IT979902B - Perfezionamento nei motori a turbina a gas a ventola intubata - Google Patents
Perfezionamento nei motori a turbina a gas a ventola intubataInfo
- Publication number
- IT979902B IT979902B IT48884/73A IT4888473A IT979902B IT 979902 B IT979902 B IT 979902B IT 48884/73 A IT48884/73 A IT 48884/73A IT 4888473 A IT4888473 A IT 4888473A IT 979902 B IT979902 B IT 979902B
- Authority
- IT
- Italy
- Prior art keywords
- intubated
- improvement
- gas turbine
- turbine engines
- fan gas
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/54—Nozzles having means for reversing jet thrust
- F02K1/64—Reversing fan flow
- F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
- F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1306872A GB1424193A (en) | 1972-03-21 | 1972-03-21 | Gas turbine ducted fan engines |
Publications (1)
Publication Number | Publication Date |
---|---|
IT979902B true IT979902B (it) | 1974-09-30 |
Family
ID=10016210
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
IT48884/73A IT979902B (it) | 1972-03-21 | 1973-03-16 | Perfezionamento nei motori a turbina a gas a ventola intubata |
Country Status (6)
Country | Link |
---|---|
US (1) | US3875742A (it) |
JP (1) | JPS496698A (it) |
DE (1) | DE2314140A1 (it) |
FR (1) | FR2177006B1 (it) |
GB (1) | GB1424193A (it) |
IT (1) | IT979902B (it) |
Families Citing this family (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3916622A (en) * | 1971-09-04 | 1975-11-04 | Volkswagenwerk Ag | Combustion engine with at least one exhaust gas cleaning arrangement |
JPS5111971A (en) * | 1974-07-14 | 1976-01-30 | Santo Tekkosho Kk | Fukurojofuhakuno shiborihoho |
US4373328A (en) * | 1980-10-22 | 1983-02-15 | United Technologies Corporation | Thrust reverser |
US5315821A (en) * | 1993-02-05 | 1994-05-31 | General Electric Company | Aircraft bypass turbofan engine thrust reverser |
FR2730763B1 (fr) * | 1995-02-21 | 1997-03-14 | Hispano Suiza Sa | Inverseur de poussee a volets aval pour turboreacteur |
GB2308866B (en) * | 1996-01-04 | 1999-09-08 | Rolls Royce Plc | Ducted fan gas turbine engine with secondary duct |
US7458221B1 (en) * | 2003-10-23 | 2008-12-02 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Variable area nozzle including a plurality of convexly vanes with a crowned contour, in a vane to vane sealing arrangement and with nonuniform lengths |
FR2871776B1 (fr) * | 2004-06-21 | 2007-11-02 | Snecma Moteurs Sa | Procede de freinage d'un avion et turboreacteur a double flux pour la mise en oeuvre du procede |
GB0608985D0 (en) * | 2006-05-06 | 2006-06-14 | Rolls Royce Plc | Aeroengine thrust reverser |
US8286415B2 (en) * | 2006-10-12 | 2012-10-16 | United Technologies Corporation | Turbofan engine having inner fixed structure including ducted passages |
DE602007008299D1 (de) * | 2007-03-05 | 2010-09-16 | United Technologies Corp | Fandüse mit variablem querschnitt für eine gasturbinentriebwerksfangondel mit antriebsringbetätigungssystem |
US8061119B2 (en) | 2007-11-29 | 2011-11-22 | United Technologies Corporation | Actuation mechanism for a convertible gas turbine propulsion system |
US8511058B2 (en) * | 2007-11-29 | 2013-08-20 | United Technologies Corporation | Convertible gas turbine propulsion system |
FR2929998B1 (fr) * | 2008-04-14 | 2011-08-12 | Aircelle Sa | Nacelle de turboreacteur a double flux |
US7716932B2 (en) * | 2008-07-24 | 2010-05-18 | Spirit Aerosystems, Inc. | Dilating fan duct nozzle |
FR2947868B1 (fr) * | 2009-07-08 | 2011-12-16 | Airbus Operations Sas | Nacelle d'aeronef incorporant un dispositif pour inverser la poussee |
US9623976B2 (en) * | 2012-07-25 | 2017-04-18 | Rohr, Inc. | Nacelle for a high bypass ratio engine with multiple flow paths |
EP2971657B1 (en) * | 2013-03-12 | 2021-08-04 | Raytheon Technologies Corporation | Expanding shell flow control device |
WO2014159311A1 (en) | 2013-03-14 | 2014-10-02 | United Technologies Corporation | Ventilation system using thrust reverser linkages |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2947499A (en) * | 1954-10-02 | 1960-08-02 | Douglas Aubrey | Jet propulsion for aircraft and control means therefor |
GB978041A (en) * | 1963-08-21 | 1964-12-16 | Rolls Royce | Aerofoil-section member having relatively movable parts |
US3303653A (en) * | 1965-06-30 | 1967-02-14 | Gen Electric | Lightweight thrust reverser |
US3500646A (en) * | 1968-04-19 | 1970-03-17 | Rohr Corp | Thrust reverser |
GB1211923A (en) * | 1968-08-30 | 1970-11-11 | Rolls Royce | Thrust reverser for gas turbine jet propulsion engine |
US3599432A (en) * | 1970-04-02 | 1971-08-17 | Rohr Corp | Thrust reversing apparatus for turbo-fan propulsion unit |
US3598318A (en) * | 1970-04-10 | 1971-08-10 | Boeing Co | Movable acoustic splitter for nozzle area control and thrust reversal |
US3601992A (en) * | 1970-06-10 | 1971-08-31 | Rohr Corp | Thrust reversing apparatus |
GB1365491A (en) * | 1971-01-02 | 1974-09-04 | Dowty Rotol Ltd | Gas turbine ducted fan engines and fans therefor |
US3721389A (en) * | 1971-06-10 | 1973-03-20 | Boeing Co | Exit nozzle assemblies for gas turbine power plants |
US3792584A (en) * | 1972-02-16 | 1974-02-19 | Boeing Co | Increased or variable bypass ratio engines |
-
1972
- 1972-03-21 GB GB1306872A patent/GB1424193A/en not_active Expired
-
1973
- 1973-03-16 IT IT48884/73A patent/IT979902B/it active
- 1973-03-19 JP JP48031054A patent/JPS496698A/ja active Pending
- 1973-03-21 DE DE19732314140 patent/DE2314140A1/de active Pending
- 1973-03-21 FR FR7310152A patent/FR2177006B1/fr not_active Expired
- 1973-03-21 US US343459A patent/US3875742A/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
FR2177006A1 (it) | 1973-11-02 |
DE2314140A1 (de) | 1973-10-04 |
GB1424193A (en) | 1976-02-11 |
US3875742A (en) | 1975-04-08 |
JPS496698A (it) | 1974-01-21 |
FR2177006B1 (it) | 1980-02-22 |
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