GB738219A - Combustion chambers for rocket motors - Google Patents
Combustion chambers for rocket motorsInfo
- Publication number
- GB738219A GB738219A GB1712053A GB1712053A GB738219A GB 738219 A GB738219 A GB 738219A GB 1712053 A GB1712053 A GB 1712053A GB 1712053 A GB1712053 A GB 1712053A GB 738219 A GB738219 A GB 738219A
- Authority
- GB
- United Kingdom
- Prior art keywords
- casing
- flame tube
- nozzle
- relatively cool
- cool gas
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 238000002485 combustion reaction Methods 0.000 title abstract 5
- 239000007789 gas Substances 0.000 abstract 3
- 239000003380 propellant Substances 0.000 abstract 3
- MHAJPDPJQMAIIY-UHFFFAOYSA-N Hydrogen peroxide Chemical compound OO MHAJPDPJQMAIIY-UHFFFAOYSA-N 0.000 abstract 2
- 239000003054 catalyst Substances 0.000 abstract 2
- 239000000446 fuel Substances 0.000 abstract 2
- 239000007788 liquid Substances 0.000 abstract 2
- 239000004215 Carbon black (E152) Substances 0.000 abstract 1
- 241000196324 Embryophyta Species 0.000 abstract 1
- 235000014820 Galium aparine Nutrition 0.000 abstract 1
- 240000005702 Galium aparine Species 0.000 abstract 1
- 229910000990 Ni alloy Inorganic materials 0.000 abstract 1
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 abstract 1
- 238000000354 decomposition reaction Methods 0.000 abstract 1
- 229930195733 hydrocarbon Natural products 0.000 abstract 1
- 150000002430 hydrocarbons Chemical class 0.000 abstract 1
- 238000002347 injection Methods 0.000 abstract 1
- 239000007924 injection Substances 0.000 abstract 1
- 239000000463 material Substances 0.000 abstract 1
- 239000000203 mixture Substances 0.000 abstract 1
- 230000003647 oxidation Effects 0.000 abstract 1
- 238000007254 oxidation reaction Methods 0.000 abstract 1
- 239000001301 oxygen Substances 0.000 abstract 1
- 229910052760 oxygen Inorganic materials 0.000 abstract 1
- 230000001681 protective effect Effects 0.000 abstract 1
- 238000009834 vaporization Methods 0.000 abstract 1
- 230000008016 vaporization Effects 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/68—Decomposition chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/62—Combustion or thrust chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Hydrogen, Water And Hydrids (AREA)
Abstract
738,219. Jet propulsion plant. DE HAVILLAND ENGINE CO., Ltd., HALFORD, F. B., and CLEAVER, A. V. April 27, 1954 [June 19, 1953], No. 17120/53. Class 110 (3). [Also in Group XII] A combustion chamber for a rocket motor of the kind which employs two or more normally non-gaseous propellants comprises a casing 10 and an inner flame tube 15, a relatively cool gas produced by decomposition or vaporization or partial combustion of a liquid propellant passing through the annular space 14 between the flame tube and the casing. The casing is formed with a convergent-divergent nozzle 13, and a circular catalyst element 12 and liquid fuel injection nozzle 11 are provided at the other end of the chamber. The flame tube comprises four thin-walled cylindrical sleeves 16, 17, 18, 19 which are spaced apart where they overlap to provide inlets 20 for the entry of relatively cool gas into the combustion space 24. The flame tube is supported within the casing by radial pm 9 22 and a perforated flange 23. In the combustion chamber shown, the propellants comprise a hydro-carbon fuel which is injected through the nozzle 11 and concentrated hydrogen peroxide which is passed through the catalyst element 12 to form a gasoeus mixture of steam and oxygen at a temperature of about 600 C. Some relatively cool gas issues through the perforated flange 23 to form a protective boundary layer at the throat of the nozzle. The casing is capable of withstanding the internal pressure while the flame tube is formed of heat- and oxidation-resistant material such as nickel-alloy.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1712053A GB738219A (en) | 1953-06-19 | 1953-06-19 | Combustion chambers for rocket motors |
| CH330270D CH330270A (en) | 1953-06-19 | 1955-01-31 | Rocket motor |
| FR1118997D FR1118997A (en) | 1953-06-19 | 1955-02-09 | Rocket engine combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1712053A GB738219A (en) | 1953-06-19 | 1953-06-19 | Combustion chambers for rocket motors |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB738219A true GB738219A (en) | 1955-10-12 |
Family
ID=10089623
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1712053A Expired GB738219A (en) | 1953-06-19 | 1953-06-19 | Combustion chambers for rocket motors |
Country Status (3)
| Country | Link |
|---|---|
| CH (1) | CH330270A (en) |
| FR (1) | FR1118997A (en) |
| GB (1) | GB738219A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3017745A (en) * | 1956-08-31 | 1962-01-23 | Napier & Son Ltd | Fuel supply systems for rocket engines |
| DE1152851B (en) * | 1958-12-15 | 1963-08-14 | Snecma | Combustion process for use in combustion chambers of jet engines or rockets and jet engine or rocket to carry out the process |
| CN113217949A (en) * | 2021-05-20 | 2021-08-06 | 西安航天动力研究所 | Combustion chamber diverging and cooling structure and ramjet combustion chamber |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2652615B1 (en) * | 1989-10-04 | 1992-02-07 | Europ Propulsion | PROPELLER COMBUSTION CHAMBER. |
-
1953
- 1953-06-19 GB GB1712053A patent/GB738219A/en not_active Expired
-
1955
- 1955-01-31 CH CH330270D patent/CH330270A/en unknown
- 1955-02-09 FR FR1118997D patent/FR1118997A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3017745A (en) * | 1956-08-31 | 1962-01-23 | Napier & Son Ltd | Fuel supply systems for rocket engines |
| DE1152851B (en) * | 1958-12-15 | 1963-08-14 | Snecma | Combustion process for use in combustion chambers of jet engines or rockets and jet engine or rocket to carry out the process |
| CN113217949A (en) * | 2021-05-20 | 2021-08-06 | 西安航天动力研究所 | Combustion chamber diverging and cooling structure and ramjet combustion chamber |
Also Published As
| Publication number | Publication date |
|---|---|
| CH330270A (en) | 1958-05-31 |
| FR1118997A (en) | 1956-06-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US2735263A (en) | charshafian | |
| GB1149966A (en) | Improvements in liquid propellant rocket propulsion equipment | |
| GB836088A (en) | Improvements in turbojet engine afterburners | |
| US3588298A (en) | Detonation wave combustion | |
| GB1303123A (en) | ||
| GB904142A (en) | Improvements in or relating to gas-turbine engines | |
| GB738219A (en) | Combustion chambers for rocket motors | |
| GB741836A (en) | Combustion chambers for jet-propulsion engines, gas turbines or other prime movers | |
| GB887328A (en) | Improvements in or relating to rotary internal combustion engines | |
| GB1435083A (en) | Gas turbine engine combustion equipment | |
| US2978868A (en) | Concentric combustion system with cooled dividing partition | |
| US2482262A (en) | Steam production in jacketed combustion chambers | |
| GB736823A (en) | Engine combustion chambers | |
| GB1089055A (en) | Combined combustion chamber and propulsive unit for a rocket engine | |
| GB853495A (en) | Improvements in or relating to liquid propellent rocket motors | |
| US2952122A (en) | Fuel system for ducted rocket ramjet power plants | |
| US3345822A (en) | Burning rate control of solid propellants | |
| GB1329803A (en) | Gas generator and method of operation | |
| GB876186A (en) | High output power plant, for example, rocket engines | |
| GB891826A (en) | Improvements relating to flame-supporting devices for combustion chambers | |
| WO2021091613A3 (en) | Staged combustion liquid rocket engine cycle with the turbopump unit and preburner integrated into the structure of the combustion chamber | |
| US3312067A (en) | Jet propulsion unit | |
| GB741488A (en) | Combustion chambers for jet-propulsion engines, gas turbines and other prime movers | |
| GB998819A (en) | An injector head for a liquid fuel rocket | |
| GB763962A (en) | Rocket motors |