GB948128A - Combustion apparatus for jet-propulsion engines, gas turbines, or other prime movers - Google Patents
Combustion apparatus for jet-propulsion engines, gas turbines, or other prime moversInfo
- Publication number
- GB948128A GB948128A GB1050859A GB1050859A GB948128A GB 948128 A GB948128 A GB 948128A GB 1050859 A GB1050859 A GB 1050859A GB 1050859 A GB1050859 A GB 1050859A GB 948128 A GB948128 A GB 948128A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- annular
- nose piece
- combustion chambers
- vanes
- 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
- F23R3/045—Air inlet arrangements using pipes
-
- 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
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/34—Feeding into different combustion zones
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
-
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
948,128. Gas turbine combustion chambers. JOSEPH LUCAS (INDUSTRIES) Ltd. March 24, 1960 [March 26, 1959], No. 10508/59. Heading F1L. Combustion apparatus for jet propulsion engines and other prime movers comprises two concentrically arranged annular combustion chambers having a common annular outlet, an air jacket arranged surrounding both chambers and providing a common annular air inlet thereto, and vanes fixed within the inlet for directing air to the combustion chambers, the vanes being arranged to support two concentric annular fuel supply manifolds each carrying a number of angularly spaced burners and a nose piece itself serving to support the combustion chambers within the air jacket. As shown two concentric combustion chambers 23, 24, surrounded by an air jacket 10, are supported at the common outlet 26 by a pair of sheet metal rings 39 which are supported in complementary annular grooves 40 in the air jacket 10. In the inlet end of the air jacket are vanes 11 formed from a continuous strip of metal 12. The strip 12 is supported by axially extending vanes 15, 16. Secured to the vanes are annularly disposed bosses 17 to which are attached either bridge pieces 18 supporting fuel manifolds 19, 20, or the nose piece 30, which has air inlet openings 33 shaped to direct primary air to the swirlers 34 surrounding burners 22 arranged round the manifolds 15, 20. The nose piece 30 forms with the adjacent walls of the combustion chamber an annular air duct 25 through which secondary air passes via apertures 31 into the combustion chamber. Secondary air also passes from two other annular air passages, defined by the air jacket and combustion chamber walls, via apertures 32 into the combustion chambers. Secured within the nose piece are radial tubes 37 which are aligned with radial tubes 36 secured to combustion chamber extensions 35. A pin 38 passing through the tubes 36, 37 secures the combustion chamber to the nose piece. The air jacket 10 is formed in two parts, so that when the inlet end is disconnected the combustion chambers 23, 24, complete with fuel manifolds 19, 20 and the nose piece 30 are removed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1050859A GB948128A (en) | 1959-03-26 | 1959-03-26 | Combustion apparatus for jet-propulsion engines, gas turbines, or other prime movers |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB1050859A GB948128A (en) | 1959-03-26 | 1959-03-26 | Combustion apparatus for jet-propulsion engines, gas turbines, or other prime movers |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB948128A true GB948128A (en) | 1964-01-29 |
Family
ID=9969136
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB1050859A Expired GB948128A (en) | 1959-03-26 | 1959-03-26 | Combustion apparatus for jet-propulsion engines, gas turbines, or other prime movers |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB948128A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4151713A (en) * | 1977-03-15 | 1979-05-01 | United Technologies Corporation | Burner for gas turbine engine |
| EP0488557A1 (en) * | 1990-11-26 | 1992-06-03 | General Electric Company | Double dome combustor |
| FR2691235A1 (en) * | 1992-05-13 | 1993-11-19 | Snecma | Combustion chamber comprising a gas separator assembly. |
-
1959
- 1959-03-26 GB GB1050859A patent/GB948128A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4151713A (en) * | 1977-03-15 | 1979-05-01 | United Technologies Corporation | Burner for gas turbine engine |
| EP0488557A1 (en) * | 1990-11-26 | 1992-06-03 | General Electric Company | Double dome combustor |
| FR2691235A1 (en) * | 1992-05-13 | 1993-11-19 | Snecma | Combustion chamber comprising a gas separator assembly. |
| US5311743A (en) * | 1992-05-13 | 1994-05-17 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Gas separator for a combustion chamber |
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