GB621438A - Improvements relating to combustion equipment for gas-turbine-engines - Google Patents
Improvements relating to combustion equipment for gas-turbine-enginesInfo
- Publication number
- GB621438A GB621438A GB548847A GB548847A GB621438A GB 621438 A GB621438 A GB 621438A GB 548847 A GB548847 A GB 548847A GB 548847 A GB548847 A GB 548847A GB 621438 A GB621438 A GB 621438A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- perforations
- section
- admitted
- engines
- 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
- F23R3/06—Arrangement of apertures along the flame tube
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
Abstract
621,438. Gas turbine combustion chambers. OULIANOFF, G. Feb. 25, 1947, No. 5488. [Class 51 (i)] The diameter of a flame tube increases at the junctions of the sections 2a, 2b, 2c and the sections are joined by flanged rings 20 which are perforated at 22. Air passing through these perforations provides a layer of cooler air against the flame tube wall. Primary air is admitted through perforations 14 in an entry end wall. Secondary air is admitted through perforations 16, 19. The outer air casing comprises a cast metal section 1a, connected to an air-inlet 5 by a spherical joint 4, and a sheet metal section 1b having a flange 9 bolted to the section 1a. The cross-section of the air duct is substantially constant, or it -may decrease from the inlet to the outlet.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB548847A GB621438A (en) | 1947-02-25 | 1947-02-25 | Improvements relating to combustion equipment for gas-turbine-engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB548847A GB621438A (en) | 1947-02-25 | 1947-02-25 | Improvements relating to combustion equipment for gas-turbine-engines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB621438A true GB621438A (en) | 1949-04-08 |
Family
ID=9797142
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB548847A Expired GB621438A (en) | 1947-02-25 | 1947-02-25 | Improvements relating to combustion equipment for gas-turbine-engines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB621438A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2699648A (en) * | 1950-10-03 | 1955-01-18 | Gen Electric | Combustor sectional liner structure with annular inlet nozzles |
US2795930A (en) * | 1951-12-06 | 1957-06-18 | A V Roe Canada Ltd | Joint construction for combustion chamber casings |
US2807934A (en) * | 1951-12-06 | 1957-10-01 | A V Roe Canada Ltd | Flame tube support for a gas turbine combustion system |
US3978664A (en) * | 1974-12-20 | 1976-09-07 | United Technologies Corporation | Gas turbine engine diffuser |
-
1947
- 1947-02-25 GB GB548847A patent/GB621438A/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2699648A (en) * | 1950-10-03 | 1955-01-18 | Gen Electric | Combustor sectional liner structure with annular inlet nozzles |
US2795930A (en) * | 1951-12-06 | 1957-06-18 | A V Roe Canada Ltd | Joint construction for combustion chamber casings |
US2807934A (en) * | 1951-12-06 | 1957-10-01 | A V Roe Canada Ltd | Flame tube support for a gas turbine combustion system |
US3978664A (en) * | 1974-12-20 | 1976-09-07 | United Technologies Corporation | Gas turbine engine diffuser |
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