GB673629A - Improvements relating to supersonic combustion chambers - Google Patents
Improvements relating to supersonic combustion chambersInfo
- Publication number
- GB673629A GB673629A GB12561/51A GB1256151A GB673629A GB 673629 A GB673629 A GB 673629A GB 12561/51 A GB12561/51 A GB 12561/51A GB 1256151 A GB1256151 A GB 1256151A GB 673629 A GB673629 A GB 673629A
- Authority
- GB
- United Kingdom
- Prior art keywords
- mixture
- shock wave
- fuel
- supersonic
- duct
- 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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
Abstract
673,629. Generating combustion products under pressure. OFFICE NATIONAL D'ETUDES & DE RECHERCHES AERONAUTIQUES. Nov. 8, 1948 [May 7, 1948], No. 12561/51. Divided.out of 673,536. Class 51 (i). [Also in Group XI] In a combustion chamber in which a mixture of fuel and air flows at supersonic speed, the mixture is ignited by artificially producing a shock wave in the stream. In the arrangement shown, the fuel is injected into the air stream from a nozzle 2 and mixed therewith by a shock wave O<SP>1</SP>, as described in Specification 673,636. The speed of the fuel-air mixture is then accelerated to supersonic in a duct 3 and the mixture ignited by a shock wave O<SP>2</SP> created by the leading edge of the duct 5. An arrangement, in which the shock wave O<SP>1</SP> is dispensed with, for use with atomized fuels or explosives, or the inflammable mixture consists chiefly of oxygen and hydrogen, alcohol or other combustible organic compound, is also described.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR673629X | 1948-05-07 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB673629A true GB673629A (en) | 1952-06-11 |
Family
ID=9018235
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB12561/51A Expired GB673629A (en) | 1948-05-07 | 1948-11-08 | Improvements relating to supersonic combustion chambers |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB673629A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1095302B (en) * | 1951-09-13 | 1960-12-22 | Georges Ilune | Liquid heater with an axial combustion chamber, which is surrounded by two concentric annular chambers with a narrow passage cross-section for the liquid to be heated |
| US3340690A (en) * | 1963-10-04 | 1967-09-12 | Garrett Corp | Boundary layer control for detonation ramjets |
| DE1751369B1 (en) * | 1967-05-22 | 1971-12-16 | Sanitized Ag | Device for detoxifying the exhaust gases of an internal combustion engine |
-
1948
- 1948-11-08 GB GB12561/51A patent/GB673629A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1095302B (en) * | 1951-09-13 | 1960-12-22 | Georges Ilune | Liquid heater with an axial combustion chamber, which is surrounded by two concentric annular chambers with a narrow passage cross-section for the liquid to be heated |
| US3340690A (en) * | 1963-10-04 | 1967-09-12 | Garrett Corp | Boundary layer control for detonation ramjets |
| DE1751369B1 (en) * | 1967-05-22 | 1971-12-16 | Sanitized Ag | Device for detoxifying the exhaust gases of an internal combustion engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| GB627832A (en) | Improvement in propulsion plant comprising a gas turbine driven airscrew | |
| GB680371A (en) | Reheater for jet propulsion engines | |
| GB736699A (en) | Pulsating torch igniter for combustion chambers | |
| GB1037287A (en) | Hot gas generating installation | |
| GB579424A (en) | Improvements relating to liquid fuel combustion apparatus for generating gases for power purposes | |
| GB577865A (en) | Liquid-fuel combustion-chamber | |
| GB673629A (en) | Improvements relating to supersonic combustion chambers | |
| GB895015A (en) | Improvements in or relating to jet propulsion devices | |
| GB774059A (en) | Improvements in or relating to combined gas turbine plant and ram-jet units | |
| GB1524217A (en) | Combustion chamber for a gas turbine engine | |
| GB648699A (en) | Improvements in or relating to gas-turbine engine fuel systems and liquid fuel injectors therefor | |
| GB699166A (en) | Improvements in or relating to gas turbine plants | |
| GB911125A (en) | Improvements in or relating to precombustion chamber-torch ignition in internal combustion engines | |
| GB661498A (en) | Improvements in or relating to combustion chambers, particularly for gas turbines | |
| GB838326A (en) | Method and means for control of combustion in internal combustion engines | |
| GB673536A (en) | Improvements relating to supersonic combustion | |
| GB885908A (en) | Improvements in intakes for compressible fluids | |
| GB706924A (en) | Improvements in or relating to aircraft | |
| GB578261A (en) | Improvements in or relating to ignition devices for combustion chambers | |
| GB691302A (en) | Devices for deflecting a fluid flow and applications thereof | |
| GB576545A (en) | Improvements relating to combustion chambers for prime movers | |
| GB632506A (en) | Improvements in or relating to fuel-injection nozzles and gas-turbine fuel-systems | |
| GB617353A (en) | Improvements in jet propulsion plant | |
| GB583549A (en) | Improvements in or relating to blast propulsion | |
| GB699471A (en) | Rocket apparatus |