GB742990A - Combustion chamber for gas turbines - Google Patents
Combustion chamber for gas turbinesInfo
- Publication number
- GB742990A GB742990A GB2511352A GB2511352A GB742990A GB 742990 A GB742990 A GB 742990A GB 2511352 A GB2511352 A GB 2511352A GB 2511352 A GB2511352 A GB 2511352A GB 742990 A GB742990 A GB 742990A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- axial
- flame tube
- fuel injector
- air inlet
- 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
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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
742,990. Generating combustion products under pressure. SHELL REFINING & MARKETING CO., Ltd. Oct. 5, 1953 [Oct. 7, 1952], No. 25113/52. Class 51 (1). In an air jacketed type of combustion chamber for a gas turbine engine, combustion air is admitted to the flame tube through an inner swirler 18 which surrounds the fuel injector 11 through an axial air inlet 20<SP>1</SP> and through an outer swirler 21 which surrounds the axial air inlet. The flame tube comprises the cylindrical portions 5, 6 connected by the frusto-conical portion 7 and is contained in an outer casing 8 to which air is supplied through the duct 12, air entering the flame tube wall through apertures 13. The downstream end of the fuel injector is covered by a shroud 14 which permits a flow of cooling air over the burner tip. An intermediate cylindrical wall 17 is disposed between the fuel injector 11 and the wall 5 and is surrounded by a shroud 19 having apertures 20 at its upstream end, this forming the axial air inlet 20<SP>1</SP>. The axial position of the injector may be adjusted. A shutter may be provided for restricting the air flow to the outer swirler 21 when the fuel supply is reduced and may comprise a rotatable apertured ring cooperating with a fixed apertured ring. The air swirlers 18, 21 preferably impart swirl in opposed directions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2511352A GB742990A (en) | 1952-10-07 | 1952-10-07 | Combustion chamber for gas turbines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2511352A GB742990A (en) | 1952-10-07 | 1952-10-07 | Combustion chamber for gas turbines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB742990A true GB742990A (en) | 1956-01-04 |
Family
ID=10222420
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2511352A Expired GB742990A (en) | 1952-10-07 | 1952-10-07 | Combustion chamber for gas turbines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB742990A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0550218A1 (en) * | 1991-12-30 | 1993-07-07 | General Electric Company | Gas turbine combustors |
-
1952
- 1952-10-07 GB GB2511352A patent/GB742990A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0550218A1 (en) * | 1991-12-30 | 1993-07-07 | General Electric Company | Gas turbine combustors |
| US5253478A (en) * | 1991-12-30 | 1993-10-19 | General Electric Company | Flame holding diverging centerbody cup construction for a dry low NOx combustor |
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