WO1998025021A1 - Moteur combine pour aeronefs - Google Patents

Moteur combine pour aeronefs Download PDF

Info

Publication number
WO1998025021A1
WO1998025021A1 PCT/BY1997/000004 BY9700004W WO9825021A1 WO 1998025021 A1 WO1998025021 A1 WO 1998025021A1 BY 9700004 W BY9700004 W BY 9700004W WO 9825021 A1 WO9825021 A1 WO 9825021A1
Authority
WO
WIPO (PCT)
Prior art keywords
air
propulsion system
sgορaniya
combined
small
Prior art date
Application number
PCT/BY1997/000004
Other languages
English (en)
Russian (ru)
Inventor
Alexandr Evgenievich Yashin
Original Assignee
Alexandr Evgenievich Yashin
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 Alexandr Evgenievich Yashin filed Critical Alexandr Evgenievich Yashin
Publication of WO1998025021A1 publication Critical patent/WO1998025021A1/fr

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
    • F02K7/16—Composite ram-jet/turbo-jet engines

Definitions

  • the unit for loading a combined motor unit for the aircraft is made in the form of separate sections that are installed on an internal or external unit.
  • the unit or part of it is located in the central and central part of the city and is equipped with a fully-equipped investigative unit.
  • the air-propelled engine is equipped with separate air intakes. ⁇ ⁇ 98/25021 ⁇ / ⁇ 97 / 00004
  • ⁇ a ⁇ ig. 1 A general view of the combined propulsion system for airborne units is shown.
  • ⁇ a ⁇ ig. 2 the same, with a ring regulated output of the products of the combustion of an air-reactive engine in the combustion chamber of the installation.
  • 4, and 5 shows a general view of the combined motor unit for the flight equipment made in the form of separate sections with a cut.
  • ⁇ a ⁇ ig. 6 shows the combined motor unit for the aircraft, the chamber for the combustion of the shell is made in the form of separate sections with a split.
  • ⁇ zdu ⁇ zab ⁇ ni ⁇ 3 ⁇ ame ⁇ y sg ⁇ aniya s ⁇ l ⁇ 4 and 5 are provided ⁇ eguli ⁇ v ⁇ chnymi us ⁇ ys ⁇ vami 14 us ⁇ an ⁇ vlennymi with v ⁇ zm ⁇ zhn ⁇ s ⁇ yu ⁇ e ⁇ emescheniya vd ⁇ l and / or ⁇ e ⁇ endi ⁇ ulya ⁇ n ⁇ ⁇ si ⁇ usa 2.
  • the air inlets 3 are regulated by the direct installation of the equipment 16.
  • the 4 air vessels are equipped with regulating air inlets 17.
  • ⁇ a ⁇ ig. 2 combined engine mount for airplanes is made up of external 1 and 2 internal air vents with air intake 3 and a wing
  • a combustion chamber 5 with fuel dischargers is installed 6.
  • An internal air outlet 2 which has an exhaust outlet 5 ⁇ ⁇ 98/25021 ⁇ S ⁇ 4 / ⁇ 97 / 00004 ⁇ ea ⁇ ivny dviga ⁇ el 9 and 10 vy ⁇ lnen v ⁇ zdushny ⁇ a ⁇ v ⁇ zdushn ⁇ - ⁇ ea ⁇ ivn ⁇ g ⁇ dviga ⁇ elya 9 with us ⁇ an ⁇ vlennym thereon ⁇ m ⁇ ess ⁇ m 12.
  • ⁇ zdu ⁇ zab ⁇ ni ⁇ 3 ⁇ ame ⁇ y sg ⁇ aniya s ⁇ l ⁇ 4 and 5 are provided ⁇ eguli ⁇ v ⁇ chnymi us ⁇ ys ⁇ vami 14 us ⁇ an ⁇ vlennymi with v ⁇ zm ⁇ zhn ⁇ s ⁇ yu ⁇ e ⁇ emescheniya vd ⁇ l and / or ⁇ e ⁇ endi ⁇ ulya ⁇ n ⁇ ⁇ si ⁇ usa 2.
  • ⁇ ame ⁇ a sg ⁇ aniya 5 d ⁇ lni ⁇ eln ⁇ provided ⁇ sun ⁇ ami ⁇ isli ⁇ elya 1 5.
  • ⁇ zdushn ⁇ - ⁇ ea ⁇ ivny dviga ⁇ el 9 ⁇ as ⁇ l ⁇ zhen ⁇ delnymi se ⁇ tsiyami between 21 and provided with us ⁇ an ⁇ v ⁇ i v ⁇ zdushnym ⁇ a ⁇ m 10.
  • ⁇ zdu ⁇ zab ⁇ ni ⁇ 3 ⁇ ame ⁇ y sg ⁇ aniya s ⁇ l ⁇ 4 and 5 are provided ⁇ eguli ⁇ v ⁇ chnymi us ⁇ ys ⁇ vami 14 us ⁇ an ⁇ vlennymi with v ⁇ zm ⁇ zhn ⁇ s ⁇ yu ⁇ e ⁇ emescheniya vd ⁇ l and / or ⁇ e ⁇ endi ⁇ ulya ⁇ n ⁇ ⁇ si ⁇ usa 2.
  • the air inlet 3 is configured for use by the devices installed on it 16.
  • the equipment 4 is equipped with an air inlet 17.
  • About 12 sections 21 are equipped with outputs 22 from the shaft 11 of the jet engine 9. ⁇ ⁇ 98/25021 5 ⁇ / ⁇ 97 / 00004
  • ⁇ a ⁇ ig. 6 ⁇ mbini ⁇ vannaya dviga ⁇ elnaya us ⁇ an ⁇ v ⁇ a for le ⁇ a ⁇ elny ⁇ a ⁇ a ⁇ a ⁇ v s ⁇ s ⁇ i ⁇ of vneshneg ⁇ vnu ⁇ enneg ⁇ 1 and 2 with ⁇ us ⁇ v v ⁇ zdu ⁇ zab ⁇ ni ⁇ m 3 and 4.
  • s ⁇ l ⁇ m ⁇ ezhdu ⁇ usami 1 and 2 ⁇ as ⁇ l ⁇ zhena ⁇ ame ⁇ a sg ⁇ aniya 5 ⁇ livnymi ⁇ sun ⁇ ami 6.
  • ⁇ zdu ⁇ zab ⁇ ni ⁇ 3 ⁇ ame ⁇ y sg ⁇ aniya s ⁇ l ⁇ 4 and 5 are provided ⁇ eguli ⁇ v ⁇ chnymi us ⁇ ys ⁇ vami 14 us ⁇ an ⁇ vlennymi with v ⁇ zm ⁇ zhn ⁇ s ⁇ yu ⁇ e ⁇ emescheniya vd ⁇ l and / or ⁇ e ⁇ endi ⁇ ulya ⁇ n ⁇ ⁇ si housing 2.
  • the combustion chamber 5 is optionally equipped with a dedusting unit 15.
  • the air inlet 3 is regulated by a non-discharging equipment.
  • ⁇ zab ⁇ ni ⁇ v 3 us ⁇ an ⁇ vlen ⁇ e ⁇ edvizhn ⁇ y v ⁇ dn ⁇ y ⁇ nus 18. ⁇ vnu ⁇ ennem ⁇ use 2, v ⁇ zdushn ⁇ - ⁇ ea ⁇ ivnym dviga ⁇ elem 9 vy ⁇ lnen ⁇ ltsev ⁇ y vy ⁇ d 20 ⁇ du ⁇ v sg ⁇ aniya v ⁇ zdushn ⁇ ⁇ ea ⁇ ivn ⁇ g ⁇ dviga ⁇ elya-9.
  • a BETTER RANGE OF PREVENTION OF PREVENTION A combined motor unit for flying machines operates the following way. ⁇ eguli ⁇ v ⁇ chnye us ⁇ ys ⁇ va 14 and us ⁇ ys ⁇ va 16 ⁇ ame ⁇ y 13 and ⁇ sun ⁇ i 6 us ⁇ anavlivayu ⁇ in ⁇ l ⁇ zhenie "a" ⁇ mi ⁇ uya e ⁇ im ⁇ mu s ⁇ la 4 and ⁇ azme ⁇ v ⁇ da for v ⁇ zdu ⁇ a che ⁇ ez v ⁇ zdu ⁇ zab ⁇ ni ⁇ 3 ⁇ ame ⁇ y sg ⁇ aniya 5 and ⁇ a ⁇ zhe for s ⁇ zdaniya ⁇ imalny ⁇ usl ⁇ vy sg ⁇ aniya ⁇ liva, ⁇ as ⁇ ylyaem ⁇ g ⁇ navs ⁇ echu v ⁇ zdushn ⁇ mu ⁇ u, vy ⁇ dyaschemu of ⁇ ltsev ⁇ g
  • S ⁇ s ⁇ is ⁇ echeniya ⁇ ea ⁇ ivn ⁇ y s ⁇ ui m ⁇ zhn ⁇ ⁇ a ⁇ zhe ⁇ eguli ⁇ va ⁇ ⁇ u ⁇ em ⁇ dn ⁇ v ⁇ emenn ⁇ g ⁇ za ⁇ y ⁇ iya dvu ⁇ ⁇ iv ⁇ l ⁇ zhny ⁇ s ⁇ v ⁇ 17 s ⁇ la 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)
  • Monitoring And Testing Of Nuclear Reactors (AREA)

Abstract

L'invention concerne un moteur combiné pour aéronefs qui comprend un corps extérieur et un corps intérieur avec des entrées d'air et des tuyères, une chambre de combustion avec des injecteurs de carburant située entre les corps extérieur et intérieur, et un réacteur. Le corps intérieur comporte un canal d'air se terminant par une sortie annulaire qui est munie d'un dispositif de formation de flux d'air et qui débouche dans la chambre de combustion et dans le canal d'air du réacteur. Un compresseur est installé sur l'arbre de ce dernier. Des injecteurs de carburant avec des préchambres sont installés sur le pourtour du corps intérieur derrière la sortie annulaire de manière à pouvoir se déplacer axialement. Les entrées d'air de la chambre de combustion et les tuyères sont munies de dispositifs de régulation pouvant se déplacer le long et/ou en travers de l'axe du corps. Le corps intérieur comporte un carénage conique installé derrière le réacteur et dont la base se situe près du bord arrière de la chambre de combustion du moteur.
PCT/BY1997/000004 1996-12-02 1997-07-07 Moteur combine pour aeronefs WO1998025021A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
BY961100 1996-12-02
BY961100 1996-12-02
BY970004 1997-01-03
BY970004 1997-01-03

Publications (1)

Publication Number Publication Date
WO1998025021A1 true WO1998025021A1 (fr) 1998-06-11

Family

ID=25665744

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/BY1997/000004 WO1998025021A1 (fr) 1996-12-02 1997-07-07 Moteur combine pour aeronefs

Country Status (2)

Country Link
RU (1) RU2166659C2 (fr)
WO (1) WO1998025021A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2626278C2 (ru) * 2015-03-20 2017-07-25 Виктор Серафимович Бахирев Комбинированный воздушно-реактивный двигатель
RU2608426C2 (ru) * 2015-05-26 2017-01-18 Виктор Серафимович Бахирев Универсальный воздушно-реактивный двигатель

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3635029A (en) * 1968-09-06 1972-01-18 Snecma Composite gas turbine ramjet engine
US4294068A (en) * 1978-03-27 1981-10-13 The Boeing Company Supersonic jet engine and method of operating the same
GB2205360A (en) * 1987-05-27 1988-12-07 Mtu Muenchen Gmbh Composite fanjet/ramjet propulsion device
US5056307A (en) * 1990-05-25 1991-10-15 The United States Of America As Represented By The Secretary Of The Air Force Exhaust nozzle cooling utilizing total engine flow
FR2682719A1 (fr) * 1991-10-16 1993-04-23 Snecma Moteur pour vehicule hypersonique a fonctionnements turboreacteur et statoreacteur.

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3635029A (en) * 1968-09-06 1972-01-18 Snecma Composite gas turbine ramjet engine
US4294068A (en) * 1978-03-27 1981-10-13 The Boeing Company Supersonic jet engine and method of operating the same
GB2205360A (en) * 1987-05-27 1988-12-07 Mtu Muenchen Gmbh Composite fanjet/ramjet propulsion device
US5056307A (en) * 1990-05-25 1991-10-15 The United States Of America As Represented By The Secretary Of The Air Force Exhaust nozzle cooling utilizing total engine flow
FR2682719A1 (fr) * 1991-10-16 1993-04-23 Snecma Moteur pour vehicule hypersonique a fonctionnements turboreacteur et statoreacteur.

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
A.N. CHERSTIOUK, "Kompressori", Moskva-Leningrad, Crosydarstviennoie Energetitcheskoie Izdatelstvo, 1959, p. 90. *
R.I. KOURZINER, "Reaction Engines for High Sufrasonic Speeds (Conceptual Basis)", Moscow, Engineering Industry, 1977, page 146. *

Also Published As

Publication number Publication date
RU2166659C2 (ru) 2001-05-10

Similar Documents

Publication Publication Date Title
US2482505A (en) Mechanism providing a ram jet engine with a pilot flame and with a drive for its auxiliary equipment
US2168726A (en) Propulsion of aircraft and gas turbines
US8544280B2 (en) Continuous detonation wave engine with quenching structure
US2709889A (en) Gas turbine using revolving ram jet burners
US3775974A (en) Gas turbine engine
JP2001355515A (ja) 複合サイクル・パルスデトネーション・タービンエンジン
US5660038A (en) Rotary jet engine
US5161369A (en) Aft fan gas turbine engine
US2922278A (en) Coaxial combustion products generator and turbine
US2641902A (en) Combination ram jet and turbojet
CN109028147A (zh) 环形喉道旋转爆震燃烧器和相应的推进系统
US3442082A (en) Turbine gas generator and work propulsion system for aircraft and other vehicles
US9109535B2 (en) Propulsion system and method
GB1069217A (en) Improvements relating to engines
US8250854B2 (en) Self-starting turbineless jet engine
EP2947304B1 (fr) Moteur à turbine à gaz avec un trajet d'écoulement sélectif
US7752835B2 (en) Pulsed combustion engine
US2713243A (en) Rocket and turbine engine combination for aircraft
US2748568A (en) Fuel injection arrangement in vortex air stream in an annular combustion chamber surrounding a gas turbine
GB887328A (en) Improvements in or relating to rotary internal combustion engines
WO1998025021A1 (fr) Moteur combine pour aeronefs
GB1452267A (en) Jet propulsion powerplant frames
RU173530U1 (ru) Силовая установка гиперзвукового летательного аппарата
USH1234H (en) Solid propellant air-turborocket
US3354636A (en) Circle jet engine

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): CN JP US AM AZ BY KG KZ MD RU TJ TM

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): AT BE CH DE DK ES FI FR GB GR IE IT LU MC NL PT SE

DFPE Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101)
121 Ep: the epo has been informed by wipo that ep was designated in this application
122 Ep: pct application non-entry in european phase