RU94003399A - Composite engine for flying vehicle - Google Patents

Composite engine for flying vehicle

Info

Publication number
RU94003399A
RU94003399A RU94003399/06A RU94003399A RU94003399A RU 94003399 A RU94003399 A RU 94003399A RU 94003399/06 A RU94003399/06 A RU 94003399/06A RU 94003399 A RU94003399 A RU 94003399A RU 94003399 A RU94003399 A RU 94003399A
Authority
RU
Russia
Prior art keywords
air
main
combustion
mode
passage
Prior art date
Application number
RU94003399/06A
Other languages
Russian (ru)
Inventor
Порон Клотильд
Fr]
Тонон Давид
Эрман Эрик
Original Assignee
Сосьете Оропеен де Пропюльсьон (FR)
Сосьете Оропеен де Пропюльсьон
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 Сосьете Оропеен де Пропюльсьон (FR), Сосьете Оропеен де Пропюльсьон filed Critical Сосьете Оропеен де Пропюльсьон (FR)
Publication of RU94003399A publication Critical patent/RU94003399A/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
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
    • 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
    • F02K7/16—Composite ram-jet/turbo-jet engines

Abstract

FIELD: aeronautical engineering. SUBSTANCE: composite engine includes main passage 1 equipped with air intake 110, main combustion chamber 120 and jet nozzle 130, additional passage 2 located on the outside of main passage 1 and intake 180 where movable dampers 161 are located which are crossed in their turn by air cooling or liquefying loops; they are located in different positions for control of amount of air fed to additional passage 2, complete closing position inclusive. Additional passage 2 includes low-temperature compressor 210, ejection combustion chamber 220, turbine 230, system of nozzles 240 brought out to main combustion chamber 120 of main passage 1. Composite engine may successively function in ejector turbopneumatic mode with cooled or liquefied air, in ramjet mode of subsonic combustion and in ramjet superjet mode of supersonic combustion. EFFECT: enhanced efficiency. 2 dwg

Claims (1)

Комбинированный двигатель включает основной канал 1, снабженный воздухозаборником 110, основной камерой 120 сгорания и реактивным соплом 130, дополнительный канал 2, расположенный с наружной стороны основного канала 1 и впуска 180, где расположены подвижные заслонки 161, в свою очередь пересекаемые контурами 163 охлаждения или ожижения воздуха и располагающиеся избирательно в различных положениях, регулирующих количество поступающего воздуха в дополнительный канал 2, включая положение полного закрытия. Дополнительный канал 2 включает компрессор 210 низкой температуры, эжекторную камеру 220 сгорания, турбину 230, систему сопл 240, выходящих в основную камеру 120 сгорания основного канала 1. Комбинированный двигатель может последовательно функционировать в эжекторном турбопневматическом режиме с охлажденным или сжиженным воздухом, в прямоточном воздушно-реактивном режиме дозвукового сгорания и в прямоточном воздушно-сверхреактивном режиме сверхзвукового сгорания.
Figure 00000001
The combined engine includes a main channel 1, equipped with an air intake 110, a main combustion chamber 120 and a jet nozzle 130, an additional channel 2 located on the outside of the main channel 1 and inlet 180, where the movable shutters 161 are located, which in turn are intersected by cooling or liquefaction circuits 163 air and located selectively in various positions that regulate the amount of incoming air into the additional channel 2, including the position of complete closure. Additional channel 2 includes a low temperature compressor 210, an ejection chamber 220 of combustion, a turbine 230, a system of nozzles 240 that exit into the main chamber of combustion 120 of the main channel 1. The combined engine can be sequentially operated in an ejector turbopneumatic mode with cooled or liquefied air, in a direct-flow air jet mode of subsonic combustion and in direct-flow air-supersonic mode of supersonic combustion.
Figure 00000001
RU94003399/06A 1993-02-05 1994-02-04 Composite engine for flying vehicle RU94003399A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9301319A FR2701293B1 (en) 1993-02-05 1993-02-05 Combined engine incorporating ejector modes with turbocharged air cooled or liquefied ramjet and super ramjet.
FR9301319 1993-02-05

Publications (1)

Publication Number Publication Date
RU94003399A true RU94003399A (en) 1997-04-10

Family

ID=9443798

Family Applications (1)

Application Number Title Priority Date Filing Date
RU94003399/06A RU94003399A (en) 1993-02-05 1994-02-04 Composite engine for flying vehicle

Country Status (5)

Country Link
JP (1) JPH06241119A (en)
DE (1) DE4402941B4 (en)
FR (1) FR2701293B1 (en)
GB (1) GB2274881B (en)
RU (1) RU94003399A (en)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2775499B1 (en) * 1998-02-27 2000-05-05 Aerospatiale MIXED ENGINE CAPABLE OF IMPLEMENTING AT LEAST ONE STATOREACTOR MODE AND ONE SUPERSTATOREACTOR MODE
DE10033653A1 (en) * 2000-06-16 2002-03-07 Sandor Nagy Drive system for e.g. aircraft, is formed multistage with drives units such that the drive system is combined with at least one negative pressure system
EP1172544A1 (en) * 2000-07-14 2002-01-16 Techspace Aero S.A. Combined turbo and rocket engine with air liquefier and air separator
DE10126632A1 (en) * 2000-08-08 2002-09-12 Sandor Nagy Combination propulsion system pref. for aircraft has thrust vector control, also useable as lifting device, located behind multistage vacuum system or ram jet engines
US8572946B2 (en) 2006-12-04 2013-11-05 Firestar Engineering, Llc Microfluidic flame barrier
US7886516B2 (en) * 2006-12-18 2011-02-15 Aerojet-General Corporation Combined cycle integrated combustor and nozzle system
CA2769293A1 (en) 2009-07-07 2011-01-13 Firestar Engineering Llc Tiered porosity flashback suppressing elements for monopropellant or pre-mixed bipropellant systems
US20110219742A1 (en) * 2010-03-12 2011-09-15 Firestar Engineering, Llc Supersonic combustor rocket nozzle
GB201400497D0 (en) * 2014-01-11 2014-02-26 Lewis Stephen D Low weight aircraft engine intake pre-cooler
CN103806968B (en) * 2014-03-10 2016-06-22 苟仲武 A kind of liquid air TRT and method of work
CN103835766A (en) * 2014-03-19 2014-06-04 苟仲武 Efficient energy-saving power generation method and system
JP6310293B2 (en) * 2014-03-26 2018-04-11 三菱重工業株式会社 Combustor, jet engine, flying object, and operation method of jet engine
JP6310292B2 (en) 2014-03-26 2018-04-11 三菱重工業株式会社 Combustor, jet engine, flying object, and operation method of jet engine
CN105298682B (en) * 2015-11-11 2017-03-22 沈阳黎明航空发动机(集团)有限责任公司 Cold thrust augmentation exhaust nozzle for aircraft engine
CN106150566B (en) * 2016-08-26 2018-08-21 朱小波 A kind of generating equipment based on compressed air-driven technology
CN106968835B (en) * 2017-04-14 2018-07-06 西北工业大学 Full runner is combined in a kind of rocket punching press of wide scope work
GB201808352D0 (en) 2018-05-22 2018-07-11 Rolls Royce Plc Air intake system
CN114396341A (en) * 2022-01-05 2022-04-26 北京航空航天大学 Intermediate circulation heat dissipation system for combined engine
WO2023238148A1 (en) * 2022-06-06 2023-12-14 Supnekar Subhash Internal combustion jet engine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB805418A (en) * 1955-10-05 1958-12-03 Power Jets Res & Dev Ltd Jet propulsion plant
GB971223A (en) * 1962-12-17 1964-09-30 Rolls Royce Gas turbine power plant
DE1288859B (en) * 1965-04-14 1969-02-06 Daimler Benz Ag Control device for fluid-operated devices, in particular for the hydraulic operation of windows, door locks or the like in motor vehicles
US3981144A (en) * 1975-10-28 1976-09-21 The United States Of America As Represented By The Secretary Of The Air Force Dual stage supersonic diffuser
DE3617757C1 (en) * 1986-05-30 1987-07-02 Erno Raumfahrttechnik Gmbh, 2800 Bremen, De
GB2222635B (en) * 1987-10-24 1992-05-27 British Aerospace Propulsion units for aerospace vehicles
US5052176A (en) * 1988-09-28 1991-10-01 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Combination turbojet-ramjet-rocket propulsion system
DE3912331A1 (en) * 1989-01-19 1990-10-18 Mtu Muenchen Gmbh Nozzle for hypersonic turbo-ram-jet engine
DE3909050C1 (en) * 1989-03-18 1990-08-16 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De
US5094070A (en) * 1989-04-14 1992-03-10 Mtu Motoren- Und Turbinen Union Munchin Gmbh Propelling nozzle for a hypersonic jet plane
DE3942022A1 (en) * 1989-12-20 1991-06-27 Mtu Muenchen Gmbh METHOD AND DEVICE FOR COOLING AN AIRCRAFT ENGINE
DE4016897C1 (en) * 1990-05-25 1991-06-06 Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De Method of obtaining liq. oxygen in hypersonic flight - uses turbine which reduces pressure of entering air and cools it before liquefying and sepg. into oxygen and nitrogen

Also Published As

Publication number Publication date
FR2701293A1 (en) 1994-08-12
DE4402941A1 (en) 1994-08-11
FR2701293B1 (en) 1995-04-28
JPH06241119A (en) 1994-08-30
GB2274881B (en) 1996-10-02
DE4402941B4 (en) 2005-01-20
GB9401592D0 (en) 1994-03-23
GB2274881A (en) 1994-08-10

Similar Documents

Publication Publication Date Title
RU94003399A (en) Composite engine for flying vehicle
US4085583A (en) Method for selectively switching motive fluid supply to an aft turbine of a multicycle engine
US3938328A (en) Multicycle engine
US6758032B2 (en) System of pulsed detonation injection for fluid flow control of inlets, nozzles, and lift fans
US5511374A (en) High pressure air source for aircraft and engine requirements
US5337975A (en) Breathing system for hypersonic aircraft
US7788899B2 (en) Fixed nozzle thrust augmentation system
US3659422A (en) Method and apparatus for aircraft propulsion
US20080155961A1 (en) Convertible gas turbine engine
US6662546B1 (en) Gas turbine engine fan
GB1268515A (en) A composite gas turbine ramjet engine
CA1317770C (en) Gas turbine engines
US5664415A (en) After-burning turbo-fan engine with a fixed geometry exhaust nozzle having a variable flow coefficient
US5094070A (en) Propelling nozzle for a hypersonic jet plane
DE69423481D1 (en) Nozzle with cross-section and jet vector adjustment for a jet engine
CN113738514B (en) Multi-mode combined power cycle system and method for precooling/supporting combustion by using N2O
JPS61241447A (en) Method and device for controlling cooling flow pressure of thrust intensifier by mixed flow type variable cycle gas turbine engine
US3111842A (en) Supersonic wind tunnel
Tanatsugu et al. Development study on ATREX engine
US20230340930A1 (en) Turboramjet engine
Vdoviak et al. VCE test bed engine for supersonic cruise research
GB955013A (en) Improvements in and relating to Composite Jet Engines
US3981144A (en) Dual stage supersonic diffuser
US3280564A (en) Keenan etal gas turbine power plant
JP2601906B2 (en) Air liquefaction cycle engine