GB1046909A - Rocket thrust chambers - Google Patents

Rocket thrust chambers

Info

Publication number
GB1046909A
GB1046909A GB3376163A GB3376163A GB1046909A GB 1046909 A GB1046909 A GB 1046909A GB 3376163 A GB3376163 A GB 3376163A GB 3376163 A GB3376163 A GB 3376163A GB 1046909 A GB1046909 A GB 1046909A
Authority
GB
United Kingdom
Prior art keywords
fuel
cone
annular
supplied
oxidant
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
GB3376163A
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.)
GUR CHARAN SAINI
Original Assignee
GUR CHARAN SAINI
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 GUR CHARAN SAINI filed Critical GUR CHARAN SAINI
Priority to GB3376163A priority Critical patent/GB1046909A/en
Publication of GB1046909A publication Critical patent/GB1046909A/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
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F02K9/64—Combustion or thrust chambers having cooling arrangements
    • 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

1,046,909. Rocket combustion chambers. G. C. SAINI. Nov. 24, 1964 [Aug. 26, 1963], No. 33761/63. Headings F1J and F1L. A rocket motor having a coolant jacket 32 comprises main and additional combustion chambers 1, 2, respectively, separated by a hollow deflector cone 9. Annular propellant injector elements 8, 8a, 8b, 8c surround cone 9, each element 8 being mounted between casing ribs 7 and comprising a series of thin annular laminae, having radial grooves on one side, welded together and electroplated to form injection orifices 25. In a modification, each element 8 consists of a single piece sintered porous member. Annular galleries 29, 29a are supplied with oxidant, such as nitric acid, through inlets 15, 15a and similar galleries 28, 28a are supplied with fuel, such as aniline, through inlets 14, 14a, the fuel and oxidant issuing through orifices 25 into the main combustion chamber 1. Deflector cone 9 is mounted on a hollow stem 22 and is supplied with fuel through an inner pipe 23, the fuel being guided round the interior of cone 9 to effect cooling before issuing through nozzles 11 into the combustion chamber 2. Oxidiser is injected through nozzles 12 to impinge upon the jets of fuel. The combustion products from chamber 2 flow through an annular gap 34 between cone 9 and injector element 8 to vaporise and effect mixing of the fuel and oxidant injected into the main chamber 1 through orifices 25. The mixture is further dispersed by impingement on a target surface 18.
GB3376163A 1963-08-26 1963-08-26 Rocket thrust chambers Expired GB1046909A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3376163A GB1046909A (en) 1963-08-26 1963-08-26 Rocket thrust chambers

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3376163A GB1046909A (en) 1963-08-26 1963-08-26 Rocket thrust chambers

Publications (1)

Publication Number Publication Date
GB1046909A true GB1046909A (en) 1966-10-26

Family

ID=10357105

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3376163A Expired GB1046909A (en) 1963-08-26 1963-08-26 Rocket thrust chambers

Country Status (1)

Country Link
GB (1) GB1046909A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2196393A (en) * 1986-10-14 1988-04-27 Gen Electric Propulsion apparatus and method
US4811556A (en) * 1986-10-14 1989-03-14 General Electric Company Multiple-propellant air vehicle and propulsion system
US4835959A (en) * 1986-10-14 1989-06-06 General Electric Company Multiple-propellant air vehicle and propulsion system
US4840025A (en) * 1986-10-14 1989-06-20 General Electric Company Multiple-propellant air vehicle and propulsion system
US4841723A (en) * 1986-10-14 1989-06-27 General Electric Company Multiple-propellant air vehicle and propulsion system
EP0401107A1 (en) * 1989-05-29 1990-12-05 Societe Europeenne De Propulsion (S.E.P.) S.A. Combustion chamber for ram jet
EP0604279A1 (en) * 1992-12-24 1994-06-29 Societe Europeenne De Propulsion Injector with porous wall for a rocket combustion chamber
DE102007063539A1 (en) * 2007-12-21 2009-06-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. combustion chamber device
DE102010043337A1 (en) * 2010-11-03 2012-05-16 Deutsches Zentrum für Luft- und Raumfahrt e.V. Fluid supplying device, particularly for engine of vehicle, particularly missile, for supplying two fluids to mixing chamber, has fluid supplying unit for supplying fluid to mixing chamber

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2196393B (en) * 1986-10-14 1991-07-17 Gen Electric Improvements relating to rocket casings.
US4811556A (en) * 1986-10-14 1989-03-14 General Electric Company Multiple-propellant air vehicle and propulsion system
US4835959A (en) * 1986-10-14 1989-06-06 General Electric Company Multiple-propellant air vehicle and propulsion system
US4840025A (en) * 1986-10-14 1989-06-20 General Electric Company Multiple-propellant air vehicle and propulsion system
US4841723A (en) * 1986-10-14 1989-06-27 General Electric Company Multiple-propellant air vehicle and propulsion system
GB2196393A (en) * 1986-10-14 1988-04-27 Gen Electric Propulsion apparatus and method
EP0401107A1 (en) * 1989-05-29 1990-12-05 Societe Europeenne De Propulsion (S.E.P.) S.A. Combustion chamber for ram jet
EP0604279A1 (en) * 1992-12-24 1994-06-29 Societe Europeenne De Propulsion Injector with porous wall for a rocket combustion chamber
FR2699963A1 (en) * 1992-12-24 1994-07-01 Europ Propulsion Close combustion gas generator.
US5438834A (en) * 1992-12-24 1995-08-08 Societe Europeenne De Propulsion Close combustion gas generator
DE102007063539A1 (en) * 2007-12-21 2009-06-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. combustion chamber device
DE102010043337A1 (en) * 2010-11-03 2012-05-16 Deutsches Zentrum für Luft- und Raumfahrt e.V. Fluid supplying device, particularly for engine of vehicle, particularly missile, for supplying two fluids to mixing chamber, has fluid supplying unit for supplying fluid to mixing chamber
DE102010043337B4 (en) 2010-11-03 2023-01-05 Deutsches Zentrum für Luft- und Raumfahrt e.V. fluid delivery device

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