ES2135579T3 - Conjunto de cascada para uso en un mecanismo inversor del empuje. - Google Patents
Conjunto de cascada para uso en un mecanismo inversor del empuje.Info
- Publication number
- ES2135579T3 ES2135579T3 ES94915796T ES94915796T ES2135579T3 ES 2135579 T3 ES2135579 T3 ES 2135579T3 ES 94915796 T ES94915796 T ES 94915796T ES 94915796 T ES94915796 T ES 94915796T ES 2135579 T3 ES2135579 T3 ES 2135579T3
- Authority
- ES
- Spain
- Prior art keywords
- waterfall
- elements
- matrix
- group
- default
- Prior art date
- Legal status (The legal status 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 status listed.)
- Expired - Lifetime
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
- F02K1/56—Reversing jet main flow
- F02K1/563—Reversing jet main flow in specified direction, e.g. to obviate its reinjection
-
- 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
- F02K1/56—Reversing jet main flow
- F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
- F02K1/605—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers the aft end of the engine cowling being movable to uncover openings for the reversed flow
-
- 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)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Toys (AREA)
Abstract
SE PRESENTA UN DISPOSITIVO DE CASCADA (14) PARA SU USO EN UN MECANISMO DE INVERSION DE IMPULSION (16) DE UN MOTOR A REACCION (18) QUE INCLUYE AL MENOS UN GRUPO DE ELEMENTOS EN CASCADA DE FORMA SUBSTANCIALMENTE IDENTICA (28) CADA UNO EN LA FORMA DE UN POLIGONO PREDEFINIDO. LOS ELEMENTOS DE CASCADA (28) ESTAN POSICIONADOS EN UNA MATRIZ, EN DONDE CADA UNO DE LOS ELEMENTOS DE CASCADA EN EL GRUPO PUEDE SER INTERCAMBIADO EN UNA UBICACION EN LA MATRIZ CON OTRO ELEMENTO DE CASCADA EN EL GRUPO. EN UNA PRIMERA CONFORMACION PREFERIDA, EL POLIGONO PREDEFINIDO ES UN POLIGONO REGULAR Y CADA ELEMENTO DE CASCADA (28) PUEDE GIRAR EN SU POSICION DE MATRIZ ALREDEDOR DE UN EJE GENERALMENTE NORMAL AL ELEMENTO DE CASCADA (28). LA MATRIZ SE APROXIMA SUBSTANCIALMENTE A SECCIONES DE DOS ESFERAS INTERSECTANTES, EN DONDE UN EJE CENTRAL DE LA MATRIZ ES GENERALMENTE COINCIDENTE CON EL EJE LONGITUDINAL DEL MOTOR A REACCION (18). LOS ELEMENTOS DE CASCADA ESTAN SOPORTADOS EN UN DISPOSITIVO DE CASCADA (14) MEDIANTE UNA ESTRUCTURA (30) QUE TIENE UNA ARMADURA QUE DEFINE ABERTURAS (32) EN LA FORMA DEL POLIGONO REGULAR PREDEFINIDO PARA RECIBIR LOS ELEMENTOS DE CASCADA (28).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US4710493A | 1993-04-13 | 1993-04-13 |
Publications (1)
Publication Number | Publication Date |
---|---|
ES2135579T3 true ES2135579T3 (es) | 1999-11-01 |
Family
ID=21947085
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
ES94915796T Expired - Lifetime ES2135579T3 (es) | 1993-04-13 | 1994-04-13 | Conjunto de cascada para uso en un mecanismo inversor del empuje. |
Country Status (6)
Country | Link |
---|---|
US (1) | US5507143A (es) |
EP (1) | EP0699273B1 (es) |
AU (1) | AU6768594A (es) |
DE (1) | DE69420555T2 (es) |
ES (1) | ES2135579T3 (es) |
WO (1) | WO1994024430A1 (es) |
Families Citing this family (34)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0763653B1 (en) * | 1995-09-13 | 2001-07-18 | SOCIETE DE CONSTRUCTION DES AVIONS HUREL-DUBOIS (société anonyme) | Thrust reverser door with jet deflection cascade |
US5987880A (en) * | 1997-07-08 | 1999-11-23 | Mcdonnell Douglas Corporation | Supersonic engine, multi-port thrust reversing system |
US6311928B1 (en) | 2000-01-05 | 2001-11-06 | Stage Iii Technologies, L.C. | Jet engine cascade thrust reverser for use with mixer/ejector noise suppressor |
US6725541B1 (en) * | 2000-01-21 | 2004-04-27 | Rolls-Royce Plc | Flow directing element and a method of manufacturing a flow directing element |
GB0001279D0 (en) * | 2000-01-21 | 2000-03-08 | Rolls Royce Plc | A flow directing element and a method of manufacturing a flow directing element |
FR2849113B1 (fr) * | 2002-12-24 | 2005-02-04 | Hurel Hispano | Inverseur de poussee a grilles de deflection optimisees |
US7820875B2 (en) * | 2004-03-29 | 2010-10-26 | The Procter & Gamble Company | Disposable absorbent articles being adaptable to wearer's anatomy |
US20110101158A1 (en) * | 2005-03-29 | 2011-05-05 | The Boeing Company | Thrust Reversers Including Monolithic Components |
US7690190B2 (en) * | 2005-05-11 | 2010-04-06 | The Boeing Company | Aircraft systems including cascade thrust reversers |
US7484356B1 (en) * | 2005-07-26 | 2009-02-03 | Aeronautical Concepts Of Exhaust, Llc | Cascade reverser without blocker doors |
GB0608985D0 (en) * | 2006-05-06 | 2006-06-14 | Rolls Royce Plc | Aeroengine thrust reverser |
FR2905991B1 (fr) * | 2006-09-20 | 2012-01-13 | Snecma | Systeme propulsif integre comportant un moteur a turboreacteur a double flux. |
EP2074319B1 (en) * | 2006-10-12 | 2012-08-15 | United Technologies Corporation | Gas turbine engine with a variable exit area fan nozzle, nacelle assembly of such a engine, and corresponding operating method |
US8201390B2 (en) * | 2007-12-12 | 2012-06-19 | Spirit Aerosystems, Inc. | Partial cascade thrust reverser |
US8127532B2 (en) * | 2008-11-26 | 2012-03-06 | The Boeing Company | Pivoting fan nozzle nacelle |
US8959889B2 (en) | 2008-11-26 | 2015-02-24 | The Boeing Company | Method of varying a fan duct nozzle throat area of a gas turbine engine |
USRE45142E1 (en) | 2009-03-31 | 2014-09-23 | Blanco Gmbh + Co Kg | Sink |
USD632373S1 (en) * | 2009-03-31 | 2011-02-08 | Blanco Gmbh + Co Kg | Sink |
FR2956162B1 (fr) * | 2010-02-08 | 2012-11-16 | Snecma | Tuyere de flux froid d'un turboreacteur a double flux a flux separes incorporant un inverseur de poussee a grilles |
FR2960918B1 (fr) * | 2010-06-08 | 2012-05-25 | Aircelle Sa | Grille de deviation du type autosupporte pour inverseur de poussee |
FR2978990A1 (fr) * | 2011-08-08 | 2013-02-15 | Aircelle Sa | Dispositif d'inversion de poussee |
US9038367B2 (en) * | 2011-09-16 | 2015-05-26 | United Technologies Corporation | Fan case thrust reverser |
US9109462B2 (en) * | 2011-12-15 | 2015-08-18 | United Technologies Corporation | Energy-absorbing fan case for a gas turbine engine |
FR2987600B1 (fr) * | 2012-03-02 | 2014-02-28 | Aircelle Sa | Nacelle aplatie de turboreacteur |
USD733159S1 (en) * | 2013-01-14 | 2015-06-30 | Samsung Electronics Co., Ltd. | Monitor |
DE102014210025A1 (de) * | 2014-05-26 | 2015-12-17 | Rolls-Royce Deutschland Ltd & Co Kg | Schubumkehrkaskadenelement einer Fluggasturbine |
US10344709B2 (en) * | 2015-09-10 | 2019-07-09 | Honeywell International Inc. | System and method for reducing idle thrust in a translating cowl thrust reverser |
FR3044719B1 (fr) * | 2015-12-08 | 2017-12-22 | Snecma | Ensemble de propulsion d'aeronef equipe de marches permettant a un operateur d'atteindre sa portion superieure |
US10648426B2 (en) | 2016-01-14 | 2020-05-12 | Honeywell International Inc. | Single row vane assembly for a thrust reverser |
US10337454B2 (en) * | 2016-01-25 | 2019-07-02 | Honeywell International Inc. | Thrust reverser with asymmetric vane geometry |
US10539095B2 (en) * | 2016-04-06 | 2020-01-21 | Rolls-Royce Plc | Aircraft gas turbine engine nacelle |
US10598127B2 (en) | 2017-08-15 | 2020-03-24 | Spirit Aerosystems, Inc. | Method of fabricating a thrust reverser cascade assembly |
FR3074855A1 (fr) * | 2017-12-11 | 2019-06-14 | Airbus Operations | Grille pour la formation d'un flux d'inversion d'un turboreacteur d'aeronef |
US11078871B2 (en) * | 2018-12-21 | 2021-08-03 | Rohr, Inc. | Thrust reverser system with cascades |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1733770A (en) * | 1928-02-15 | 1929-10-29 | Glenn L Martin Co | Method of manufacturing cowlings |
BE546877A (es) * | 1954-12-23 | |||
US2997845A (en) * | 1957-03-22 | 1961-08-29 | Rolls Royce | Jet propulsion nozzle adjustable to give forward and reverse thrusts |
US3374588A (en) * | 1964-03-30 | 1968-03-26 | Dow Chemical Co | Modular, curved structure and method of assembly |
DE1481543A1 (de) * | 1967-01-31 | 1969-10-23 | Entwicklungsring Sued Gmbh | Duese fuer Strahltriebwerk |
FR1590144A (es) * | 1968-08-08 | 1970-04-13 | ||
DE2232114B2 (de) * | 1972-06-30 | 1975-05-22 | Max Dr.-Ing. 8700 Wuerzburg Mengeringhausen | Kuppeiförmiges Gebäude |
US4067094A (en) * | 1976-04-26 | 1978-01-10 | Harry Feick Co., Inc. | Load bearing vane structure for thrust reversal |
US4278220A (en) * | 1979-03-30 | 1981-07-14 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Thrust reverser for a long duct fan engine |
US4778110A (en) * | 1982-09-30 | 1988-10-18 | Rohr Industries, Inc. | Modular composite cascade assembly |
FR2540536A1 (fr) * | 1983-02-04 | 1984-08-10 | Chamayou Gerard | Element de couverture et dome realise a partir d'un tel element |
US4596621A (en) * | 1984-01-03 | 1986-06-24 | The Boeing Company | Method of making a composite bond cascade for a thrust reverser unit of an aircraft engine nacelle |
FR2590375B1 (fr) * | 1985-11-19 | 1987-12-31 | Chamayou Gerard | Ecran courbe, notamment ecran de projection cinematographique |
GB8812783D0 (en) * | 1988-05-28 | 1988-06-29 | Pengelley L N | Guide frame for locating cladding elements |
-
1994
- 1994-04-01 US US08/222,317 patent/US5507143A/en not_active Expired - Fee Related
- 1994-04-13 DE DE69420555T patent/DE69420555T2/de not_active Expired - Fee Related
- 1994-04-13 AU AU67685/94A patent/AU6768594A/en not_active Abandoned
- 1994-04-13 EP EP94915796A patent/EP0699273B1/en not_active Expired - Lifetime
- 1994-04-13 WO PCT/US1994/004097 patent/WO1994024430A1/en active IP Right Grant
- 1994-04-13 ES ES94915796T patent/ES2135579T3/es not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
WO1994024430A1 (en) | 1994-10-27 |
AU6768594A (en) | 1994-11-08 |
US5507143A (en) | 1996-04-16 |
DE69420555T2 (de) | 1999-12-23 |
EP0699273A1 (en) | 1996-03-06 |
DE69420555D1 (de) | 1999-10-14 |
EP0699273B1 (en) | 1999-09-08 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
FG2A | Definitive protection |
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