Patent US3595020A successfully refreshed from Google Patents.
US3595020A
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US
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Method for producing burnable gases for thrust engines
Assignee: Bolkow GmbH
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Filing: 1970-04-14
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Granted: 1971-07-27
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Expires: 1990-04-14
Abstract
Abstract Burnable gases under pressure for operating engines such as thrust engines and particular rocket and ramjet engines are produced by arranging together two solid propellant charges, one of which comprises an auxiliary propellant charge having a high thermal efficiency and the other constituting a main propellant charge comprising a material of low heat of fusion and evaporation. The auxiliary charge is ignited by a fuse device and will burn off adjacent the main charge but shielded therefrom by a burn-off insulation. The burnable gases which are produced are directed by their own pressure through a gas duct into a combustion chamber where they are admixed with an oxidizer which may be supplied under the pressure force of the gases themselves.
Inventors
- 👤 Johannes Schubert
- 👤 Rolf Fuchs
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 10:02
CPC Classifications
F; F02; F02K; F02K7/00; F02K7/10; F02K7/18; F02K9/00; F02K9/08; F02K9/10; F02K9/12; F02K9/72; Y; Y10; Y10S; Y10S60/00; Y10S60/917
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
118 words
A method for producing burnable gases under pressure for thrust engines using a combination of two solid propellant charges, comprising arranging an auxiliary propellant charge of a high thermal efficiency directly adjacent a main propulsion charge of a low heat of fusion and evaporation, igniting and burning off (stoichiometrically) the auxiliary charge in a closed chamber and in a manner to cause the main charge to become simultaneously transformed into a different state by being fused, evaporated, and sublimated without chemical change, and using the pressure of the gases generated by the burn-off of the auxiliary charge to conduct the gases formed by the combined charges to a combustion chamber for addition with an oxidizer for further combustion.
Claim 2
Independent Claim
118 words
A method for producing burnable gases under pressure for thrust engines using a combination of two solid propellant charges, comprising arranging an auxiliary propellant charge of a high thermal efficiency directly adjacent a main propulsion charge of a low heat of fusion and evaporation, igniting and burning off (stoichiometrically) the auxiliary charge in a closed chamber and in a manner to cause the main charge to become simultaneously transformed into a different state by being fused, evaporated, and sublimated without chemical change, and using the pressure of the gases generated by the burn-off of the auxiliary charge to conduct the gases formed by the combined charges to a combustion chamber for addition with an oxidizer for further combustion.
Claim 3
Dependent Claim
29 words
A method, according to claim 1, including conveying an oxidizer to the combustion chamber using the force of the gas pressure produced by the burning of the auxiliary charge.
Claim 4
Dependent Claim
26 words
A method, according to claim 1, wherein an oxidizer such as air is directed into the combustion chamber along with the gases of the combined charge.
Claim 5
Independent Claim
126 words
A method for producing burnable gases under pressure for thrust engines using a combination of a solid main propellant charge having a low heat of fusion and of evaporation and a solid auxiliary propellant charge having a high thermal efficiency, comprising arranging the auxiliary propellant charge adjacent to the main propellant charge in an enclosed space and igniting and burning off the auxiliary charge in the enclosed space and transferring the heat generated thereby to the main charge for simultaneously completely transforming the solid main charge into the gaseous state and retaining its molecular structure free of chemical change, and collecting the gases generated by the burn-off of the auxiliary charge and employing the pressure of the collected gases for conveying them into a combustion space.
Claim 6
Independent Claim
126 words
A method for producing burnable gases under pressure for thrust engines using a combination of a solid main propellant charge having a low heat of fusion and of evaporation and a solid auxiliary propellant charge having a high thermal efficiency, comprising arranging the auxiliary propellant charge adjacent to the main propellant charge in an enclosed space and igniting and burning off the auxiliary charge in the enclosed space and transferring the heat generated thereby to the main charge for simultaneously completely transforming the solid main charge into the gaseous state and retaining its molecular structure free of chemical change, and collecting the gases generated by the burn-off of the auxiliary charge and employing the pressure of the collected gases for conveying them into a combustion space.
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) | 1974-07-26 | 1975-01-25 | 1975-07-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-07-26 | 1979-01-25 | 1979-07-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-07-26 | 1983-01-25 | 1983-07-27 | $7700.00 | Window Closed / Lapsed |