GB741488A - Combustion chambers for jet-propulsion engines, gas turbines and other prime movers - Google Patents
Combustion chambers for jet-propulsion engines, gas turbines and other prime moversInfo
- Publication number
- GB741488A GB741488A GB511953A GB511953A GB741488A GB 741488 A GB741488 A GB 741488A GB 511953 A GB511953 A GB 511953A GB 511953 A GB511953 A GB 511953A GB 741488 A GB741488 A GB 741488A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- flame tube
- header
- annular
- passages
- 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
-
- 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
-
- 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
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
741,488. Generating combustion products under pressure. LUCAS (INDUSTRIES), Ltd., J. April 13, 1954 [Feb. 24, 1953; April 2, 1953], Nos. 5119/53 and 9157/53. Class 51 (1). In a combustion chamber for a gas turbine engine or a jet propulsion engine comprising an annular flame tube disposed within an annular air casing, air is supplied to the flame tube and to the inner and outer air spaces respectively through passages from an annular header, the entrance to each passage being such that it extends across the whole or substantially the whole of the radial width of the header. In Figs. 1 and 4 groups of three passages e, f, g extend from the annular header a to the flame tube b and air spaces c, d, the two end passages e, f of each group leading to the outer and inner air spaces d, c respectively, and the middle passage g leading to the interior of the flame tube. The groups are separated by spacers. The upstream end of the flame tube comprises dished segments p, each of which has an air swirler q and a fuel nozzle r is disposed opposite each segment to inject fuel in an upstream direction. Air is also admitted to the flame tube through inlets s, t, u. In Fig. 6 a duct i is disposed within the annular header, the upstream end of the duct being of corrugated form. Air flowing through the duct enters the flame tube at its upstream end and air flowing through the passages j, k formed by the corrugations enters the inner and outer air spaces respectively. The invention eliminates the effects of non-uniformity of air flow in the header.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB511953A GB741488A (en) | 1953-02-24 | 1953-02-24 | Combustion chambers for jet-propulsion engines, gas turbines and other prime movers |
US433188A US2882681A (en) | 1953-02-24 | 1954-05-28 | Air-jacketed annular combustion chambers for jet-propulsion engines, gas turbines or like prime movers |
DEL23428A DE1006216B (en) | 1953-02-24 | 1955-11-15 | Annular combustion chamber for jet engines, gas turbines, etc. like. prime movers |
FR1135631D FR1135631A (en) | 1953-02-24 | 1955-11-17 | Combustion chamber for jet engine, gas turbine or other engine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB511953A GB741488A (en) | 1953-02-24 | 1953-02-24 | Combustion chambers for jet-propulsion engines, gas turbines and other prime movers |
Publications (1)
Publication Number | Publication Date |
---|---|
GB741488A true GB741488A (en) | 1955-12-07 |
Family
ID=9790071
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB511953A Expired GB741488A (en) | 1953-02-24 | 1953-02-24 | Combustion chambers for jet-propulsion engines, gas turbines and other prime movers |
Country Status (2)
Country | Link |
---|---|
FR (1) | FR1135631A (en) |
GB (1) | GB741488A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2996884A (en) * | 1959-03-11 | 1961-08-22 | Rolls Royce | Combustion chamber |
DE1217139B (en) * | 1960-09-13 | 1966-05-18 | Rolls Royce | Combustion chamber for a gas turbine plant |
DE1626040B1 (en) * | 1968-03-02 | 1971-06-24 | Lucas Industries Ltd | Annular combustion chamber for gas turbine engines |
EP0120173A1 (en) * | 1983-02-28 | 1984-10-03 | United Technologies Corporation | Diffuser for gas turbine engine |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3316714A (en) * | 1963-06-20 | 1967-05-02 | Rolls Royce | Gas turbine engine combustion equipment |
-
1953
- 1953-02-24 GB GB511953A patent/GB741488A/en not_active Expired
-
1955
- 1955-11-17 FR FR1135631D patent/FR1135631A/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2996884A (en) * | 1959-03-11 | 1961-08-22 | Rolls Royce | Combustion chamber |
DE1217139B (en) * | 1960-09-13 | 1966-05-18 | Rolls Royce | Combustion chamber for a gas turbine plant |
DE1626040B1 (en) * | 1968-03-02 | 1971-06-24 | Lucas Industries Ltd | Annular combustion chamber for gas turbine engines |
EP0120173A1 (en) * | 1983-02-28 | 1984-10-03 | United Technologies Corporation | Diffuser for gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
FR1135631A (en) | 1957-05-02 |
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