SE8703970D0 - AIRCRAFT DRIVING SYSTEM - Google Patents

AIRCRAFT DRIVING SYSTEM

Info

Publication number
SE8703970D0
SE8703970D0 SE8703970A SE8703970A SE8703970D0 SE 8703970 D0 SE8703970 D0 SE 8703970D0 SE 8703970 A SE8703970 A SE 8703970A SE 8703970 A SE8703970 A SE 8703970A SE 8703970 D0 SE8703970 D0 SE 8703970D0
Authority
SE
Sweden
Prior art keywords
fuel
oxidizer
passageway
injection holes
combustion chamber
Prior art date
Application number
SE8703970A
Other languages
Swedish (sv)
Other versions
SE464719B (en
SE8703970L (en
Inventor
G A Coffinberry
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of SE8703970D0 publication Critical patent/SE8703970D0/en
Publication of SE8703970L publication Critical patent/SE8703970L/en
Publication of SE464719B publication Critical patent/SE464719B/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/18—Composite ram-jet/rocket engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/14—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/34—Casings; Combustion chambers; Liners thereof
    • 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
    • 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
    • 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
    • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means

Abstract

A propulsion device includes a rocket casing 8 having a combustor chamber 64 with a combustor liner 52 and a nozzle throat chamber 62 with a nozzle throat liner 52; a fuel passageway 56 defined between the liners and an outerwall 54 and a plurality of vanes 80 disposed in the fuel passageway to direct fuel circumferentially whereby the fuel travels a longer path through the passageway, and the residence time of fuel in the passageway is increased to promote heat transfer to the fuel. A plurality of fuel injection holes 68 in the combustor liner are also arranged so that fuel is injected into the combustion chamber in a direction which promotes circumferential motion of the fuel. An oxidizer is introduced through oxidizer injection holes 66 at the center of the combustion chamber to inject oxidizer into the combustion chamber in a direction which promotes circumferential motion of the oxidizer. The fuel injection holes and oxidizer injection holes may be staggered to promote overlapping of fuel and oxidizer and further promote mixing prior to and during combustion. Details are given concerning the nature of the fuel and other propellant components, and catalyst assisted endothermic pyrolysis of the fuel in the passage way is referred to. Details are also given concerning the construction of the rocket casing walls and propellant storage tanks (Fig. 2) and the arrangement of tanks and rocket motors in a vehicle (Fig. 1). Use of the device in a ram-jet or scram-jet is also referred to. <IMAGE>
SE8703970A 1986-10-14 1987-10-13 Propulsion system SE464719B (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US91821786A 1986-10-14 1986-10-14

Publications (3)

Publication Number Publication Date
SE8703970D0 true SE8703970D0 (en) 1987-10-13
SE8703970L SE8703970L (en) 1988-04-15
SE464719B SE464719B (en) 1991-06-03

Family

ID=25440002

Family Applications (1)

Application Number Title Priority Date Filing Date
SE8703970A SE464719B (en) 1986-10-14 1987-10-13 Propulsion system

Country Status (8)

Country Link
JP (1) JPS63120842A (en)
CN (1) CN87106913A (en)
DE (1) DE3734099A1 (en)
FR (1) FR2605053A1 (en)
GB (1) GB2196394B (en)
IT (1) IT1225459B (en)
NO (1) NO874263L (en)
SE (1) SE464719B (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3911655C1 (en) * 1989-04-10 1990-06-07 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De Cryogenic supersonic aircraft fuel tank - is surrounded by fuel pipe harness to permit heating or cooling
DE4437524C2 (en) * 1994-10-20 1997-04-24 Kunkel Klaus Dr Ing Method for operating a missile propulsion system and missile propulsion
DE19927735B4 (en) * 1999-06-17 2005-10-06 Eads Space Transportation Gmbh Thrust chamber arrangement for aerospace engines
US7213392B2 (en) 2003-06-10 2007-05-08 United Technologies Corporation Rocket engine combustion chamber
DE102014107316A1 (en) * 2014-05-23 2015-11-26 Airbus Operations Gmbh Tank system for the cryogenic storage of hydrogen and aircraft with a tank system for the cryogenic storage of hydrogen
DE102017106758A1 (en) * 2017-03-15 2018-09-20 Deutsches Zentrum für Luft- und Raumfahrt e.V. Thrust chamber device and method for operating a thrust chamber device
CN109162831A (en) * 2018-09-05 2019-01-08 北京航空航天大学 Solid-liquid power engine and the rocket for applying it
RU2752960C1 (en) * 2020-07-03 2021-08-11 Виктор Николаевич Исаков Combustion chamber with catalytic coating for ramjet engine and method for applying a catalytic coating
DE102020123422A1 (en) * 2020-09-08 2022-03-31 Deutsches Zentrum für Luft- und Raumfahrt e.V. Thrust chamber device and method for operating a thrust chamber device
CN112298502A (en) * 2020-10-20 2021-02-02 广东石油化工学院 Wingless electric extrusion spiral rotation forward type intelligent underwater unmanned vehicle
CN112298501B (en) * 2020-10-20 2023-06-16 广东石油化工学院 Winged electric extrusion propulsion type intelligent underwater unmanned aircraft
CN113357052B (en) * 2021-06-25 2022-07-19 中国科学院力学研究所 Method for controlling uniform retreating of combustion surface of explosive column of solid-liquid engine

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE716175C (en) * 1935-02-09 1942-01-14 Eugen Saenger Dr Ing Rocket engine
DE1085719B (en) * 1944-12-04 1960-07-21 Dr Eberhard Schneller Rocket propulsion and training
US2526222A (en) * 1948-01-02 1950-10-17 Daniel And Florence Guggenheim Cooling and feeding means for rocket type combustion chambers
BE490776A (en) * 1948-10-26
US2695496A (en) * 1952-03-05 1954-11-30 Daniel And Florence Guggenheim Structure for feeding, intermingling, vaporizing, and igniting combustion liquids ina combustion chamber for rocket-type propulsion apparatus
GB793300A (en) * 1953-06-19 1958-04-16 Havilland Engine Co Ltd Rocket motors
US2749706A (en) * 1953-10-29 1956-06-12 Daniel And Florence Guggenheim Mechanism for cooling a combustion chamber in propulsion apparatus and for feeding combustion liquids thereto
GB800354A (en) * 1955-12-23 1958-08-27 Aerojet General Co Combustion chamber for gas generation provided with cooling means and a system for operating the same
GB865942A (en) * 1958-10-10 1961-04-26 Gen Motors Corp Improvements relating to exhaust ducts included in jet propulsion engines
US3067594A (en) * 1959-05-11 1962-12-11 Catacycle Company Cooling with endothermic chemical reactions
GB970222A (en) * 1962-04-17 1964-09-16 Anders Folke Anden Improvements in liquid fuel burning apparatus
GB1196489A (en) * 1966-11-29 1970-06-24 Lutz Tilo Kayser Improvements in or relating to Rocket Engines
DE1626066C3 (en) * 1967-09-23 1974-06-12 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Process for generating pressurized gas by catalytic decomposition of a liquid monergol and device for carrying out the process
US4271675A (en) * 1977-10-21 1981-06-09 Rolls-Royce Limited Combustion apparatus for gas turbine engines
CA1159356A (en) * 1979-10-25 1983-12-27 Kurt Skoog Method and device for producing microdroplets of fluid
US4535518A (en) * 1983-09-19 1985-08-20 Rockwell International Corporation Method of forming small-diameter channel within an object

Also Published As

Publication number Publication date
IT8722207A0 (en) 1987-10-09
DE3734099A1 (en) 1988-04-21
SE464719B (en) 1991-06-03
GB2196394A (en) 1988-04-27
GB2196394B (en) 1991-06-26
NO874263D0 (en) 1987-10-13
IT1225459B (en) 1990-11-14
GB8724107D0 (en) 1987-11-18
CN87106913A (en) 1988-07-13
FR2605053A1 (en) 1988-04-15
NO874263L (en) 1988-04-15
SE8703970L (en) 1988-04-15
JPS63120842A (en) 1988-05-25

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