US3910037A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Dual fuel rocket engine
Assignee: Individual
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Filing: 1973-07-30
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Granted: 1975-10-07
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Expires: 1993-07-30
Abstract
Abstract A chemical rocket engine incorporates the necessary valves, feed lines, preburners, turbopumps and injectors to enable a single combustion/thrust chamber to operate with two different propellant combinations. To increase vehicle performance in accordance with a mixed-mode propulsion principle, these two propellant combinations are burned sequentially, the combination having the higher density and higher specific impulse being preferably operated first. In one arrangement, the two combinations involved three propellants, two fuels, and a common oxidizer. In such arrangement, the first burned fuel may be kerosene or a similar hydrocarbon, the second burned fuel may be hydrogen and the common oxidizer is liquid oxygen. When oxygen is also used as the coolent for both modes of operation, then the fuel circuits may be made fully independent of each other and of the oxygen circuit, so that the engine can be assembled modularly either to operate with only one fuel or the other, as well as in a dual-fuel arrangement.
Inventors
- 👤 Robert J Salkeld
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 16:11
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/42; F02K9/44
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
126 words
A chemical rocket engine, said engine having a single thrust chamber, said engine having a first means to feed and effect combustion of a first propellant combination in said thrust chamber to effect a first mode of propulsion in the atmosphere for a sustained long time duration to effect propulsion of said engine for a substantial long distance through the atmosphere, said engine having a second means to feed and effect combustion of a second propellant combination in said thrust chamber to effect a second mode of propulsion in the atmosphere for a sustained long time duration to effecT propulsion of said engine for a substantial long distance through the atmosphere, and third means for preventing simultaneous operation of said first means and said second means.
Claim 2
Dependent Claim
126 words
A chemical rocket engine, said engine having a single thrust chamber, said engine having a first means to feed and effect combustion of a first propellant combination in said thrust chamber to effect a first mode of propulsion in the atmosphere for a sustained long time duration to effect propulsion of said engine for a substantial long distance through the atmosphere, said engine having a second means to feed and effect combustion of a second propellant combination in said thrust chamber to effect a second mode of propulsion in the atmosphere for a sustained long time duration to effecT propulsion of said engine for a substantial long distance through the atmosphere, and third means for preventing simultaneous operation of said first means and said second means.
Claim 3
Dependent Claim
27 words
A rocket engine as set forth in claim 1 in which said first and said second propellant combinations consist of two different fuels and a common oxidizer.
Claim 4
Dependent Claim
34 words
A rocket engine as set forth in claim 2 in which said engine incorporates means defining a coolant passageway, and means for moving said common oxidizer through said passageway during both modes of propulsion.
Claim 5
Dependent Claim
99 words
A rocket engine as set forth in claim 1 in which each of said propellant combinations include a fuel, a fuel circuit for each fuel of said first and said second propellant combinations, one fuel circuit being fully independent of the other, said first and said second propellant combinations including a common oxidizer, said engine incorporating an oxidizer circuit, each fuel circuit being independent of the oxidizer circuit, so that the engine may be assembled modularly to be capable of operating either with only one fuel or the other burning with the oxidizer, or as a dual fuel engine.
Claim 6
Dependent Claim
139 words
In a system of the character described wherein it is desired to enable a single rocket vehicle stage to be propelled by two different propellant combinations, the improvement which comprises engine means on said vehicle, said engine means having a single thrust chamber, first means to feed and effect combustion of a first propellant combination in said thrust chamber to effect a first mode of propulsion of said vehicle in the atmosphere for a sustained long time duration to effect propulsion of said vehicle for a substantial long distance through the atmosphere, second means to feed a second propellant combination in said thrust chamber to effect a second mode of propulsion of said vehicle in the atmosphere for a substantial long distance through the atmosphere, and means for preventing simultaneous operation of said first means and said second means.
Claim 7
Dependent Claim
139 words
In a system of the character described wherein it is desired to enable a single rocket vehicle stage to be propelled by two different propellant combinations, the improvement which comprises engine means on said vehicle, said engine means having a single thrust chamber, first means to feed and effect combustion of a first propellant combination in said thrust chamber to effect a first mode of propulsion of said vehicle in the atmosphere for a sustained long time duration to effect propulsion of said vehicle for a substantial long distance through the atmosphere, second means to feed a second propellant combination in said thrust chamber to effect a second mode of propulsion of said vehicle in the atmosphere for a substantial long distance through the atmosphere, and means for preventing simultaneous operation of said first means and said second means.
Claim 8
Dependent Claim
41 words
The improvement set forth in claim 5 in which said first and said second propellant combinations include a common oxidizer, said engine means incorporating a coolant passageway, and means for moving said oxidizer through said passageway, during both modes of propulsion.
Claim 9
Dependent Claim
100 words
The improvement as set forth in claim 5, each of such said propellant combinations include a fuel, a fuel circuit for each fuel of said first and said second propellant combinations, one fuel circuit being fully independent of the other, said first and said second propellant combinations including a common oxidizer, said engine means incorporating an oxidizer circuit, each fuel circuit being independent of the oxidizer circuit, so that the engine can be assembled modularly to be capable of operating either with only one fuel or only the other fuel burning with the oxidizer, or as a dual fuel engine.
Claim 10
Dependent Claim
25 words
The improvement set forth in claim 5 in which said first and said second propellant combinations consist of two different fuels and a common oxidizer.
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) | 1978-10-06 | 1979-04-07 | 1979-10-07 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-10-06 | 1983-04-07 | 1983-10-07 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-10-06 | 1987-04-07 | 1987-10-07 | $7700.00 | Window Closed / Lapsed |