Patent US3851468A successfully refreshed from Google Patents.
US3851468A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Apparatus for varying sealing pressures on abutting wall parts,particularly of liquid fuel rocket engines from the exterior of such engines
Assignee: Airbus Defence and Space GmbH
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Filing: 1973-09-12
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Granted: 1974-12-03
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Expires: 1993-09-12
Abstract
Abstract A device for varying the sealing pressure of a plurality of abutting wall sealing surfaces, particularly in a liquid fuel rocket engine, comprises a first wall or combustion chamber front wall which has a face with a first sealing surface directed in a direction away from the combustion chamber which is engaged by a second sealing surface which is defined on an intermediate carrier member or wall part which also has a third sealing surface on its opposite or outer face which is directed in the same direction as the first sealing surface and is in abutting engagement with a fourth sealing surface carried on a thrust piece. Ths thrust piece may be shifted in an axial direction by pressure which may be brought to bear by changing the flexure of a flexible diaphragm of a column member in order to urge the thrust member in a direction toward the intermediate wall member in the front wall of the combustion chamber. The partition wall may be operated by a threaded bolt member which bears against the partition wall to urge it in a direction toward the thrust piece. The sealing surfaces are advantageously defined between radial flow passages extending from two separate ring conduits provided for separate propellant components. Between the abutting sealing surfaces, there are defined tangentially extending conduits for the inflow of the propellant components in a whirling flow to a central swirl chamber of a nozzle aimed into the combustion chamber.
Inventors
- 👤 H Frankle
- 👤 F Schmalzriedt
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 22:18
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/42; F02K9/44; F02K9/52
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
175 words
A device for sealing the surfaces of an assembled device, particularly by pressing together the sealing surfaces forming a head of a combustion chamber in a liquid fuel rocket engine, comprising a first wall having one face with a first sealing surface, a second wall member connected to said first wall, and having one face with a second sealing surface in abutting engagement with said first sealing surface and having an opposite face at its opposite end with a third sealing surface directed in the same direction as said first sealing surface, a thrust piece having a fourth sealing surface in abutting engagement with said third sealing surface, a pressure member connected to said second wall member, and having an elastic partition wall bearing against said thrust piece in a direction to urge it toward said first wall and said wall, and means engageable with said elastic partition to bend said partition toward said thrust piece to cause tighter sealing engagement of said second and first sealing surfaces and said third and fourth sealing surfaces.
Claim 2
Independent Claim
175 words
A device for sealing the surfaces of an assembled device, particularly by pressing together the sealing surfaces forming a head of a combustion chamber in a liquid fuel rocket engine, comprising a first wall having one face with a first sealing surface, a second wall member connected to said first wall, and having one face with a second sealing surface in abutting engagement with said first sealing surface and having an opposite face at its opposite end with a third sealing surface directed in the same direction as said first sealing surface, a thrust piece having a fourth sealing surface in abutting engagement with said third sealing surface, a pressure member connected to said second wall member, and having an elastic partition wall bearing against said thrust piece in a direction to urge it toward said first wall and said wall, and means engageable with said elastic partition to bend said partition toward said thrust piece to cause tighter sealing engagement of said second and first sealing surfaces and said third and fourth sealing surfaces.
Claim 3
Dependent Claim
86 words
A device according to claim 1, wherein said pressure member comprises a bush, said second wall member comprising a carrier having a recess in which said bush is positioned, said pressure member being secured to said carrier and containing said elastic partition wall bearing against said thrust piece, said second wall member defining a central swirl nozzle and a means defining a combustion chamber extending outwardly from said swirl nozzle, said first member defining a front wall closing said combustion chamber and surrounding said swirl nozzle.
Claim 4
Dependent Claim
20 words
A device according to claim 2, wherein said combustion chamber front wall includes a central opening accommodating said swirl nozzle.
Claim 5
Dependent Claim
105 words
A device according to claim 1, wherein said first wall comprises a front wall of a combustion chamber, said second wall comprising a carrier member having a central nozzle portion extending through said front wall of said combustion chamber, said second and first sealing surfaces having grooves therein defining a ring conduit for a first propellant component and also having tangentially extending passages from said ring conduit into said swirl nozzle, said third and fourth seaLing surfaces having complimentary annular grooves defining a second ring conduit containing a second propellant component and including tangential passages extending from said second ring conduit to said swirl nozzle.
Claim 6
Dependent Claim
244 words
A liquid fuel rocket engine, comprising a tubular wall forming a combustion chamber, a combustion chamber front wall closing one end of said combustion chamber and having a central opening therethrough, said combustion chamber and wall having a first sealing surface, an intermediate carrier wall connected to said combustion chamber front wall and having a face with a second sealing surface in abutting engagement with said first sealing surface, said first and second sealing surfaces together defining an annular ring conduit for a first propellant component having at least one tangential passage therefrom leading into a swirl nozzle, said swirl nozzle being formed centrally of said carrier member and extending through the opening of said front wall, said intermediate carrier wall having an opposite face at its opposite end with a third sealing surface directed in the same direction as said first sealing surface, a thrust piece having a fourth sealing surface in abutting engagement with said third sealing surface, said carrier having a recess in the outer end thereof, a pressure member bush disposed in said recess and connected to said intermediate carrier wall, and having a partition wall at its interior bearing against said thrust piece, and means engageable with said partition wall for deflecting said wall into engagement with said thrust piece to move said thrust piece toward said combustion chamber front wall and to cause an increase in pressure on said second and first and third and fourth sealing surfaces.
Claim 7
Dependent Claim
244 words
A liquid fuel rocket engine, comprising a tubular wall forming a combustion chamber, a combustion chamber front wall closing one end of said combustion chamber and having a central opening therethrough, said combustion chamber and wall having a first sealing surface, an intermediate carrier wall connected to said combustion chamber front wall and having a face with a second sealing surface in abutting engagement with said first sealing surface, said first and second sealing surfaces together defining an annular ring conduit for a first propellant component having at least one tangential passage therefrom leading into a swirl nozzle, said swirl nozzle being formed centrally of said carrier member and extending through the opening of said front wall, said intermediate carrier wall having an opposite face at its opposite end with a third sealing surface directed in the same direction as said first sealing surface, a thrust piece having a fourth sealing surface in abutting engagement with said third sealing surface, said carrier having a recess in the outer end thereof, a pressure member bush disposed in said recess and connected to said intermediate carrier wall, and having a partition wall at its interior bearing against said thrust piece, and means engageable with said partition wall for deflecting said wall into engagement with said thrust piece to move said thrust piece toward said combustion chamber front wall and to cause an increase in pressure on said second and first and third and fourth sealing surfaces.
References Cited (Backward Citations)
No citation records indexed.
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1977-12-02 | 1978-06-03 | 1978-12-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-12-02 | 1982-06-03 | 1982-12-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-12-02 | 1986-06-03 | 1986-12-03 | $7700.00 | Window Closed / Lapsed |