GB953060A - Gas turbine engines - Google Patents
Gas turbine enginesInfo
- Publication number
- GB953060A GB953060A GB1749960A GB1749960A GB953060A GB 953060 A GB953060 A GB 953060A GB 1749960 A GB1749960 A GB 1749960A GB 1749960 A GB1749960 A GB 1749960A GB 953060 A GB953060 A GB 953060A
- Authority
- GB
- United Kingdom
- Prior art keywords
- flame tube
- troughs
- angularly
- spaced
- walls
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
Abstract
953,060. Gas turbine engine combustion equipment. JOSEPH LUCAS (INDUSTRIES) Ltd. May 12,1961 [May 18, 1960], No. 17499/60. Heading F1L. Combustion equipment for a gas turbine engine comprises an annular air casing 3 within which is disposed an annular flame tube 5, downstream end portions of the flame tube walls being recessed at angularly-spaced positions to afford trough members which extend radially at least to the centre of the flame tube section, the troughs in the inner and outer walls respectively being angularly spaced from one another and the side walls of the troughs being apertured so as to allow air to enter the flame tube in a circumferential direction. The radiallyextending troughs are shown at 14 each being formed by a pair of substantially parallel side walls and by a curved bottom wall. Each trough is closed at its downstream end and the side walls are formed with apertures 17 for entry of dilution air into the flame tube. The downstream portions 16 of the flame tube walls are formed of overlapping sections which are spaced apart to form inlets for cooling air. Primary air enters the flame tube through angularly-spaced inlets 8 and swirl devices 7, and fuel is supplied through injectors 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1749960A GB953060A (en) | 1960-05-18 | 1960-05-18 | Gas turbine engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1749960A GB953060A (en) | 1960-05-18 | 1960-05-18 | Gas turbine engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB953060A true GB953060A (en) | 1964-03-25 |
Family
ID=10096253
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1749960A Expired GB953060A (en) | 1960-05-18 | 1960-05-18 | Gas turbine engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB953060A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3242674A (en) * | 1961-05-05 | 1966-03-29 | Lucas Industries Ltd | Liquid fuel combustion apparatus |
| US5465572A (en) * | 1991-03-11 | 1995-11-14 | General Electric Company | Multi-hole film cooled afterburner cumbustor liner |
-
1960
- 1960-05-18 GB GB1749960A patent/GB953060A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3242674A (en) * | 1961-05-05 | 1966-03-29 | Lucas Industries Ltd | Liquid fuel combustion apparatus |
| US5465572A (en) * | 1991-03-11 | 1995-11-14 | General Electric Company | Multi-hole film cooled afterburner cumbustor liner |
| US5483794A (en) * | 1991-03-11 | 1996-01-16 | General Electric Company | Multi-hole film cooled afterburner combustor liner |
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