RU94031217A - DIRECT-FLOW AIR JET ENGINE - Google Patents
DIRECT-FLOW AIR JET ENGINEInfo
- 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
Links
- 230000000875 corresponding Effects 0.000 claims 1
Claims (1)
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) |
Families Citing this family (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5904470A (en) * | 1997-01-13 | 1999-05-18 | Massachusetts Institute Of Technology | Counter-rotating compressors with control of boundary layers by fluid removal |
GB2407142B (en) * | 2003-10-15 | 2006-03-01 | Rolls Royce Plc | An arrangement for bleeding the boundary layer from an aircraft engine |
FR2903455B1 (en) * | 2006-07-05 | 2013-01-18 | Airbus France | METHOD FOR REVERTING THE THRUST GENERATED BY A PROPELLANT ASSEMBLY OF AN AIRCRAFT, DEVICE FOR IMPLEMENTING IT, NACELLE EQUIPPED WITH SAID DEVICE |
FR2910056A1 (en) * | 2006-12-18 | 2008-06-20 | Michel Aguilar | Rotary wing-less vertical take-off and landing vehicle for transporting passengers by air, has rear wing whose variable incidence is set to generate lift force in take-off mode, and added to forces developed on front wings in cruise mode |
EP2074323B1 (en) * | 2006-10-12 | 2012-11-21 | United Technologies Corporation | Turbofan engine with variable bypass nozzle exit area and method of operation |
US7797944B2 (en) * | 2006-10-20 | 2010-09-21 | United Technologies Corporation | Gas turbine engine having slim-line nacelle |
US7870721B2 (en) * | 2006-11-10 | 2011-01-18 | United Technologies Corporation | Gas turbine engine providing simulated boundary layer thickness increase |
US8408491B2 (en) * | 2007-04-24 | 2013-04-02 | United Technologies Corporation | Nacelle assembly having inlet airfoil for a gas turbine engine |
US7708230B2 (en) * | 2007-05-29 | 2010-05-04 | United Technologies Corporation | Flow distribution system for inlet flow control |
US8657567B2 (en) * | 2007-05-29 | 2014-02-25 | United Technologies Corporation | Nacelle compartment plenum for bleed air flow delivery system |
US8402739B2 (en) * | 2007-06-28 | 2013-03-26 | United Technologies Corporation | Variable shape inlet section for a nacelle assembly of a gas turbine engine |
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 |
EP2971735A1 (en) * | 2013-03-15 | 2016-01-20 | 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 |
US10465538B2 (en) * | 2014-11-21 | 2019-11-05 | General Electric Company | Gas turbine engine with reversible fan |
US10113508B2 (en) | 2014-11-21 | 2018-10-30 | General Electric Company | Gas turbine engine and method of assembling the same |
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 |
Family Cites Families (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1097765B (en) * | 1952-12-12 | 1961-01-19 | Snecma | Nozzle for recoil engines |
FR1463771A (en) * | 1963-12-07 | 1966-07-22 | Snecma | Device for adjusting the flow of fluid in a channel |
US3476486A (en) * | 1966-04-12 | 1969-11-04 | Dowty Rotol Ltd | Gas turbine engines |
US3528752A (en) * | 1966-04-12 | 1970-09-15 | Dowty Rotol Ltd | Gas turbine engines |
DE1628240A1 (en) * | 1966-04-12 | 1971-07-08 | Dowty Rotol Ltd | Device for blade adjustment with blowers |
DE1626028C3 (en) * | 1966-04-12 | 1974-04-04 | Dowty Rotol Ltd., Gloucester (Grossbritannien) | By-pass gas turbine engine |
US3468473A (en) * | 1966-05-25 | 1969-09-23 | Dowty Rotol Ltd | Gas turbine engines |
GB1233061A (en) * | 1968-07-15 | 1971-05-26 | ||
GB1319793A (en) * | 1970-11-19 | 1973-06-06 | ||
US3770228A (en) * | 1971-12-08 | 1973-11-06 | Lockheed Aircraft Corp | Air inlet flap |
US3931708A (en) * | 1973-10-11 | 1976-01-13 | United Technologies Corporation | Variable flap for a variable pitch ducted fan propulsor |
GB1506588A (en) * | 1975-10-11 | 1978-04-05 | Rolls Royce | Gas turbine engine power plants for aircraft |
GB1565212A (en) * | 1975-12-22 | 1980-04-16 | British Hovercraft Corp Ltd | Ductecd fan propulsors |
US4749151A (en) * | 1985-09-19 | 1988-06-07 | The Boeing Company | Apparatus for re-energizing boundary layer air |
DE3720318A1 (en) * | 1987-06-19 | 1989-01-05 | Mtu Muenchen Gmbh | GONDOLA FOR JET ENGINES |
US4865628A (en) * | 1988-12-28 | 1989-09-12 | Iwanczyk Louis C | Method for confining and removing spray drift |
US5090196A (en) * | 1989-07-21 | 1992-02-25 | The Boeing Company | Ducted fan type gas turbine engine power plants |
-
1991
- 1991-10-15 DE DE4134051A patent/DE4134051C2/en not_active Expired - Fee Related
-
1992
- 1992-10-01 US US08/211,798 patent/US5568724A/en not_active Expired - Fee Related
- 1992-10-01 WO PCT/EP1992/002274 patent/WO1993008397A1/en active IP Right Grant
- 1992-10-01 EP EP92920576A patent/EP0680557B1/en not_active Expired - Lifetime
- 1992-10-01 JP JP5507389A patent/JPH07500169A/en active Pending
- 1992-10-01 RU RU94031217A patent/RU2101535C1/en active
- 1992-10-01 DE DE59208873T patent/DE59208873D1/en not_active Expired - Fee Related
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