RU94031217A - DIRECT-FLOW AIR JET ENGINE - Google Patents

DIRECT-FLOW AIR JET ENGINE

Info

Publication number
RU94031217A
RU94031217A RU94031217/06A RU94031217A RU94031217A RU 94031217 A RU94031217 A RU 94031217A RU 94031217/06 A RU94031217/06 A RU 94031217/06A RU 94031217 A RU94031217 A RU 94031217A RU 94031217 A RU94031217 A RU 94031217A
Authority
RU
Russia
Prior art keywords
direct
air jet
jet engine
flow air
casing
Prior art date
Application number
RU94031217/06A
Other languages
Russian (ru)
Other versions
RU2101535C1 (en
Inventor
Линднер Эрнст
Вальтер Триттлер Гвидо
Бритц Клаус
Original Assignee
Мту Моторен-Унд Турбинен-Унион Мюнхен Гмбх
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
Priority claimed from DE4134051A external-priority patent/DE4134051C2/en
Application filed by Мту Моторен-Унд Турбинен-Унион Мюнхен Гмбх filed Critical Мту Моторен-Унд Турбинен-Унион Мюнхен Гмбх
Publication of RU94031217A publication Critical patent/RU94031217A/en
Application granted granted Critical
Publication of RU2101535C1 publication Critical patent/RU2101535C1/en

Links

Claims (1)

Описывается прямоточный воздушно-реактивный двигатель с подающей воздух во вторичный канал воздуходувкой или винтовым вентилятором и с внешним кожухом для воздуходувки и вторичного канала, в котором выполнен передний конец кожуха с входной закраиной, задний конец кожуха выполнен заостренным в виде сопла, и по меньшей мере один конец кожуха изменяется с точки зрения эффективной геометрии профиля с помощью отобранного из двигателя выпущенного на соответствующем конце кожуха сжатого воздуха.Describes a ramjet engine with an air blower into the secondary channel by a blower or a screw fan and with an external casing for the blower and a secondary channel in which the front end of the casing with the inlet edge is made; the end of the casing changes in terms of the effective geometry of the profile using the compressed air released at the corresponding end of the casing selected from the engine.
RU94031217A 1991-10-15 1992-10-01 Turbojet engine RU2101535C1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE4134051A DE4134051C2 (en) 1991-10-15 1991-10-15 Turbine jet engine with fan
DEP4134051.5 1991-10-15
PCT/EP1992/002274 WO1993008397A1 (en) 1991-10-15 1992-10-01 Turbojet engine with a fan or propfan

Publications (2)

Publication Number Publication Date
RU94031217A true RU94031217A (en) 1995-12-20
RU2101535C1 RU2101535C1 (en) 1998-01-10

Family

ID=6442694

Family Applications (1)

Application Number Title Priority Date Filing Date
RU94031217A RU2101535C1 (en) 1991-10-15 1992-10-01 Turbojet engine

Country Status (6)

Country Link
US (1) US5568724A (en)
EP (1) EP0680557B1 (en)
JP (1) JPH07500169A (en)
DE (2) DE4134051C2 (en)
RU (1) RU2101535C1 (en)
WO (1) WO1993008397A1 (en)

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US8408491B2 (en) * 2007-04-24 2013-04-02 United Technologies Corporation Nacelle assembly having inlet airfoil for a gas turbine engine
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FR2920134B1 (en) * 2007-08-20 2010-02-26 Aircelle Sa NACELLE EQUIPPED WITH AT LEAST ONE OVERPRESSURE TRAPPER
US9004399B2 (en) 2007-11-13 2015-04-14 United Technologies Corporation Nacelle flow assembly
US8192147B2 (en) * 2007-12-14 2012-06-05 United Technologies Corporation Nacelle assembly having inlet bleed
US8186942B2 (en) * 2007-12-14 2012-05-29 United Technologies Corporation Nacelle assembly with turbulators
DE102008027275A1 (en) * 2008-06-06 2010-01-07 Atena Engineering Gmbh Air-breathing nacelle for aircraft engine, has circular front contour and sucking unit that is provided for sucking air into nacelle, where sucking unit comprises turbocharger with fan and turbine
RU2447308C2 (en) * 2010-07-09 2012-04-10 Федеральное государственное унитарное предприятие "Летно-исследовательский институт имени М.М. Громова" Bypass turbojet engine with airflow redistribution at inlet
US20140363276A1 (en) * 2013-03-15 2014-12-11 Rolls-Royce Corporation Ultra high bypass ratio turbofan engine
EP2823952A1 (en) * 2013-07-09 2015-01-14 Siemens Aktiengesellschaft Adaptation method and production method for components produced by means of SLM
US10113508B2 (en) 2014-11-21 2018-10-30 General Electric Company Gas turbine engine and method of assembling the same
US10465538B2 (en) * 2014-11-21 2019-11-05 General Electric Company Gas turbine engine with reversible fan
FR3039228B1 (en) * 2015-07-22 2020-01-03 Safran Aircraft Engines AIRCRAFT COMPRISING A CARENE REAR PROPELLER WITH INLET STATOR INCLUDING A BLOWING FUNCTION
FR3052191B1 (en) * 2016-06-01 2019-07-12 Safran Aircraft Engines INVERSION OF PUSH IN A TURBOMACHINE WITH VARIABLE CALIBRATION BLOWER
PL417832A1 (en) 2016-07-04 2018-01-15 General Electric Company Socket expansion unit, preferably for a nozzle and method for disassembling it and the fan engine containing that unit
PL235797B1 (en) * 2018-02-21 2020-10-19 Gen Electric Bell-shaped nozzle unit for gas-turbine engines
FR3095193B1 (en) * 2019-04-17 2022-06-24 Safran Aircraft Engines Method of using a turbojet nacelle air inlet comprising an air inlet lip comprising a movable portion to promote a thrust reversal phase
FR3095244B1 (en) 2019-04-17 2022-06-24 Safran Aircraft Engines Method for using a turbojet nacelle air inlet during a thrust phase and during a thrust reversal phase
FR3106861B1 (en) * 2020-02-03 2023-03-17 Safran Aircraft Engines Nacelle air outlet for an aircraft turbojet comprising a straightening device to promote a thrust reversal phase
US20230340927A1 (en) * 2022-04-26 2023-10-26 General Electric Company Reverse thrust turbofan engine

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