force
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Filing: 1972-10-04
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Granted: 1974-04-09
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Expires: 1992-10-04
Abstract
Abstract An integral rocket-ramjet engine, wherein a rocket fuel grain is located in the ramjet combustor, having a flow distribution plate forming a plenum chamber at the forward end of the engine to increase efficiency and stabilize the burning of the fuel during ramjet operation.
Inventors
- 👤 E Curran
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 06:35
CPC Classifications
F; F02; F02K; F02K7/00; F02K7/10; F02K7/18
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
182 words
In an integral rocket-ramjet booster having a rocket housing; a payload within said housing; a ramjet combustor within said housing; means for supplying ram air to said ramjet combustor; means for supplying fuel to said ramjet combustor; a rocket fuel grain in the ramjet combustor and nozzle means connected to said ramjet combustor; an apparatus for stabilizing the burning of the fuel in the ramjet combustor after rocket burnout; comprising: means, adjacent the front end of the fuel grain, for forming a plenum chamber at the head end of said ramjet combustor for receiving ram air and fuel means, in said plenum chamber forming means, for providing a stabilized flow of air and fuel in the ramjet combustor; said means for forming a plenum chamber comprising a wall member spaced from the forward end of said combustor; said wall member having a plurality of passages for fuel and air; said wall member having a projection adapted to fit into a central cavity in said fuel grain; said projection including means for providing a radial flow of air and fuel into said combustor.
Claim 2
Dependent Claim
182 words
In an integral rocket-ramjet booster having a rocket housing; a payload within said housing; a ramjet combustor within said housing; means for supplying ram air to said ramjet combustor; means for supplying fuel to said ramjet combustor; a rocket fuel grain in the ramjet combustor and nozzle means connected to said ramjet combustor; an apparatus for stabilizing the burning of the fuel in the ramjet combustor after rocket burnout; comprising: means, adjacent the front end of the fuel grain, for forming a plenum chamber at the head end of said ramjet combustor for receiving ram air and fuel means, in said plenum chamber forming means, for providing a stabilized flow of air and fuel in the ramjet combustor; said means for forming a plenum chamber comprising a wall member spaced from the forward end of said combustor; said wall member having a plurality of passages for fuel and air; said wall member having a projection adapted to fit into a central cavity in said fuel grain; said projection including means for providing a radial flow of air and fuel into said combustor.
Claim 3
Dependent Claim
170 words
In an integral rocket-ramjet booster having a rocket housing; a payload within said housing; a ramjet combustor within said housing; means for supplying ram air to said ramjet combustor; means for supplying fuel to said ramjet combustor; a rocket fuel grain in the ramjet combustor and nozzle means connected to said ramjet combustor; an apparatus for stabilizing the burning of the fuel in the ramjet combustor after rocket burnout; comprising: means, adjacent the front end of the fuel grain, for forming a plenum chamber at the head end of said ramjet combustor for receiving ram air and fuel and means, in said plenum chamber forming means, for providing a stabilized flow of air and fuel in the ramjet combustor; said means for forming a plenum chamber comprising a wall member spaced from the forward end of said combustor; said wall member having a plurality of passages for fuel and air; means positioned adjacent and supported by said wall member for controlling the flow of fuel and air through said passages.
Claim 4
Dependent Claim
170 words
In an integral rocket-ramjet booster having a rocket housing; a payload within said housing; a ramjet combustor within said housing; means for supplying ram air to said ramjet combustor; means for supplying fuel to said ramjet combustor; a rocket fuel grain in the ramjet combustor and nozzle means connected to said ramjet combustor; an apparatus for stabilizing the burning of the fuel in the ramjet combustor after rocket burnout; comprising: means, adjacent the front end of the fuel grain, for forming a plenum chamber at the head end of said ramjet combustor for receiving ram air and fuel and means, in said plenum chamber forming means, for providing a stabilized flow of air and fuel in the ramjet combustor; said means for forming a plenum chamber comprising a wall member spaced from the forward end of said combustor; said wall member having a plurality of passages for fuel and air; means positioned adjacent and supported by said wall member for controlling the flow of fuel and air through said passages.
Claim 5
Dependent Claim
140 words
In an integral rocket-ramjet booster having a rocket housing; a payload within said housing; a ramjet combustor within said housing; means for supplying ram air to said ramjet combustor; means for supplying fuel to said ramjet combustor; a rocket fuel grain in the ramjet combustor and nozzle means connected to said ramjet combustor; an apparatus for stabilizing the burning of the fuel in the ramjet combustor after rocket burnout; comprising: means, adjacent the front end of the fuel grain, for forming a plenum chamber at the head end of said ramjet combustor for receiving ram air and fuel and means, in said plenum chamber forming means, for providing a stabilized flow of air and fuel in the ramjet combustor; wherein the means for forming a plenum chamber includes means for providing a swirl of air and fuel in said combustor.
Claim 6
Dependent Claim
140 words
In an integral rocket-ramjet booster having a rocket housing; a payload within said housing; a ramjet combustor within said housing; means for supplying ram air to said ramjet combustor; means for supplying fuel to said ramjet combustor; a rocket fuel grain in the ramjet combustor and nozzle means connected to said ramjet combustor; an apparatus for stabilizing the burning of the fuel in the ramjet combustor after rocket burnout; comprising: means, adjacent the front end of the fuel grain, for forming a plenum chamber at the head end of said ramjet combustor for receiving ram air and fuel and means, in said plenum chamber forming means, for providing a stabilized flow of air and fuel in the ramjet combustor; wherein the means for forming a plenum chamber includes means for providing a swirl of air and fuel in said combustor.
Claim 7
Dependent Claim
145 words
In an integral rocket-ramjet booster having a rocket housing; a payload within said housing; a ramjet combustor within said housing; means for supplying ram air to said ramjet combustor; means for supplying fuel to said ramjet combustor; a rocket fuel grain in the ramjet combustor and nozzle means connected to said ramjet combustor; an apparatus for stabilizing the burning of the fuel in the ramjet combustor after rocket burnout; comprising: means, adjacent the front end of the fuel grain, for forming a plenum chamber at the head end of said ramjet combustor for receiving ram air and fuel and means, in said plenum chamber forming means, for providing a stabilizer flow of air and fuel in the ramjet combustor; said plenum chamber is an annular plenum chamber; means for providing a radial inward flow of air and fuel from said plenum chamber into the combustor.
Claim 8
Dependent Claim
145 words
In an integral rocket-ramjet booster having a rocket housing; a payload within said housing; a ramjet combustor within said housing; means for supplying ram air to said ramjet combustor; means for supplying fuel to said ramjet combustor; a rocket fuel grain in the ramjet combustor and nozzle means connected to said ramjet combustor; an apparatus for stabilizing the burning of the fuel in the ramjet combustor after rocket burnout; comprising: means, adjacent the front end of the fuel grain, for forming a plenum chamber at the head end of said ramjet combustor for receiving ram air and fuel and means, in said plenum chamber forming means, for providing a stabilizer flow of air and fuel in the ramjet combustor; said plenum chamber is an annular plenum chamber; means for providing a radial inward flow of air and fuel from said plenum chamber into the combustor.
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 |