GB1028465A - Method of deflecting a hot gas jet passing through a nozzle for carrying out the method - Google Patents
Method of deflecting a hot gas jet passing through a nozzle for carrying out the methodInfo
- Publication number
- GB1028465A GB1028465A GB519163A GB519163A GB1028465A GB 1028465 A GB1028465 A GB 1028465A GB 519163 A GB519163 A GB 519163A GB 519163 A GB519163 A GB 519163A GB 1028465 A GB1028465 A GB 1028465A
- Authority
- GB
- United Kingdom
- Prior art keywords
- nozzle
- liquid
- injected
- injection
- insert
- 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 abstract 9
- 238000002347 injection Methods 0.000 abstract 5
- 239000007924 injection Substances 0.000 abstract 5
- 239000007789 gas Substances 0.000 abstract 3
- 238000011144 upstream manufacturing Methods 0.000 abstract 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 abstract 1
- 238000001816 cooling Methods 0.000 abstract 1
- 238000007599 discharging Methods 0.000 abstract 1
- 239000012530 fluid Substances 0.000 abstract 1
- 229910002804 graphite Inorganic materials 0.000 abstract 1
- 239000010439 graphite Substances 0.000 abstract 1
- 229910052751 metal Inorganic materials 0.000 abstract 1
- 239000002184 metal Substances 0.000 abstract 1
- 239000011148 porous material Substances 0.000 abstract 1
- 230000035939 shock Effects 0.000 abstract 1
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 abstract 1
- 229910052721 tungsten Inorganic materials 0.000 abstract 1
- 239000010937 tungsten Substances 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/60—Steering arrangements
- F42B10/66—Steering by varying intensity or direction of thrust
- F42B10/668—Injection of a fluid, e.g. a propellant, into the gas shear in a nozzle or in the boundary layer at the outer surface of a missile, e.g. to create a shock wave in a supersonic flow
-
- 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
- F02K9/80—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
- F02K9/82—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control by injection of a secondary fluid into the rocket exhaust gases
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Nozzles (AREA)
- Physical Or Chemical Processes And Apparatus (AREA)
Abstract
1,028,465. Deflecting aircraft propulsion jets. BERTIN & CIE. Feb. 8, 1963 [Feb. 8, 1962; Jan. 15, 1963], No. 5191/63. Heading B7G. [Also in Division F1] A hot gas jet flowing in a nozzle, e.g. of a rocket engine, is deflected by injection of a liquid into the flow from the nozzle wall, the expansion of the liquid along the nozzle wall deflecting the jet. Fig. 1 is a half section through a nozzle in which liquid is injected into the boundary layer on the nozzle wall through nozzles 7 formed between two parts 4, 6 of the graphite nozzle lining. Injection may alternatively take place at or upstream of the throat 5. The fluid may be injected with an upstream component of velocity. The liquid, in the slow-moving boundary layer, has time to vaporize, decompose and/or to react with the gases of the jet, the resulting rapid expansion causing a shock wave and detachment of the flow from the nozzle wall at 12. A slow-moving wake 13 is formed. In case the liquid in the feed pipe 8 becomes heated and decomposes (in the case of a monopropellant) while liquid is not being injected, the pipe 8 may feed several smaller conduits each discharging into a nozzle 7, these smaller conduits withstanding high pressures better. The injected liquid may have been used for cooling the nozzle. A second set of injection nozzles spaced axially of the nozzle from the first set may be provided, the same or a different liquid, or a gas, being injected therethrough. The injection slots or apertures may be formed in inserts cemented into the nozzle lining, the exposed face of each insert being coated with tungsten. Such an insert may have a plurality of injection bores 39 communicating with a common plenum chamber in the insert, Fig. 11, and a second liquid may be injected through a pipe system 42. Alternatively, the insert may define a plenum chamber with the nozzle wall, and be of a porous material, e.g. sintered metal.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR887391A FR1322872A (en) | 1962-02-08 | 1962-02-08 | Method and device for deflecting the jet of a rocket |
| FR921523A FR82940E (en) | 1963-01-15 | 1963-01-15 | Method and device for deflecting the jet of a rocket |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1028465A true GB1028465A (en) | 1966-05-04 |
Family
ID=26194288
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB519163A Expired GB1028465A (en) | 1962-02-08 | 1963-02-08 | Method of deflecting a hot gas jet passing through a nozzle for carrying out the method |
Country Status (2)
| Country | Link |
|---|---|
| DE (1) | DE1240747C2 (en) |
| GB (1) | GB1028465A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1158156A2 (en) * | 2000-05-26 | 2001-11-28 | General Electric Company | Fluidic nozzle control system |
| GB2398046A (en) * | 2003-01-15 | 2004-08-11 | S & C Thermofluids Ltd | Porous nozzle arrangement |
| GB2428413A (en) * | 2005-02-24 | 2007-01-31 | Rolls Royce Plc | Fluid vectoring nozzle |
| US7658337B2 (en) | 2005-02-24 | 2010-02-09 | Rolls-Royce Plc | Fluid vectoring nozzle |
| CN104712460A (en) * | 2015-01-14 | 2015-06-17 | 北京理工大学 | Solid rocket engine with controllable thrust |
| US11629669B1 (en) * | 2019-05-31 | 2023-04-18 | Exquadrum, Inc. | Liquid monopropellant controlled solid rocket motor with aft end injection deflector |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2922576C2 (en) * | 1979-06-02 | 1982-02-18 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Jet engine with vector thrust control |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2916873A (en) * | 1958-10-22 | 1959-12-15 | Advanced Res Associates Inc | Jet deflecting apparatus |
-
1963
- 1963-02-07 DE DE1963S0083648 patent/DE1240747C2/en not_active Expired
- 1963-02-08 GB GB519163A patent/GB1028465A/en not_active Expired
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1158156A2 (en) * | 2000-05-26 | 2001-11-28 | General Electric Company | Fluidic nozzle control system |
| EP1158156A3 (en) * | 2000-05-26 | 2003-10-29 | General Electric Company | Fluidic nozzle control system |
| GB2398046A (en) * | 2003-01-15 | 2004-08-11 | S & C Thermofluids Ltd | Porous nozzle arrangement |
| GB2398046B (en) * | 2003-01-15 | 2006-07-12 | S & C Thermofluids Ltd | The use of porous surfaces with coanda effect |
| GB2428413A (en) * | 2005-02-24 | 2007-01-31 | Rolls Royce Plc | Fluid vectoring nozzle |
| GB2428413B (en) * | 2005-02-24 | 2008-02-20 | Rolls Royce Plc | Fluid vectoring nozzle |
| US7658337B2 (en) | 2005-02-24 | 2010-02-09 | Rolls-Royce Plc | Fluid vectoring nozzle |
| EP1696116A3 (en) * | 2005-02-24 | 2012-12-12 | Rolls-Royce plc | Thrust vectoring using fluid jets |
| CN104712460A (en) * | 2015-01-14 | 2015-06-17 | 北京理工大学 | Solid rocket engine with controllable thrust |
| US11629669B1 (en) * | 2019-05-31 | 2023-04-18 | Exquadrum, Inc. | Liquid monopropellant controlled solid rocket motor with aft end injection deflector |
Also Published As
| Publication number | Publication date |
|---|---|
| DE1240747C2 (en) | 1975-07-10 |
| DE1240747B (en) | 1975-07-10 |
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