US3768256A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Thrust gas generator having a combustion chamber and thrust nozzle regeneratively cooled by a liquid
Assignee: Airbus Defence and Space GmbH
•
Filing: 1970-08-12
•
Granted: 1973-10-30
•
Expires: 1990-08-12
Abstract
Abstract A thrust gas generator includes a combustion chamber and a nozzle including a converging portion terminating in a nozzle neck and a diverging outer portion extending from the neck to the thrust gas discharge. The combustion chamber proper and/or also the converging thrust nozzle part and the thrust nozzle neck comprises an inner part with a solid base wall body having cooling channels which are machined into the exterior thereof and which extend longitudinally and which include an outer wall which covers the cooling channels and which is applied by electroplating. An outer end part includes the divergent outer end of the thrust nozzle which is constructed of capillary tubes which are arranged at least over a portion of their lengths with spaces therebetween and around the longitudinal axis of the thrust nozzle and they have a constant cross section over at least a major portion of their length. A closed electroplated layer connects the tubes and it is applied firmly over a portion of the periphery of each tube and extends between the spaces of the tubes to bind the tubes into a single unit. The inner part and the outer parts are interconnected by a solid intermediate part by the electroplated layer which also covers and interconnects the tubes. The connection between the capillary tubes of the outer part and the longitudinally extending passages of the intermediate part is effected especially by soldering or welding of adjacent tube ends into the longitudinal passages in a mechanically strong and pressure-tight manner.
Inventors
- 👤 K Butter
- 👤 M Kaufmann
- 👤 H Dederra
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 12:47
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/42; F02K9/60; F02K9/62; F02K9/64; F02K9/97; F02K9/972; Y; Y10; Y10T; Y10T29/00; Y10T29/49; Y10T29/49826; Y10T29/49888
Claims Analysis
Total Claims: 18
Claim 1
Independent Claim
189 words
A thrust gas generator, particularly a liquid fueled rocket propulsion engine, comprising a tubular combustion chamber and a nozzle having a converging wall extending from said combustion chamber to a narrow nozzle neck and a diverging portion terminating in a discharge, said combustion chamber and said nozzle comprising a plurality of interengaged parts including an inner part and at least one other part, said parts together defining the whole generator, said inner part comprising at least a portion of said combustion chamber, said other part comprising at least the diverging portion of said nozzle, said inner part having an inner body wall with a plurality of circumferentially spaced radially extending longitudinal ribs defining longitudinally exTending cooling channels therebetween, said other part comprising a plurality of circumferentially arranged and circumferentially spaced tubes defining cooling passages, respective ones of said cooling passages communicating with respective ones of said cooling channels, and an electroplated layer circumferentially surrounding said tubes and bonded to the walls of said tubes and extending over said cooling channels and being bonded to the outer ends of said ribs and forming an exterior wall holding said parts together.
Claim 2
Dependent Claim
189 words
A thrust gas generator, particularly a liquid fueled rocket propulsion engine, comprising a tubular combustion chamber and a nozzle having a converging wall extending from said combustion chamber to a narrow nozzle neck and a diverging portion terminating in a discharge, said combustion chamber and said nozzle comprising a plurality of interengaged parts including an inner part and at least one other part, said parts together defining the whole generator, said inner part comprising at least a portion of said combustion chamber, said other part comprising at least the diverging portion of said nozzle, said inner part having an inner body wall with a plurality of circumferentially spaced radially extending longitudinal ribs defining longitudinally exTending cooling channels therebetween, said other part comprising a plurality of circumferentially arranged and circumferentially spaced tubes defining cooling passages, respective ones of said cooling passages communicating with respective ones of said cooling channels, and an electroplated layer circumferentially surrounding said tubes and bonded to the walls of said tubes and extending over said cooling channels and being bonded to the outer ends of said ribs and forming an exterior wall holding said parts together.
Claim 3
Dependent Claim
106 words
A thrust gas generator, according to claim 1, wherein said at least one other part includes an intermediate part and an outer part, said outer part having said tubes, and including said diverging portion of said nozzle, said intermediate part having a plurality of longitudinally extending intermediate passages corresponding to the number of said passages defined by said tubes, said intermediate part being connected to said inner part by said electroplated layer and having a plugged connection in at least some of said passages closing the communication between said passages and said cooling channels, said tubes being connected into said intermediate passages by soldering or welding.
Claim 4
Dependent Claim
60 words
A thrust gas generator, according to claim 1, wherein said tubes have a constant cross section over at least a major portion of their length and form the divergent portion of said thrust nozzle and said thrust nozzle neck, said tubes touching each other laterally only in the area of said neck at the narrowest cross section of said nozzle.
Claim 5
Dependent Claim
70 words
A thrust gas generator, according to claim 1, wherein said other part comprises said converging portion, said thrust nozzle and neck, and said diverging portion, said tubes comprising capillary tubes and having a variable cross section in the area of said convergent thrust nozzle portion, and said nozzle neck and having a constant cross section in the area extending from said thrust nozzle neck and diverging outwardly to said discharge.
Claim 6
Dependent Claim
52 words
A thrust gas generator, according to claim 1, wherein said at least one other part includes an intermediate part and an outer part said intermediate part being located between said outer part and said inner part said electroplated layer covering substantially the entire part of said intermediate part and said inner part.
Claim 7
Dependent Claim
30 words
A thrust gas generator, according to claim 4, wherein said electroplated layer in the region of said inner part is of a selected thickness comparable to the structural requirements thereof.
Claim 8
Dependent Claim
64 words
A thrust gas generator, according to claim 1, wherein said at least one other part includes an intermediate part and an outer part, said inner part and said intermediate part being connected together at their inner radial wall portions by an annular seam made by electroplating and at their radial outer wall portions by said electroplated layer in a mechanically strong and pressure-tight manner.
Claim 9
Dependent Claim
79 words
A thrust gas generator, according to claim 1, wherein said at least one other part includes an intermediate part and an outer part said intermediate part being located between said outer part and said inner part, an entrance collector ring located at the rear of said outer part and an exit collector ring located at the front of said inner part, each of said collector rings having annular passages communicating with said tubular passages and said cooling channels respectively.
Claim 10
Dependent Claim
231 words
A thrust gas generator particularly a liquid fueled rocket propulsion engine, comprising a tubular member formed of a plurality of longitudinally extending separate wall parts with a combustion chamber portion and a nozzle portion, said combustion chamber portion being of substantially uniform diameter, said nozzle portion including a converging portion, a narrow nozzle neck portion and a diverging portion terminating in a discharge proceeding from one end to the other, said tubular member comprising a first part including said combustion chamber, a converging portion of said nozzle neck and havinG an inner wall with longitudinally extending cooling channels arranged around the circumference, an intermediate part including a plurality of intermediate cooling passages arranged around the circumference in alignment with respective ones of said cooling channels and comprising a diverging portion of said nozzle, and an outer part including the remaining divergent portion of said nozzle and terminating in said discharge and having a plurality of capillary tubes extending along the length thereof arranged in spaced circumferential relationship, said first part, said intermediate part and said outer part forming the entire length of said tubular member, and an electroplated layer extending around the circumference of the entire length of said tubular member covering the tops of said channels and being bonded to said inner wall and to said tubes around a portion of the outer periphery thereof and joining said parts together.
Claim 11
Dependent Claim
231 words
A thrust gas generator particularly a liquid fueled rocket propulsion engine, comprising a tubular member formed of a plurality of longitudinally extending separate wall parts with a combustion chamber portion and a nozzle portion, said combustion chamber portion being of substantially uniform diameter, said nozzle portion including a converging portion, a narrow nozzle neck portion and a diverging portion terminating in a discharge proceeding from one end to the other, said tubular member comprising a first part including said combustion chamber, a converging portion of said nozzle neck and havinG an inner wall with longitudinally extending cooling channels arranged around the circumference, an intermediate part including a plurality of intermediate cooling passages arranged around the circumference in alignment with respective ones of said cooling channels and comprising a diverging portion of said nozzle, and an outer part including the remaining divergent portion of said nozzle and terminating in said discharge and having a plurality of capillary tubes extending along the length thereof arranged in spaced circumferential relationship, said first part, said intermediate part and said outer part forming the entire length of said tubular member, and an electroplated layer extending around the circumference of the entire length of said tubular member covering the tops of said channels and being bonded to said inner wall and to said tubes around a portion of the outer periphery thereof and joining said parts together.
Claim 12
Dependent Claim
74 words
A thrust gas generator, according to claim 9, including an entrance ring extending around said intermediate part and communicating with alternate ones of said circumferentially spaces intermediate passages, said alternate ones of said passages being plugged at the ends thereof which are adjacent said inner part, said outer part tubes being connected in circumferential progression to respective ones of said passages, said cooling channels being connected to respective circumferentially progressing passages around the periphery.
Claim 13
Dependent Claim
127 words
A thrust gas generator for liquid fueled rocket propulsion engine comprising a tubular member forming a combustion chamber and a thrust nozzle, said tubular member being formed of a plurality of longitudinally extending separate wall parts each with an inside wall portion with longitudinally extending circumferentially spaced cooling passages defined therein and including a first part with longitudinally extending tubes defining the cooling passages and a second part with circumferentially spaced radially extending longitudinally extending ribs defining exteriorly opening cooling channels therebetween forming said cooling passages, and an outer electroplated layer extending completely around the circumference of said inner wall bonded over said tubes and extending between the exterior ends of said ribs to close said channels and to form an exterior wall holding said parts together.
Claim 14
Dependent Claim
127 words
A thrust gas generator for liquid fueled rocket propulsion engine comprising a tubular member forming a combustion chamber and a thrust nozzle, said tubular member being formed of a plurality of longitudinally extending separate wall parts each with an inside wall portion with longitudinally extending circumferentially spaced cooling passages defined therein and including a first part with longitudinally extending tubes defining the cooling passages and a second part with circumferentially spaced radially extending longitudinally extending ribs defining exteriorly opening cooling channels therebetween forming said cooling passages, and an outer electroplated layer extending completely around the circumference of said inner wall bonded over said tubes and extending between the exterior ends of said ribs to close said channels and to form an exterior wall holding said parts together.
Claim 15
Dependent Claim
64 words
A thrust gas generator, according to claim 11, including an entrance collector ring duct arranged at said discharge and connected to said tubes, and an exit collector ring duct arranged at the inner end of said inner part and connected to said cooling channels, said exit collector ring duct having an inner surface substantially flush with the inner surface of the said electroplated layer.
Claim 16
Dependent Claim
66 words
A thrust gas generator, according to claim 12, wherein said inlet collector ring duct is connected around its inner periphery to said tubes, said tubes comprising bent tube elements having respective leg portions extending from said inlet collector duct ring to said inner part and being connected to respective cooling channels of said inner part said tubes being non-removably fastened to said inlet collector ring duct.
Claim 17
Dependent Claim
20 words
A thrust gas generator, according to claim 12, wherein said collector ring ducts are shrunk fit on the associated parts.
Claim 18
Dependent Claim
34 words
A thrust gas generator, according to claim 12, wherein said collector ring ducts are shrunk fitted on the associated parts and are surrounded except at their inlet and outlet openings by said electroplated layer.
References Cited (Backward Citations)
US2603593A
Cited
US2094483A
Cited
US2608529A
Cited
US2569368A
Cited
US2844939A
Cited
US3524319A
Cited
US2977754A
Cited
US3022230A
Cited
US3289943A
Cited
US3467583A
Cited
US3690103A
Cited
US3460759A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-10-29 | 1977-04-30 | 1977-10-30 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-10-29 | 1981-04-30 | 1981-10-30 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-10-29 | 1985-04-30 | 1985-10-30 | $7700.00 | Window Closed / Lapsed |