GB776106A - Improvements in or relating to combustion equipment for a turbo-jet engine - Google Patents
Improvements in or relating to combustion equipment for a turbo-jet engineInfo
- Publication number
- GB776106A GB776106A GB18998/55A GB1899855A GB776106A GB 776106 A GB776106 A GB 776106A GB 18998/55 A GB18998/55 A GB 18998/55A GB 1899855 A GB1899855 A GB 1899855A GB 776106 A GB776106 A GB 776106A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- flame tube
- vanes
- mixing device
- fuel
- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
776,106. Generating combustion products under pressure. LUMMUS CO. June 30, 1955, No. 18998/55. Class 51 (1). A combustion chamber of a gas turbine jet-propulsion engine comprises an outer casing 26 and an inner flame tube 30, an air and fuel mixing device 28 being mounted on the upstream end of the flame tube. The cylindrical wall of the air and fuel mixing device is formed with two sets of tangential vanes 38 which impart vortical flow to air entering therebetween, and fuel is introduced into the vortical air now through nozzles 40 projecting through the closed end wall of the mixing device. The mixture of fuel and air discharges through the open end 28b of the mixing device into the combustion zone 30 where ignition is caused by a spark plug 46. A second set of tangential vanes 32 is disposed around the wall of the flame tube through which secondary air flows into the flame tube. The downstream end of the flame tube passes through the outer casing 26 and is formed with a throat 16b and a sector-shaped outlet 16a. The vanes 32 may be disposed so as to give vortical flow in the same direction as the vanes 38. Further air inlets are provided at 48 and 36. In a second embodiment Fig. 5, an annular flame tube 66, 68 is disposed within an annular air casing formed by walls 10, 60. An air and fuel mixing device 72 is disposed at the upstream end of the flame tube and comprises two sets of tangential vanes 70 in the outer wall thereof which impart vortical flow to air passing therebetween. Fuel is admitted through nozzles 74 projecting through the closed end wall of the mixing device and the vortical flow of air and fuel passes through the open end 74b of the mixing device into the annular flame tube. A second set of tangential vanes 80 is disposed around the outer wall of the flame tube and imparts vortical flow to secondary air flowing therethrough. A further set of tangential vanes 82 may be disposed around the outer wall of the flame tube downstream of the vanes 80, and the vanes 82 may be disposed so as to impart flow in a direction opposite to that imparted by the vanes 80.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB18998/55A GB776106A (en) | 1955-06-30 | 1955-06-30 | Improvements in or relating to combustion equipment for a turbo-jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB18998/55A GB776106A (en) | 1955-06-30 | 1955-06-30 | Improvements in or relating to combustion equipment for a turbo-jet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB776106A true GB776106A (en) | 1957-06-05 |
Family
ID=10122028
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB18998/55A Expired GB776106A (en) | 1955-06-30 | 1955-06-30 | Improvements in or relating to combustion equipment for a turbo-jet engine |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB776106A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008095860A3 (en) * | 2007-02-06 | 2008-12-24 | Basf Se | Method for providing a gas flow comprising oxygen for the endothermic reaction of a starting flow comprising one or more hydrocarbons |
| CN111894760A (en) * | 2020-07-13 | 2020-11-06 | 潍坊联信增压器股份有限公司 | Turbojet engine capable of eliminating tail rotating vortex |
-
1955
- 1955-06-30 GB GB18998/55A patent/GB776106A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008095860A3 (en) * | 2007-02-06 | 2008-12-24 | Basf Se | Method for providing a gas flow comprising oxygen for the endothermic reaction of a starting flow comprising one or more hydrocarbons |
| US8969644B2 (en) | 2007-02-06 | 2015-03-03 | Basf Se | Method for providing an oxygen-containing gas stream for the endothermic reaction of an initial stream comprising one or more hydrocarbons |
| CN111894760A (en) * | 2020-07-13 | 2020-11-06 | 潍坊联信增压器股份有限公司 | Turbojet engine capable of eliminating tail rotating vortex |
| CN111894760B (en) * | 2020-07-13 | 2022-11-15 | 潍坊联信增压器股份有限公司 | Turbojet engine capable of eliminating tail rotating vortex |
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