GB683555A - Improvements in or relating to combustion chamber - Google Patents
Improvements in or relating to combustion chamberInfo
- Publication number
- GB683555A GB683555A GB12598/50A GB1259850A GB683555A GB 683555 A GB683555 A GB 683555A GB 12598/50 A GB12598/50 A GB 12598/50A GB 1259850 A GB1259850 A GB 1259850A GB 683555 A GB683555 A GB 683555A
- Authority
- GB
- United Kingdom
- Prior art keywords
- air
- combustion
- casing
- inlet
- plate
- 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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gas Burners (AREA)
- Air Supply (AREA)
Abstract
683,555. Generating combustion products under pressure. ELLIOTT CO. May 19, 1950 [June 2, 1949], No. 12598/50. Class 51 (i). A combustion chamber comprises a casing 1 having an air inlet 5 and an outlet 4 at one end for combustion gases, a plurality of parallel combustion tubes 15 being disposed in the casing lengthwise thereof having air inlets and burner nozzles 30. The air inlet 5 is disposed in the side wall of the casing and a plate 7 extends across the casing between the air inlet 5 and the inlet end of the casing, the plate having a plurality of openings in which the inlet ends of the combustion tubes 15 are fitted. The plate 7 also has a plurality of holes 35 and the major portion of the air from the inlet passes through the holes 35 to the inlet ends of the combustion tubes. The downstream ends of the combustion tubes are accommodated in a second plate 8 which also has openings 36 for the flow of air direct to the outlet 4, and openings 11 for the flow of air into the space 10 between the double walls of the tapered duct for cooling purposes. The combustion tubes comprise an outer shell 15 and telescopically arranged liner sections 16, 17, 18 which are spaced apart to permit air to enter the combustion zone along the length of the tube. The smallest diameter section 16 has air inlets 22 which may be adjusted by pivotally-mounted flaps. Reference has 'been directed by the Comptroller to Specification 661,864.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US96753A US2565843A (en) | 1949-06-02 | 1949-06-02 | Multiple tubular combustion chamber |
Publications (1)
Publication Number | Publication Date |
---|---|
GB683555A true GB683555A (en) | 1952-12-03 |
Family
ID=22258914
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB12598/50A Expired GB683555A (en) | 1949-06-02 | 1950-05-19 | Improvements in or relating to combustion chamber |
Country Status (2)
Country | Link |
---|---|
US (1) | US2565843A (en) |
GB (1) | GB683555A (en) |
Families Citing this family (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2885858A (en) * | 1947-12-02 | 1959-05-12 | Power Jets Res & Dev Ltd | Combustion system with mixing chamber |
US2608057A (en) * | 1949-12-24 | 1952-08-26 | A V Roe Canada Ltd | Gas turbine nozzle box |
US2673726A (en) * | 1950-08-16 | 1954-03-30 | American Mach & Foundry | Jet tobacco curer |
NL84788C (en) * | 1951-06-12 | |||
US3073583A (en) * | 1960-10-28 | 1963-01-15 | John Wood Company | Heater |
DE1224095B (en) * | 1962-07-24 | 1966-09-01 | Prvni Brnenska Strojirna Zd Y | Gas turbine combustor |
US3958922A (en) * | 1974-09-20 | 1976-05-25 | John Zink Company | Duct burner assembly |
DE2950535A1 (en) * | 1979-11-23 | 1981-06-11 | BBC AG Brown, Boveri & Cie., Baden, Aargau | COMBUSTION CHAMBER OF A GAS TURBINE WITH PRE-MIXING / PRE-EVAPORATING ELEMENTS |
DE2949388A1 (en) * | 1979-12-07 | 1981-06-11 | Kraftwerk Union AG, 4330 Mülheim | COMBUSTION CHAMBER FOR GAS TURBINES AND METHOD FOR OPERATING THE COMBUSTION CHAMBER |
CA2089302C (en) * | 1992-03-30 | 2004-07-06 | Joseph Frank Savelli | Double annular combustor |
US7631499B2 (en) * | 2006-08-03 | 2009-12-15 | Siemens Energy, Inc. | Axially staged combustion system for a gas turbine engine |
US8522555B2 (en) * | 2009-05-20 | 2013-09-03 | General Electric Company | Multi-premixer fuel nozzle support system |
US9033699B2 (en) * | 2011-11-11 | 2015-05-19 | General Electric Company | Combustor |
US20130122437A1 (en) * | 2011-11-11 | 2013-05-16 | General Electric Company | Combustor and method for supplying fuel to a combustor |
US9134023B2 (en) * | 2012-01-06 | 2015-09-15 | General Electric Company | Combustor and method for distributing fuel in the combustor |
US9341376B2 (en) * | 2012-02-20 | 2016-05-17 | General Electric Company | Combustor and method for supplying fuel to a combustor |
US9416973B2 (en) * | 2013-01-07 | 2016-08-16 | General Electric Company | Micromixer assembly for a turbine system and method of distributing an air-fuel mixture to a combustor chamber |
WO2016160010A1 (en) * | 2015-04-01 | 2016-10-06 | Siemens Energy, Inc. | Pre-mixing based fuel nozzle for use in a combustion turbine engine |
US10890329B2 (en) | 2018-03-01 | 2021-01-12 | General Electric Company | Fuel injector assembly for gas turbine engine |
US10935245B2 (en) | 2018-11-20 | 2021-03-02 | General Electric Company | Annular concentric fuel nozzle assembly with annular depression and radial inlet ports |
US11286884B2 (en) | 2018-12-12 | 2022-03-29 | General Electric Company | Combustion section and fuel injector assembly for a heat engine |
US11073114B2 (en) | 2018-12-12 | 2021-07-27 | General Electric Company | Fuel injector assembly for a heat engine |
US11156360B2 (en) | 2019-02-18 | 2021-10-26 | General Electric Company | Fuel nozzle assembly |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1801007A (en) * | 1926-09-23 | 1931-04-14 | Jezler Hubert | Production of gas jets for power purposes |
US2078956A (en) * | 1930-03-24 | 1937-05-04 | Milo Ab | Gas turbine system |
US2410450A (en) * | 1943-01-30 | 1946-11-05 | Westinghouse Electric Corp | Turbine apparatus |
US2402377A (en) * | 1943-02-09 | 1946-06-18 | Westinghouse Electric Corp | Turbine apparatus |
BE489359A (en) * | 1944-10-05 | |||
US2447482A (en) * | 1945-04-25 | 1948-08-24 | Westinghouse Electric Corp | Turbine apparatus |
-
1949
- 1949-06-02 US US96753A patent/US2565843A/en not_active Expired - Lifetime
-
1950
- 1950-05-19 GB GB12598/50A patent/GB683555A/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
US2565843A (en) | 1951-08-28 |
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