GB650528A - Improvements in or relating to combustion apparatus - Google Patents

Improvements in or relating to combustion apparatus

Info

Publication number
GB650528A
GB650528A GB26365/49A GB2636549A GB650528A GB 650528 A GB650528 A GB 650528A GB 26365/49 A GB26365/49 A GB 26365/49A GB 2636549 A GB2636549 A GB 2636549A GB 650528 A GB650528 A GB 650528A
Authority
GB
United Kingdom
Prior art keywords
holes
divided
passing
air
tube
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
Application number
GB26365/49A
Inventor
Hugh Stanley Ellis
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Publication of GB650528A publication Critical patent/GB650528A/en
Expired legal-status Critical Current

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

Abstract

650,528. Burners. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. Nov. 3, 1947, No. 26365/49. Divided out of 650,462. [Class 75(i)] [Also in Group XII] Primary air is admitted to a combustion chamber throagh holes 5, 6, 7 and forms an annular whirl B into which gaseous or liquid fuel is injected from nozzles 16. Secondary air is admitted centrally and downstream of the whirl through a perforated cone piece 12. Air entering at A is divided by an edge 10. The part passing into the tube 4 is divided by the piece 14 into portions passing to the holes 5 and to the perforated cone piece 12. The part of the air passing outside the tube 4 is divided by a cover 11. That passing under the cover reaches holes 6 and of the rest part passes through holes 7 and part enters the end of the chamber through holes 15. Specification 650,462 is referred to.
GB26365/49A 1947-11-03 1947-11-03 Improvements in or relating to combustion apparatus Expired GB650528A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB273847X 1947-11-03

Publications (1)

Publication Number Publication Date
GB650528A true GB650528A (en) 1951-02-28

Family

ID=10258730

Family Applications (1)

Application Number Title Priority Date Filing Date
GB26365/49A Expired GB650528A (en) 1947-11-03 1947-11-03 Improvements in or relating to combustion apparatus

Country Status (3)

Country Link
CH (1) CH273847A (en)
GB (1) GB650528A (en)
NL (1) NL80817C (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2742762A (en) * 1951-05-31 1956-04-24 Ca Nat Research Council Combustion chamber for axial flow gas turbines
DE2633387A1 (en) * 1975-08-05 1977-02-24 Stal Laval Turbin Ab COMBUSTION CHAMBER FOR A GAS TURBINE
CN108006695A (en) * 2016-11-01 2018-05-08 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Method of the optimization for the premixer fuel nozzle of gas turbine

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE535905A (en) * 1954-02-23
DE1029196B (en) * 1955-10-01 1958-04-30 Messerschmitt Boelkow Blohm Annular combustion chamber for internal combustion turbines, especially aircraft internal combustion turbines
DE1097213B (en) * 1958-05-22 1961-01-12 Rolls Royce Incinerator for gas turbine engines
NL111857C (en) * 1959-04-28
GB903834A (en) * 1960-05-18 1962-08-22 Rolls Royce Combustion chamber

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2742762A (en) * 1951-05-31 1956-04-24 Ca Nat Research Council Combustion chamber for axial flow gas turbines
DE2633387A1 (en) * 1975-08-05 1977-02-24 Stal Laval Turbin Ab COMBUSTION CHAMBER FOR A GAS TURBINE
CN108006695A (en) * 2016-11-01 2018-05-08 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Method of the optimization for the premixer fuel nozzle of gas turbine
WO2018082538A1 (en) * 2016-11-01 2018-05-11 Beijing Huatsing Gas Turbine & Igcc Technology Co., Ltd Method of optimizing premix fuel nozzles for a gas turbine
CN108006695B (en) * 2016-11-01 2019-12-06 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Method of optimizing a premix fuel nozzle for a gas turbine
US11835234B2 (en) 2016-11-01 2023-12-05 Beijing Huatsing Gas Turbine & Igcc Technology Co., Ltd Method of optimizing premix fuel nozzles for a gas turbine

Also Published As

Publication number Publication date
CH273847A (en) 1951-02-28
NL80817C (en)

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