FR2615906B1 - Reacteur combine, commutable, pour l'entrainement d'avions et d'engins speciaux - Google Patents
Reacteur combine, commutable, pour l'entrainement d'avions et d'engins speciauxInfo
- Publication number
- FR2615906B1 FR2615906B1 FR8807090A FR8807090A FR2615906B1 FR 2615906 B1 FR2615906 B1 FR 2615906B1 FR 8807090 A FR8807090 A FR 8807090A FR 8807090 A FR8807090 A FR 8807090A FR 2615906 B1 FR2615906 B1 FR 2615906B1
- Authority
- FR
- France
- Prior art keywords
- combined
- special machinery
- driving aircraft
- switchable reactor
- switchable
- 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 - Fee Related
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D7/00—Rotors with blades adjustable in operation; Control thereof
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- 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
- F02K1/06—Varying effective area of jet pipe or nozzle
- F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
-
- 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
-
- 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
- F02K7/18—Composite ram-jet/rocket engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/74—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant
- F02K9/78—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof combined with another jet-propulsion plant with an air-breathing jet-propulsion plant
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
- F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
- F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE3717968 | 1987-05-27 | ||
DE19873738703 DE3738703A1 (de) | 1987-05-27 | 1987-11-14 | Kombiniertes, umschaltbares strahltriebwerk zum antrieb von flugzeugen und raumfahrzeugen |
Publications (2)
Publication Number | Publication Date |
---|---|
FR2615906A1 FR2615906A1 (fr) | 1988-12-02 |
FR2615906B1 true FR2615906B1 (fr) | 1994-05-06 |
Family
ID=25856090
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
FR8807090A Expired - Fee Related FR2615906B1 (fr) | 1987-05-27 | 1988-05-27 | Reacteur combine, commutable, pour l'entrainement d'avions et d'engins speciaux |
Country Status (4)
Country | Link |
---|---|
US (1) | US4909031A (fr) |
DE (1) | DE3738703A1 (fr) |
FR (1) | FR2615906B1 (fr) |
GB (1) | GB2205360B (fr) |
Families Citing this family (76)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3836912A1 (de) * | 1988-09-01 | 1990-03-15 | Mtu Muenchen Gmbh | Verfahren zur brennstoffzufuehrung |
FR2637018A1 (fr) * | 1988-09-28 | 1990-03-30 | Snecma | Dispositif d'injection de gaz pour propulseur combine turbo-stato-fusee |
FR2637017B1 (fr) * | 1988-09-28 | 1990-11-30 | Snecma | Structure de tuyere pour propulseur combine turbo-stato-fusee |
US5052176A (en) * | 1988-09-28 | 1991-10-01 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation | Combination turbojet-ramjet-rocket propulsion system |
US5105615A (en) * | 1989-02-03 | 1992-04-21 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Turbojet engine with at least one axially movable arranged sliding valve |
DE3909050C1 (fr) * | 1989-03-18 | 1990-08-16 | Messerschmitt-Boelkow-Blohm Gmbh, 8012 Ottobrunn, De | |
DE3911715A1 (de) * | 1989-04-10 | 1990-10-11 | Mtu Muenchen Gmbh | Absperreinrichtung fuer geblaese-, insbesondere geblaese-staustrahltriebwerke |
DE3912330A1 (de) * | 1989-04-14 | 1990-10-18 | Mtu Muenchen Gmbh | Integriertes turbo-staustrahltriebwerk |
DE3912392A1 (de) * | 1989-04-14 | 1990-10-25 | Mtu Muenchen Gmbh | Turbinen-staustrahltriebwerk |
FR2648517B1 (fr) * | 1989-06-14 | 1994-04-01 | Snecma | Propulseur combine turbofusee statoreacteur a rechauffe et son procede de fonctionnement |
DE3935313C1 (fr) * | 1989-10-24 | 1991-06-06 | Mtu Muenchen Gmbh | |
DE3942323C2 (de) * | 1989-12-21 | 1993-11-25 | Mtu Muenchen Gmbh | Einlaufkonfiguration für ein kombiniertes Turbo-Staustrahltriebwerk |
FR2656382B1 (fr) * | 1989-12-21 | 1994-07-08 | Europ Propulsion | Moteur a propulsion combinee a haute adaptabilite pour aeronef ou avion spatial. |
US5694768A (en) * | 1990-02-23 | 1997-12-09 | General Electric Company | Variable cycle turbofan-ramjet engine |
DE4111396A1 (de) * | 1990-04-14 | 1991-10-02 | Kastens Karl | Turbotriebwerk fuer hyperschallfluggeraete |
DE4012103C1 (en) * | 1990-04-14 | 1991-07-25 | Karl Dipl.-Ing. 2742 Gnarrenburg De Kastens | Hypersonic aircraft reaction drive - has flow tube with frontal air entry slot and trough at trailing end |
FR2682719B1 (fr) * | 1991-10-16 | 1995-03-24 | Snecma | Moteur pour vehicule hypersonique a fonctionnements turboreacteur et statoreacteur. |
FR2687433B1 (fr) * | 1992-02-14 | 1994-05-06 | Onera | Propulseur a composants inverses, a alimentation modulee. |
EP0560453A1 (fr) * | 1992-03-10 | 1993-09-15 | The Boeing Company | Turboréacteur avec compresseur supersonique |
FR2692939B1 (fr) * | 1992-06-24 | 1994-09-02 | Snecma | Réacteur combiné en statoréacteur et turboréacteur. |
US5831155A (en) * | 1996-12-02 | 1998-11-03 | Atlantic Research Corporation | Apparatus and method for simulating rocket-to-ramjet transition in a propulsion system |
WO1998025021A1 (fr) * | 1996-12-02 | 1998-06-11 | Alexandr Evgenievich Yashin | Moteur combine pour aeronefs |
FR2819556B1 (fr) * | 2001-01-12 | 2003-04-04 | Aerospatiale Matra Missiles | Systeme d'obturation pour un orifice d'un conduit, en particulier pour un orifice d'une voie d'introduction d'air dans la chambre de combustion d'un statoreacteur |
US6901739B2 (en) * | 2003-10-07 | 2005-06-07 | General Electric Company | Gas turbine engine with variable pressure ratio fan system |
DE102004026367B4 (de) * | 2004-05-29 | 2014-05-28 | MTU Aero Engines AG | Turbomaschine |
DE102004042739A1 (de) * | 2004-09-03 | 2006-03-09 | Mtu Aero Engines Gmbh | Fan für ein Flugtriebwerk sowie Flugtriebwerk |
US20060086078A1 (en) * | 2004-10-21 | 2006-04-27 | Paul Marius A | Universal Carnot propulsion systems for turbo rocketry |
US7334392B2 (en) * | 2004-10-29 | 2008-02-26 | General Electric Company | Counter-rotating gas turbine engine and method of assembling same |
WO2007013058A2 (fr) * | 2005-07-27 | 2007-02-01 | Aryeh Yaakov Kohn | Systeme de propulsion d'aeronef/d'engin spatial deployable et procedes |
US7603844B2 (en) * | 2005-10-19 | 2009-10-20 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7726113B2 (en) * | 2005-10-19 | 2010-06-01 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7752836B2 (en) * | 2005-10-19 | 2010-07-13 | General Electric Company | Gas turbine assembly and methods of assembling same |
US7493754B2 (en) * | 2005-10-19 | 2009-02-24 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7685808B2 (en) * | 2005-10-19 | 2010-03-30 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US7490461B2 (en) * | 2005-10-19 | 2009-02-17 | General Electric Company | Gas turbine engine assembly and methods of assembling same |
US20070138886A1 (en) * | 2005-10-25 | 2007-06-21 | Massachusetts Institute Of Technology | Converting Rotational Motion into Radial Motion |
EA015726B1 (ru) * | 2006-10-30 | 2011-10-31 | Денис Анатольевич Катковский | Комбинированный реактивный многорежимный двигатель |
US7765789B2 (en) * | 2006-12-15 | 2010-08-03 | General Electric Company | Apparatus and method for assembling gas turbine engines |
US20100229568A1 (en) * | 2007-08-02 | 2010-09-16 | Kevork Nercessian | Gas turbine engine |
US8015798B2 (en) * | 2007-12-13 | 2011-09-13 | United Technologies Corporation | Geared counter-rotating gas turbofan engine |
GR20100100340A (el) * | 2010-06-07 | 2012-01-31 | Ανδρεας Ανδριανος | Στροβιλοαντιδραστηρας διπλης ροης, μεταβλητου κυκλου, με στροβιλους αντιστροφων φορων, με θαλαμο καυσης χωρις περιοχη διαλυσης, με ψυχομενο στροβιλο υψηλης πιεσης χωρις πτερυγια σταθερου περιβληματος,με θερμοδυναμικο κυκλο πολυ υψηλης θερμοκρασιας και με θερμικο καταλυτη διασπασης υδρογονανθρακων η/και υδατος σε υδρογονο |
DE102010023998A1 (de) | 2010-06-16 | 2011-12-22 | Mtu Aero Engines Gmbh | Strömungskanal mit veränderlicher Kanalgeometrie |
US9109539B2 (en) | 2010-12-27 | 2015-08-18 | Rolls-Royce North American Technologies, Inc. | Turbine based combined cycle engine |
US9279388B2 (en) * | 2011-11-01 | 2016-03-08 | United Technologies Corporation | Gas turbine engine with two-spool fan and variable vane turbine |
US9845726B2 (en) | 2012-01-31 | 2017-12-19 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section |
US10287914B2 (en) | 2012-01-31 | 2019-05-14 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section and bearing support features |
US10240526B2 (en) | 2012-01-31 | 2019-03-26 | United Technologies Corporation | Gas turbine engine with high speed low pressure turbine section |
US20130192263A1 (en) * | 2012-01-31 | 2013-08-01 | Gabriel L. Suciu | Gas turbine engine with high speed low pressure turbine section |
US10125693B2 (en) | 2012-04-02 | 2018-11-13 | United Technologies Corporation | Geared turbofan engine with power density range |
US8690097B1 (en) | 2012-04-30 | 2014-04-08 | The Boeing Company | Variable-geometry rotating spiral cone engine inlet compression system and method |
WO2014186018A2 (fr) | 2013-03-13 | 2014-11-20 | United Technologies Corporation | Support de coiffe |
EP3039276B1 (fr) * | 2013-08-29 | 2019-12-25 | United Technologies Corporation | Réacteur triple corps à réducteur avec pignon de commande de compresseur basse pression et contrôleur mécanique |
DE102014000991A1 (de) * | 2014-01-29 | 2015-07-30 | Bayern Chemie Gmbh | Flugkörper mit Turbine-Verdichter-Einheit |
US20160102609A1 (en) * | 2014-10-09 | 2016-04-14 | United Technologies Corporation | Pulse detonation combustor |
US11041463B1 (en) * | 2015-02-11 | 2021-06-22 | Raytheon Technologies Corporation | Turbine engine structure with oxidizer enhanced mode |
US10801442B2 (en) | 2017-02-08 | 2020-10-13 | General Electric Company | Counter rotating turbine with reversing reduction gear assembly |
US10823114B2 (en) | 2017-02-08 | 2020-11-03 | General Electric Company | Counter rotating turbine with reversing reduction gearbox |
US10465606B2 (en) | 2017-02-08 | 2019-11-05 | General Electric Company | Counter rotating turbine with reversing reduction gearbox |
US10663036B2 (en) | 2017-06-13 | 2020-05-26 | General Electric Company | Gas turbine engine with rotating reversing compound gearbox |
DE102017211865A1 (de) * | 2017-07-11 | 2019-01-17 | MTU Aero Engines AG | Strömungsmaschine mit Turbine |
US10815881B2 (en) | 2017-09-20 | 2020-10-27 | General Electric Company | Counter rotating turbine with reversing speed reduction assembly |
US11008883B2 (en) | 2017-09-20 | 2021-05-18 | General Electric Company | Turbomachine with a gearbox and integrated electric machine assembly |
US10329201B2 (en) | 2017-09-21 | 2019-06-25 | General Electric Company | Ceramic matrix composite articles formation method |
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US11156128B2 (en) | 2018-08-22 | 2021-10-26 | General Electric Company | Embedded electric machine |
GB201820924D0 (en) * | 2018-12-21 | 2019-02-06 | Rolls Royce Plc | Turbine engine |
US11261791B2 (en) | 2019-02-25 | 2022-03-01 | Rolls-Royce Corporation | Hybrid propulsion cooling system |
US11118535B2 (en) | 2019-03-05 | 2021-09-14 | General Electric Company | Reversing gear assembly for a turbo machine |
GB2582529B (en) * | 2020-06-25 | 2021-03-24 | Qureshi Sarah | A supersonic turbofan engine |
CN112727635B (zh) * | 2020-12-31 | 2022-04-26 | 中国航空发动机研究院 | 一种双外涵发动机 |
US11428160B2 (en) | 2020-12-31 | 2022-08-30 | General Electric Company | Gas turbine engine with interdigitated turbine and gear assembly |
US20220389884A1 (en) * | 2021-06-04 | 2022-12-08 | Raytheon Technologies Corporation | Variable cycle jet engine |
CN114704407A (zh) * | 2021-08-10 | 2022-07-05 | 中国电子科技集团公司第三十八研究所 | 一种多级涡轮风扇发动机 |
CN114439646B (zh) * | 2022-01-27 | 2022-12-06 | 西北工业大学 | 空气涡轮火箭冲压组合推进*** |
CN114837811A (zh) * | 2022-04-19 | 2022-08-02 | 南京航空航天大学 | 一种延伸外机匣的组合动力模态转换方法 |
US20240093644A1 (en) * | 2022-09-16 | 2024-03-21 | General Electric Company | Gas turbine engines with a fuel cell assembly |
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GB133834A (fr) * | ||||
US3296800A (en) * | 1967-01-10 | Gas turbine power plant | ||
FR923996A (fr) * | 1946-02-15 | 1947-07-23 | Propulseur rotatif canalisé | |
US2635420A (en) * | 1947-05-14 | 1953-04-21 | Shell Dev | Jet propulsion engine with auxiliary pulse jet engine |
US2672726A (en) * | 1950-09-19 | 1954-03-23 | Bell Aircraft Corp | Ducted fan jet aircraft engine |
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FR79090E (fr) * | 1960-07-11 | 1962-10-19 | Nord Aviation | Combiné turboréacteur-statoréacteur |
FR1271544A (fr) * | 1960-07-11 | 1961-09-15 | Nord Aviation | Combiné turboréacteur-statoréacteur |
FR1325056A (fr) * | 1962-03-15 | 1963-04-26 | Nord Aviation | Perfectionnements aux combinés turboréacteur-statoréacteur |
FR1377199A (fr) * | 1963-12-17 | 1964-10-31 | Rolls Royce | Moteur à turbine à gaz |
FR1496091A (fr) * | 1966-04-20 | 1967-09-29 | Snecma | Tuyère d'éjection pour propulseurs à plusieurs flux moteurs, notamment à deux flux moteurs |
FR2141435B1 (fr) * | 1971-06-02 | 1973-06-29 | Snecma | |
US4137708A (en) * | 1973-07-02 | 1979-02-06 | General Motors Corporation | Jet propulsion |
US4185457A (en) * | 1976-01-28 | 1980-01-29 | United Technologies Corporation | Turbofan-ramjet engine |
US4159624A (en) * | 1978-02-06 | 1979-07-03 | Gruner George P | Contra-rotating rotors with differential gearing |
US4543785A (en) * | 1982-07-07 | 1985-10-01 | Hugh Patrick | Turbo-ram-jet engine |
GB2155110A (en) * | 1984-03-02 | 1985-09-18 | Gen Electric | High bypass ratio counter-rotating turbofan engine |
DE3617915C1 (de) * | 1986-05-28 | 1987-09-17 | Messerschmitt Boelkow Blohm | Kombinationsantrieb |
-
1987
- 1987-11-14 DE DE19873738703 patent/DE3738703A1/de active Granted
-
1988
- 1988-05-27 US US07/199,901 patent/US4909031A/en not_active Expired - Fee Related
- 1988-05-27 FR FR8807090A patent/FR2615906B1/fr not_active Expired - Fee Related
- 1988-05-27 GB GB8812678A patent/GB2205360B/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
DE3738703A1 (de) | 1988-12-08 |
DE3738703C2 (fr) | 1990-10-31 |
US4909031A (en) | 1990-03-20 |
GB8812678D0 (en) | 1988-06-29 |
FR2615906A1 (fr) | 1988-12-02 |
GB2205360A (en) | 1988-12-07 |
GB2205360B (en) | 1992-01-22 |
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