GB1043020A - Improvements in or relating to liquid injection devices, for jet propulsion or rocket type power units - Google Patents
Improvements in or relating to liquid injection devices, for jet propulsion or rocket type power unitsInfo
- Publication number
- GB1043020A GB1043020A GB47394/64A GB4739464A GB1043020A GB 1043020 A GB1043020 A GB 1043020A GB 47394/64 A GB47394/64 A GB 47394/64A GB 4739464 A GB4739464 A GB 4739464A GB 1043020 A GB1043020 A GB 1043020A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pairs
- propellant
- orifices
- ducts
- alternate
- 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
- 239000007788 liquid Substances 0.000 title abstract 3
- 238000002347 injection Methods 0.000 title 1
- 239000007924 injection Substances 0.000 title 1
- 239000003380 propellant Substances 0.000 abstract 10
- 238000002485 combustion reaction Methods 0.000 abstract 6
- 239000000446 fuel Substances 0.000 abstract 2
- 230000004048 modification Effects 0.000 abstract 2
- 238000012986 modification Methods 0.000 abstract 2
- 238000000889 atomisation Methods 0.000 abstract 1
- 239000003795 chemical substances by application Substances 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
- F02K9/44—Feeding propellants
- F02K9/52—Injectors
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
1,043,020. Generating combustion products under pressure; jet propulsion plant. FRANCE, MINISTER OF ARMED FORCES. Nov. 20, 1964 [Jan. 29, 1964], No. 47394/64. Headings F1J and F1L. For injecting two propellants-a liquid fuel and a liquid combustion supporting agentinto the combustion chamber of a jet propulsion or rocket power plant, the combustion chamber wall is provided with a number of orifices which open into the chamber and which are grouped in pairs, both orifices of any pair delivering the same propellant, the orifices of any pair being disposed such that the two jets of propellant issuing therefrom meet at a point where atomization of the propellant takes place. In at least one direction, the pairs of orifices supplying the fuel alternate with those supplying the combustion supporting agent. As shown, a combustion chamber includes a cylindrical wall in which are provided three circumferential rows of pairs of orifices, the uppermost row comprising pairs 7, 8 for delivering one of the propellants and whose axes meet at points A, and pairs 12, 13 for delivering the other propellant and whose axes meet at points B. The pairs 12, 13 alternate with the pairs 7, 8. Similar pairs 7a 8a and 12a, 13a, and 7b, 8b and 12b, 13b are provided in the middle and lower rows respectively. One propellant is supplied to the pairs 7, 8 etc. through pipe 5 and a number of angularlyspaced, axially-extending ducts 6. The other propellant is supplied to the pairs 12, 13 &c. through pipe 21, annular chamber 19 and ducts 15-18. Alternatively the pairs 12, 13 &c. of each axial row may open into a common cavity in the outer surface of the cylindrical wall, each cavity communicating with the annular chamber 19. The circumferential rows of points A and B are axially aligned to give alternate axial rows A, A, A and B, B, B. In another embodiment, Fig. 3 (not shown), three circumferential rows of points A and B are axially aligned to give alternate axial rows A, B, A and B, A, B, the pairs 7, 8 &c. and the pairs 12, 13 &c. being fed with their respective propellants by two series of helical ducts, the ducts of one series alternating with the ducts of the other. A further modification, Fig. 1 (not shown), includes only one circumferential row of alternate pairs 7, 8 and 12, 13 fed with their respective propellants by two series of axially extending ducts. In a final modification, all the pairs of orifices of each row are used for injecting the same propellant.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR961921A FR1391928A (en) | 1964-01-29 | 1964-01-29 | Injector |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1043020A true GB1043020A (en) | 1966-09-21 |
Family
ID=8821965
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB47394/64A Expired GB1043020A (en) | 1964-01-29 | 1964-11-20 | Improvements in or relating to liquid injection devices, for jet propulsion or rocket type power units |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US3402552A (en) |
| DE (1) | DE1258194B (en) |
| FR (1) | FR1391928A (en) |
| GB (1) | GB1043020A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1626070B1 (en) * | 1967-11-20 | 1970-12-03 | Messerschmitt Boelkow Blohm | Rocket-type gas generator |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3748852A (en) * | 1969-12-05 | 1973-07-31 | L Cole | Self-stabilizing pressure compensated injector |
| FR2705120B1 (en) * | 1993-05-11 | 1995-08-04 | Europ Propulsion | INJECTION SYSTEM WITH CONCENTRIC SLOTS AND INJECTION ELEMENTS THEREOF. |
| DE19515879C1 (en) * | 1995-04-29 | 1996-06-20 | Daimler Benz Aerospace Ag | Coaxial injection unit for rocket combustion chambers |
| DE10054333B4 (en) * | 2000-11-02 | 2006-11-30 | Eads Space Transportation Gmbh | Combustion chamber with increased heat input into a cooling device |
| CN108457768B (en) * | 2017-08-30 | 2020-04-24 | 上海空间推进研究所 | Direct-flow cold-wall type engine combustion chamber |
| US11661907B2 (en) | 2018-10-11 | 2023-05-30 | Sierra Space Corporation | Vortex hybrid rocket motor |
| US11572851B2 (en) | 2019-06-21 | 2023-02-07 | Sierra Space Corporation | Reaction control vortex thruster system |
| US11952967B2 (en) * | 2021-08-19 | 2024-04-09 | Sierra Space Corporation | Liquid propellant injector for vortex hybrid rocket motor |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2397834A (en) * | 1942-06-08 | 1946-04-02 | Mabel J Bowman | Rocket motor |
| US2555080A (en) * | 1945-07-16 | 1951-05-29 | Daniel And Florence Guggenheim | Feeding and cooling means for continuously operated internal-combustion chambers |
| US2602290A (en) * | 1947-05-07 | 1952-07-08 | Daniel And Florence Guggenheim | Rotational fuel feed for combustion chambers |
| US2523656A (en) * | 1947-11-01 | 1950-09-26 | Daniel And Florence Guggenheim | Combustion apparatus comprising successive combustion chambers |
| US2763987A (en) * | 1953-12-11 | 1956-09-25 | Kretschmer Willi | Propellant supply systems for jet reaction motors |
| US3242668A (en) * | 1961-06-05 | 1966-03-29 | Aerojet General Co | Means for reducing rocket motor combustion chamber instability |
-
1964
- 1964-01-29 FR FR961921A patent/FR1391928A/en not_active Expired
- 1964-10-30 DE DEE28041A patent/DE1258194B/en active Pending
- 1964-11-05 US US409251A patent/US3402552A/en not_active Expired - Lifetime
- 1964-11-20 GB GB47394/64A patent/GB1043020A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1626070B1 (en) * | 1967-11-20 | 1970-12-03 | Messerschmitt Boelkow Blohm | Rocket-type gas generator |
Also Published As
| Publication number | Publication date |
|---|---|
| US3402552A (en) | 1968-09-24 |
| FR1391928A (en) | 1965-03-12 |
| DE1258194B (en) | 1968-01-04 |
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