Patent US3595023A successfully refreshed from Google Patents.
US3595023A
Expired / Lapsed
US
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Rocket engine combustion chamber cooling
Assignee: Bolkow GmbH
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Filing: 1968-01-11
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Granted: 1971-07-27
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Expires: 1988-01-11
Abstract
Abstract A liquid-cooled rocket combustion chamber construction includes a thrust nozzle and is characterized by the cooling of the walls using a plurality of separate cooling circuits which are independent form each other. In one embodiment the combustion chamber includes a first or head section which comprises the combustion chamber and a convergent wall portion of the nozzle which is joined through a flange to a second or trailing section which includes a small convergent portion and the divergent portion of the nozzle. A nozzle insert is formed as a continuation of the convergent and divergent portions. At least one first cooling circuit includes a plurality of axially extending passages defined along the length of the head section and trailing section. A second circuit for cooling includes an annular inlet which is connected at the divergent trailing end of the nozzle insert and provides means for directing a fluid in counterflow arrangement along the nozzle section wall and then for directing the cooling fluid in the form of a mist into the combustion chamber at the nozzle section. Another embodiment includes three separate and independent wall coding circuits, one fluid circuit comprising means for circulating a cooling fluid in association with the walls of the combustion chamber head section and another circuit providing means for circulating fluid in association with the trailing section, and a third fluid conduit connection for the nozzle insert.
Inventors
- 👤 Karl Stockel
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 10:50
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/97; F02K9/972; F02K9/42; F02K9/60; F02K9/62; F02K9/64
Claims Analysis
Total Claims: 16
Claim 1
Independent Claim
156 words
A rocket engine combustion chamber construction comprising a housing having walls defining a substantially cylindrical head section, an intermediate converging and diverging nozzle section and a trailing section, a separate nozzle neck insert arranged in said intermediate section and forming a continuation of said head section and said trailing section and defining an interior wall of said combustion chamber, said nozzle neck insert having ends which are out of abutting contact with, and being freely expandible in axial directions independently of, said head section and said trailing section, at least one first flow circuit having a flow path in heat exchange contact with said walls at selected locations therealong for circulating a separately controlled cooling liquid in heat exchange contact with said wall in each of said head section and said trailing section, and a separate second flow circuit having a flow path in heat exchange contact with said interior wall of said nozzle neck insert.
Claim 2
Dependent Claim
156 words
A rocket engine combustion chamber construction comprising a housing having walls defining a substantially cylindrical head section, an intermediate converging and diverging nozzle section and a trailing section, a separate nozzle neck insert arranged in said intermediate section and forming a continuation of said head section and said trailing section and defining an interior wall of said combustion chamber, said nozzle neck insert having ends which are out of abutting contact with, and being freely expandible in axial directions independently of, said head section and said trailing section, at least one first flow circuit having a flow path in heat exchange contact with said walls at selected locations therealong for circulating a separately controlled cooling liquid in heat exchange contact with said wall in each of said head section and said trailing section, and a separate second flow circuit having a flow path in heat exchange contact with said interior wall of said nozzle neck insert.
Claim 3
Dependent Claim
35 words
A rocket engine combustion chamber construction according to claim 1, wherein said first flow circuit defines a flow path in heat exchange contact with the walls of both said head section and said trailing section.
Claim 4
Dependent Claim
42 words
A rocket engine combustion chamber construction according to claim 1, wherein said nozzle insert includes a converging portion adjacent said head section and a diverging portion adjacent said trailing section, said converging portion being of a greater length than said diverging portion.
Claim 5
Dependent Claim
38 words
A rocket engine combustion chamber construction according to claim 1, wherein said nozzle neck insert is made of a different material than said cylindrical head section and said trailing section, the material being a heat and chemical-resistant material.
Claim 6
Dependent Claim
252 words
A rocket engine combustion chamber construction according to claim 1, wherein said nozzle insert includes a porous wall to permit the sweat cooling of the interior of the combustion chamber by the passage of liquid from said cooling chambers through said openings. 6. A rocket engine combustion chamber comprising a housing having walls defining a first section defining a substantially cylindrical head having an intermediate converging nozzle forming wall and an end nozzle insert-mounting wall, a second section having a divergent wall defining a partial nozzle expansion section and an intermediate nozzle insert mounting wall joined to the intermediate nozzle mounting wall of said first section, means defining a plurality of first flow passages along the walls of said first and second sections, and a first fluid flow circuit connected to said first flow passages for circulating a cooling fluid through said first passages, a separate nozzle insert member secured to the intermediate nozzle insert-mounting wall defined by said first and second sections and including a converging wall aligned with and complementary to the intermediate converging wall of said first section and a divergent wall portion extending from the inner end of said nozzle insert converging wall portion and diverging outwardly into alignment with and complementary to the divergent wall portion of said second section, second means defining second fluid flow passages along the walls of said nozzle insert member, and a second separate cooling circuit connected to said second flow passages for circulating a separate cooling fluid through said second passages.
Claim 7
Dependent Claim
86 words
A rocket engine combustion chamber according to claim 6, wherein said intermediate nozzle section comprises a member made of a separate material secured to said first and second sections, said second cooling circuit including an annular inlet connected to said second cooling passages adjacent the converging end of said nozzle section and an annular discharge connected to said cooling passages adjacent the converging ends of said nozzle section, said annular discharge passage including at least one opening for discharging the cooling medium into the combustion chamber.
Claim 8
Dependent Claim
29 words
A rocket engine combustion chamber according to claim 7, including a flange secured to each of said first and second sections for securing said sections together at said flanges.
Claim 9
Dependent Claim
33 words
A rocket engine combustion chamber according to claim 7, wherein said first and second sections are arranged in overlapping abutting relationship, and means for sealing the joint between said first and second sections.
Claim 10
Dependent Claim
67 words
A rocket engine combustion chamber according to claim 6, wherein said first flow passages are divided into a first set of flow passages for cooling said second section and second set of flow passages for cooling said first section, said first fluid flow circuit associated with said first fluid flow passages comprises a separate head section cooling circuit connected to the passages adjacent said nozzle discharge section.
Claim 11
Dependent Claim
230 words
A rocket engine combustion chamber construction comprising a housing having walls defining a substantially cylindrical head section, an intermediate converging and diverging nozzle section and a trailing section, a separate nozzle neck insert arranged in said intermediate section and forming a continuation of said head section and said trailing section and defining an interior wall of said combustion chamber, said nozzle neck insert being freely expandible in axial directions independently of said head section and said trailing section, at least one first flow circuit having a flow path in heat exchange contact with said walls at selected locations therealong for circulating a separately controlled cooling liquid in heat exchange contact with said wall in each of said head section and said trailing section, a separate second flow circuit having a flow path in heat exchange contact with said interior wall of said nozzle neck insert, said cylindrical head section and said trailing section including an intermediate portion defining a nozzle insert support area, and means joining said head section and said trailing section together, said separate nozzle neck insert being carried on said nozzle support section and extendIng inwardly from said housing to define a converging and diverging nozzle section, said second flow circuits including separate means for circulating liquid in heat exchange relationship with the walls of said separate insert and for directing said liquid tangentially along said walls.
Claim 12
Dependent Claim
230 words
A rocket engine combustion chamber construction comprising a housing having walls defining a substantially cylindrical head section, an intermediate converging and diverging nozzle section and a trailing section, a separate nozzle neck insert arranged in said intermediate section and forming a continuation of said head section and said trailing section and defining an interior wall of said combustion chamber, said nozzle neck insert being freely expandible in axial directions independently of said head section and said trailing section, at least one first flow circuit having a flow path in heat exchange contact with said walls at selected locations therealong for circulating a separately controlled cooling liquid in heat exchange contact with said wall in each of said head section and said trailing section, a separate second flow circuit having a flow path in heat exchange contact with said interior wall of said nozzle neck insert, said cylindrical head section and said trailing section including an intermediate portion defining a nozzle insert support area, and means joining said head section and said trailing section together, said separate nozzle neck insert being carried on said nozzle support section and extendIng inwardly from said housing to define a converging and diverging nozzle section, said second flow circuits including separate means for circulating liquid in heat exchange relationship with the walls of said separate insert and for directing said liquid tangentially along said walls.
Claim 13
Dependent Claim
193 words
A rocket engine combustion chamber construction comprising a housing having walls defining a substantially cylindrical head section, an intermediate converging and diverging nozzle section and a trailing section, a separate nozzle neck insert arranged in said intermediate section and forming a continuation of said head section and said trailing section and defining an interior wall of said combustion chamber, said nozzle neck insert being freely expandible in axial directions independently of said head section and said trailing section, at least one first flow circuit having a flow path in heat exchange contact with said walls at selected locations therealong for circulating a separately controlled cooling liquid in heat exchange contact with said wall in each of said head section and said trailing section, a separate second flow circuit having a flow path in heat exchange contact with said interior wall of said nozzle neck insert, said nozzle neck insert including a plurality of axially extending flow passages, an annular chamber connecting said flow passages at one end and defining an inlet for cooling liquid, and an annular chamber connected to said passages at the opposite end defining a discharge for the cooling liquid.
Claim 14
Dependent Claim
193 words
A rocket engine combustion chamber construction comprising a housing having walls defining a substantially cylindrical head section, an intermediate converging and diverging nozzle section and a trailing section, a separate nozzle neck insert arranged in said intermediate section and forming a continuation of said head section and said trailing section and defining an interior wall of said combustion chamber, said nozzle neck insert being freely expandible in axial directions independently of said head section and said trailing section, at least one first flow circuit having a flow path in heat exchange contact with said walls at selected locations therealong for circulating a separately controlled cooling liquid in heat exchange contact with said wall in each of said head section and said trailing section, a separate second flow circuit having a flow path in heat exchange contact with said interior wall of said nozzle neck insert, said nozzle neck insert including a plurality of axially extending flow passages, an annular chamber connecting said flow passages at one end and defining an inlet for cooling liquid, and an annular chamber connected to said passages at the opposite end defining a discharge for the cooling liquid.
Claim 15
Dependent Claim
41 words
A rocket engine combustion chamber construction according to claim 12, wherein said annular discharge chamber has at least one opening into the combustion chamber for directing a coolant liquid into the opening along the exterior of the walls of said insert.
Claim 16
Dependent Claim
46 words
A rocket engine combustion chamber construction according to claim 12, wherein said annular discharge chamber includes an annular wall located within said combustion chamber and spaced from the wall defining the cooling passages of said insert to define a discharge slot directed into said combustion chamber.
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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 |