GB731739A - Burners for use with rocket motors - Google Patents

Burners for use with rocket motors

Info

Publication number
GB731739A
GB731739A GB571553A GB571553A GB731739A GB 731739 A GB731739 A GB 731739A GB 571553 A GB571553 A GB 571553A GB 571553 A GB571553 A GB 571553A GB 731739 A GB731739 A GB 731739A
Authority
GB
United Kingdom
Prior art keywords
plates
holes
supplied
oxidizer
fuel
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
GB571553A
Inventor
Reginald Dennis Lowe
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.)
Sir WG Armstrong Whitworth and Co Engineers Ltd
Sir WG Armstrong Whitworth Aircraft Ltd
Original Assignee
Sir WG Armstrong Whitworth and Co Engineers Ltd
Sir WG Armstrong Whitworth Aircraft 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 Sir WG Armstrong Whitworth and Co Engineers Ltd, Sir WG Armstrong Whitworth Aircraft Ltd filed Critical Sir WG Armstrong Whitworth and Co Engineers Ltd
Priority to GB571553A priority Critical patent/GB731739A/en
Publication of GB731739A publication Critical patent/GB731739A/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
    • 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
    • F02K9/44—Feeding propellants
    • F02K9/52—Injectors

Abstract

731,739. Rocket motors. ARMSTRONG WHITWORTH AIRCRAFT Ltd. Sir W. G. Dec. 18, 1953 [March 2, 1953], No. 5715/53. Class 110 (3). [Also in Group XII] In a rocket motor which operates with a fuel and an oxidizer as the propellant ingredients, the ingredients are supplied through a spray device comprising two spaced coaxial metal plates 11, 12 secured together at a number of points, at least one of the plates 11 being secured directly or indirectly near its outer edge 'to the combustion chamber 16 of the rocket motor to form the end wall thereof. One of the propellant ingredients, say the fuel, is supplied to the chamber from a space 20 outside the other plate 12 through holes 21 formed at the points where the two plates are secured together. The other ingredient, the oxidizer, is supplied from the space 25 between the plates through holes 28 in the first plate 11. In Fig. 1 a dished annular plate 18 is secured to the plate 12, fuel being supplied to the space therebetween before passing through the holes 21. The oxidizer is supplied to the space 25 from a channel 27 and the holes 28 from which it discharges are inclined so that the jets of oxidizer will intersect the jets of fuel from the holes 21. A number of ways in which plates 11, 12 may be secured together are described. The plates may be formed with depressions 35, 36 as shown in Fig. 1, the abutting surfaces of the depressions being connected by welding or the like or by means of rivets which are drilled to provide holes 21. One of the plates may be formed with depressions by pressing and the 'other machined to form depressions, or the two plates may both be flat and connected by means of ferrules 48, Fig. 7, which are formed with holes 21 and 28 and with a recess 35.
GB571553A 1953-03-02 1953-03-02 Burners for use with rocket motors Expired GB731739A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB571553A GB731739A (en) 1953-03-02 1953-03-02 Burners for use with rocket motors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB571553A GB731739A (en) 1953-03-02 1953-03-02 Burners for use with rocket motors

Publications (1)

Publication Number Publication Date
GB731739A true GB731739A (en) 1955-06-15

Family

ID=9801273

Family Applications (1)

Application Number Title Priority Date Filing Date
GB571553A Expired GB731739A (en) 1953-03-02 1953-03-02 Burners for use with rocket motors

Country Status (1)

Country Link
GB (1) GB731739A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3000184A (en) * 1956-08-14 1961-09-19 Allen M Fish Cooled injector
US3001365A (en) * 1957-05-27 1961-09-26 Aerojet General Co Shut-off valve
US3085394A (en) * 1959-06-17 1963-04-16 United Aircraft Corp Rocket propellant injector
DE1159694B (en) * 1960-08-26 1963-12-19 United Aircraft Corp Injection head for a liquid rocket
US3134227A (en) * 1959-06-24 1964-05-26 United Aircraft Corp Injector nozzle for rocket propellants
FR2705120A1 (en) * 1993-05-11 1994-11-18 Europ Propulsion Injection system with concentric slots and associated injection elements.

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3000184A (en) * 1956-08-14 1961-09-19 Allen M Fish Cooled injector
US3001365A (en) * 1957-05-27 1961-09-26 Aerojet General Co Shut-off valve
US3085394A (en) * 1959-06-17 1963-04-16 United Aircraft Corp Rocket propellant injector
US3134227A (en) * 1959-06-24 1964-05-26 United Aircraft Corp Injector nozzle for rocket propellants
DE1159694B (en) * 1960-08-26 1963-12-19 United Aircraft Corp Injection head for a liquid rocket
FR2705120A1 (en) * 1993-05-11 1994-11-18 Europ Propulsion Injection system with concentric slots and associated injection elements.
WO1994027038A1 (en) * 1993-05-11 1994-11-24 Societe Europeenne De Propulsion Injection system with concentric slots and associated injection elements
US5603213A (en) * 1993-05-11 1997-02-18 Societe Europeenne De Propulsion Injection system with concentric slits and the associated injection elements

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