GB806349A - Improvements relating to combustion chambers - Google Patents
Improvements relating to combustion chambersInfo
- Publication number
- GB806349A GB806349A GB28163/56A GB2816356A GB806349A GB 806349 A GB806349 A GB 806349A GB 28163/56 A GB28163/56 A GB 28163/56A GB 2816356 A GB2816356 A GB 2816356A GB 806349 A GB806349 A GB 806349A
- Authority
- GB
- United Kingdom
- Prior art keywords
- segment
- shroud portion
- segments
- combustion
- air
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
806,349. Generating combustion products under pressure. GENERAL ELECTRIC CO. Sept. 14, 1956 [Sept. 15, 1955], No. 28163/56. Class 51 (1). Combustion equipment for a gas turbine engine comprises an outer casing and an inner flame tube 4, the flame tube having an end cap 1 comprising a part-spherical annular shroud portion 13 defining ports 15 for the metering of air therethrough, and two coaxial annular segments 16, 17 of different mean diameters mounted within the shroud portion in partly overlapping relation. The segments are resiliently connected together by means of flexible metal connectors 19 and the smaller segment 17 is disposed upstream of the larger segment 16. The outer edge of the segment 16 is in slidable contact with the shroud portion 13 while the smaller segment 17 is resiliently connected to the shroud portion 13 by means of a ring member 21 secured by welding to the segment 17 and by means of clips 22 to the shroud. A fuel nozzle mounting ring 23 is secured to the inner edge of the smaller segment 17. The outer segment 16 has a plurality of louvres 25 in staggered formation in concentric rows therein for directing combustion air into the combustion space in a generally circumferential direction from the space between the shroud portion and the larger segment. The segments 16, 17 in the embodiment shown are each of frusto-conical form and the louvres in the segment 16 have arcuate slits arranged in a generally radial direction. The nozzle mounting ring 23 is formed with recesses 24 in its inner periphery so as to provide passages for the flow of cooling air over the nozzle. Air also flows radially inwardly through the annular gap 18 between the segments 16, 17. U.S.A. Specification 2,801,134 is referred to. Reference has been directed, by the Comptroller to Specification 677,602.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US534455A US2840989A (en) | 1955-09-15 | 1955-09-15 | End cap for combustor |
Publications (1)
Publication Number | Publication Date |
---|---|
GB806349A true GB806349A (en) | 1958-12-23 |
Family
ID=24130111
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB28163/56A Expired GB806349A (en) | 1955-09-15 | 1956-09-14 | Improvements relating to combustion chambers |
Country Status (4)
Country | Link |
---|---|
US (1) | US2840989A (en) |
CH (1) | CH351800A (en) |
DE (1) | DE1043719B (en) |
GB (1) | GB806349A (en) |
Families Citing this family (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2990108A (en) * | 1957-03-04 | 1961-06-27 | Curtiss Wright Corp | Compressor with annular discharge diffuser |
US3316714A (en) * | 1963-06-20 | 1967-05-02 | Rolls Royce | Gas turbine engine combustion equipment |
US3391535A (en) * | 1966-08-31 | 1968-07-09 | United Aircraft Corp | Burner assemblies |
US3916619A (en) * | 1972-10-30 | 1975-11-04 | Hitachi Ltd | Burning method for gas turbine combustor and a construction thereof |
US4077205A (en) * | 1975-12-05 | 1978-03-07 | United Technologies Corporation | Louver construction for liner of gas turbine engine combustor |
US4199936A (en) * | 1975-12-24 | 1980-04-29 | The Boeing Company | Gas turbine engine combustion noise suppressor |
US4365470A (en) * | 1980-04-02 | 1982-12-28 | United Technologies Corporation | Fuel nozzle guide and seal for a gas turbine engine |
JPS5966619A (en) * | 1982-10-06 | 1984-04-16 | Hitachi Ltd | Gas turbine combustor |
US4848081A (en) * | 1988-05-31 | 1989-07-18 | United Technologies Corporation | Cooling means for augmentor liner |
US5407133A (en) * | 1989-12-26 | 1995-04-18 | United Technologies Corporation | Cooled thin metal liner |
US5129231A (en) * | 1990-03-12 | 1992-07-14 | United Technologies Corporation | Cooled combustor dome heatshield |
US5077969A (en) * | 1990-04-06 | 1992-01-07 | United Technologies Corporation | Cooled liner for hot gas conduit |
US7260936B2 (en) * | 2004-08-27 | 2007-08-28 | Pratt & Whitney Canada Corp. | Combustor having means for directing air into the combustion chamber in a spiral pattern |
US8171736B2 (en) * | 2007-01-30 | 2012-05-08 | Pratt & Whitney Canada Corp. | Combustor with chamfered dome |
FR2948988B1 (en) * | 2009-08-04 | 2011-12-09 | Snecma | TURBOMACHINE COMBUSTION CHAMBER COMPRISING ENHANCED AIR INLET ORIFICES |
JP2011102669A (en) * | 2009-11-10 | 2011-05-26 | Mitsubishi Heavy Ind Ltd | Gas turbine combustor and gas turbine |
CN103930218B (en) | 2011-10-27 | 2017-08-29 | 固瑞克明尼苏达有限公司 | Sprayer fluid feed system with collapsible bushing pipe |
WO2013063294A1 (en) | 2011-10-27 | 2013-05-02 | Graco Minnesota Inc. | Melter cartridge |
DE102013221286B4 (en) | 2013-10-21 | 2021-07-29 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Combustion chamber, in particular gas turbine combustion chamber, e.g. B. for an aircraft engine |
US9796492B2 (en) | 2015-03-12 | 2017-10-24 | Graco Minnesota Inc. | Manual check valve for priming a collapsible fluid liner for a sprayer |
TW202110541A (en) | 2019-05-31 | 2021-03-16 | 美商葛萊兒明尼蘇達股份有限公司 | Handheld fluid sprayer |
US11920790B2 (en) * | 2021-11-03 | 2024-03-05 | General Electric Company | Wavy annular dilution slots for lower emissions |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE478436A (en) * | 1943-09-03 | 1948-01-31 | Gen Electric | |
US2458497A (en) * | 1945-05-05 | 1949-01-11 | Babcock & Wilcox Co | Combustion chamber |
FR962862A (en) * | 1946-10-26 | 1950-06-22 | ||
US2657531A (en) * | 1948-01-22 | 1953-11-03 | Gen Electric | Wall cooling arrangement for combustion devices |
US2547619A (en) * | 1948-11-27 | 1951-04-03 | Gen Electric | Combustor with sectional housing and liner |
GB677602A (en) * | 1950-03-24 | 1952-08-20 | British Thomson Houston Co Ltd | Improvements in and relating to fluid fuel combustion chambers |
US2555965A (en) * | 1950-03-24 | 1951-06-05 | Gen Electric | End cap for fluid fuel combustors |
-
1955
- 1955-09-15 US US534455A patent/US2840989A/en not_active Expired - Lifetime
-
1956
- 1956-08-31 DE DEG20440A patent/DE1043719B/en active Pending
- 1956-09-14 GB GB28163/56A patent/GB806349A/en not_active Expired
- 1956-09-14 CH CH351800D patent/CH351800A/en unknown
Also Published As
Publication number | Publication date |
---|---|
CH351800A (en) | 1961-01-31 |
US2840989A (en) | 1958-07-01 |
DE1043719B (en) | 1958-11-13 |
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