US3832847A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Regeneratively cooled rocket combustion chamber with slots between cooling channels
Assignee: Airbus Defence and Space GmbH
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Filing: 1972-06-16
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Granted: 1974-09-03
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Expires: 1992-06-16
Abstract
Abstract A regeneratively cooled rocket combustion chamber includes a combustion chamber having a thrust nozzle with a thrust gas discharge and which includes an outer wall and and inner wall having cooling channels defined therebetween extending longitudinally which are spaced apart in a circumferential direction by radially extending slots therebetween which open into the combustion chamber and which extend at their opposite ends to the outer wall.
Inventors
- 👤 M Christl
- 👤 K Butter
- 👤 O Tuscher
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 00:29
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/42; F02K9/60; F02K9/62; F02K9/64
Claims Analysis
Total Claims: 5
Claim 1
Independent Claim
114 words
A regeneratively cooled rocket combustion chamber with a thrust nozzle, comprising an outer continuous annular rigid metal wall portion and an inner plurality of discontinuous rigid metal wall portions arranged substantially parallel to and spaced radially inwardly from said outer wall portion and extending in a complete annulus, a plurality of radially extending and circumferentially spaced rigid metal sidewall portions extending between said inner and outer wall portions, all of said wall portions being integrally formed and defining a plurality of longitudinally extending and circumferentially spaced cooling channels with a radially extending slot between each channel extending from the inner surface of said inner wall portion to the outer wall between adjacent cooling channels.
Claim 2
Dependent Claim
114 words
A regeneratively cooled rocket combustion chamber with a thrust nozzle, comprising an outer continuous annular rigid metal wall portion and an inner plurality of discontinuous rigid metal wall portions arranged substantially parallel to and spaced radially inwardly from said outer wall portion and extending in a complete annulus, a plurality of radially extending and circumferentially spaced rigid metal sidewall portions extending between said inner and outer wall portions, all of said wall portions being integrally formed and defining a plurality of longitudinally extending and circumferentially spaced cooling channels with a radially extending slot between each channel extending from the inner surface of said inner wall portion to the outer wall between adjacent cooling channels.
Claim 3
Dependent Claim
35 words
A regeneratively cooled rocket combustion chamber, according to claim 1, including a cooling medium conduit extending through the outer wall into at least one slot between the adjacent cooling channels defining a cooling medium passage.
Claim 4
Dependent Claim
41 words
A regeneratively cooled rocket combustion chamber, according to claim 1, wherein said combustion chamber includes a narrow neck thrust nozzle portion and a cooling medium passage defined through the outer wall leading into one of said slots between said cooling passages.
Claim 5
Dependent Claim
29 words
A regeneratively cooled rocket combustion chamber with thrust nozzle according to claim 1, wherein said sidewalls and said inner and outer walls are made of an electroplated metal material.
References Cited (Backward Citations)
FR1019176A
Cited
US2844939A
Cited
US3066702A
Cited
US3353359A
Cited
US3690103A
Cited
US3595023A
Cited
US3605412A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1977-09-02 | 1978-03-04 | 1978-09-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-09-02 | 1982-03-04 | 1982-09-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-09-02 | 1986-03-04 | 1986-09-03 | $7700.00 | Window Closed / Lapsed |