GB817418A - Combustion apparatus - Google Patents

Combustion apparatus

Info

Publication number
GB817418A
GB817418A GB15257/57A GB1525757A GB817418A GB 817418 A GB817418 A GB 817418A GB 15257/57 A GB15257/57 A GB 15257/57A GB 1525757 A GB1525757 A GB 1525757A GB 817418 A GB817418 A GB 817418A
Authority
GB
United Kingdom
Prior art keywords
conduits
flame tube
furnace
rollers
combustion chamber
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
GB15257/57A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB817418A publication Critical patent/GB817418A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/827—Sound absorbing structures or liners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for

Abstract

817,418. Generating combustion products under pressure. UNITED AIRCRAFT CORPORATION. May 14, 1957 [May 16, 1956], No. 15257/57. Class 51 (1). A combustion chamber comprises an outer casing and an inner flame tube, the flame tube being in the form of a body of revolution produced by rotation of a curved line about the axis of the flame tube, the curved line diverging from the axis in a downstream direction. The curve may be in the form of an exponential curve or in the form of a catenary. The combustion chamber shown which may be suitable for a rocket, a ram-jet unit or reheat equipment of a gas turbine jet engine, comprises an outer casing 10 and an inner flame tube 14 comprising a perforated wall in the form of a body of revolution. The upstream end of the flame tube is closed by a wall 24 and a perforated wall 26 is disposed within the flame tube downstream of the end wall 24 so as to constitute a tuned chamber therebetween. Fuel is supplied to the inflowing air by means of the injectors 20 and combustion is initiated by means of an igniter 22. The object of the invention is to eliminate high-amplitude pressure fluctuations in the combustion chamber which produce destructive screech burning. duit with zinc (see Group II) the conduits 10 (Fig. 1) roll down sloped rails 11 into screw conveyers 12, 13 which feed them into an oxidizing furnace 14 Fig. 3) and thus on to rollers 21 from whence they are conveyed through opening 22 to reducing furnace 24. Flame heaters are provided in the roof of furnace 14 and air is injected from slotted pipes 18, 19 through the conduits. Furnace 24 (Figs. 6 and 7) receives conduits on rollers 26 and arms thus feed the conduits on to screw conveyers 28, 29. Regenerating heaters 38 are provided and an atmosphere of cracked ammonia or hydrogen, pipes 39 supplying the atmosphere to the interior of the conduits. The portion of the reducing furnace to the left of partitions 44 is cooled by passing cooling gases through units 46. The conduits are removed from the furnace by rollers 48.
GB15257/57A 1956-05-16 1957-05-14 Combustion apparatus Expired GB817418A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US585296A US2865174A (en) 1956-05-16 1956-05-16 Screech reduction in combustion chambers

Publications (1)

Publication Number Publication Date
GB817418A true GB817418A (en) 1959-07-29

Family

ID=24340835

Family Applications (1)

Application Number Title Priority Date Filing Date
GB15257/57A Expired GB817418A (en) 1956-05-16 1957-05-14 Combustion apparatus

Country Status (2)

Country Link
US (1) US2865174A (en)
GB (1) GB817418A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2504601A1 (en) * 1981-04-24 1982-10-29 Rolls Royce IMPROVED BURNER FOR A GAS TURBINE ENGINE

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1590684A (en) * 1968-09-12 1970-04-20
CN102175041B (en) * 2010-12-23 2012-06-27 中国航天科技集团公司第六研究院第十一研究所 Dividing wall type regenerative cooling air oxygen alcohol torch type igniter

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2072731A (en) * 1934-12-03 1937-03-02 Steam Motors Inc Oil burner
US2543762A (en) * 1946-07-01 1951-03-06 Westinghouse Electric Corp Liquid fuel and atomizing ring for annular combustion chambers
US2568921A (en) * 1948-04-27 1951-09-25 Westinghouse Electric Corp Combustion chamber with rotating fuel nozzles
US2669090A (en) * 1951-01-13 1954-02-16 Lanova Corp Combustion chamber
US2573536A (en) * 1951-07-02 1951-10-30 Jr Albert G Bodine Engine detonation control by acoustic methods and apparatus

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2504601A1 (en) * 1981-04-24 1982-10-29 Rolls Royce IMPROVED BURNER FOR A GAS TURBINE ENGINE

Also Published As

Publication number Publication date
US2865174A (en) 1958-12-23

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