FR2099597A7 - - Google Patents

Info

Publication number
FR2099597A7
FR2099597A7 FR7046318A FR7046318A FR2099597A7 FR 2099597 A7 FR2099597 A7 FR 2099597A7 FR 7046318 A FR7046318 A FR 7046318A FR 7046318 A FR7046318 A FR 7046318A FR 2099597 A7 FR2099597 A7 FR 2099597A7
Authority
FR
France
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
Application number
FR7046318A
Other languages
French (fr)
Other versions
FR2099597B3 (en
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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
Application filed by MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of FR2099597A7 publication Critical patent/FR2099597A7/fr
Application granted granted Critical
Publication of FR2099597B3 publication Critical patent/FR2099597B3/fr
Expired legal-status Critical Current

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
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F02K1/004—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector by using one or more swivable nozzles rotating about their own axis
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
    • B64C29/0066—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors with horizontal jet and jet deflector
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/328—Application in turbines in gas turbines providing direct vertical lift
FR7046318A 1970-07-25 1970-12-22 Expired FR2099597B3 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19702037049 DE2037049A1 (en) 1970-07-25 1970-07-25 More waves turbine jet engine

Publications (2)

Publication Number Publication Date
FR2099597A7 true FR2099597A7 (en) 1972-03-17
FR2099597B3 FR2099597B3 (en) 1973-04-27

Family

ID=5777928

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7046318A Expired FR2099597B3 (en) 1970-07-25 1970-12-22

Country Status (3)

Country Link
DE (1) DE2037049A1 (en)
FR (1) FR2099597B3 (en)
GB (1) GB1351000A (en)

Families Citing this family (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4713935A (en) * 1986-04-08 1987-12-22 Rolls-Royce Inc. Vectorable nozzles for aircraft
DE4426195C2 (en) * 1994-07-23 1998-02-05 Daimler Benz Aerospace Ag Rectangular thruster for jet engines
DE10033653A1 (en) * 2000-06-16 2002-03-07 Sandor Nagy Drive system for e.g. aircraft, is formed multistage with drives units such that the drive system is combined with at least one negative pressure system
DE10126632A1 (en) * 2000-08-08 2002-09-12 Sandor Nagy Combination propulsion system pref. for aircraft has thrust vector control, also useable as lifting device, located behind multistage vacuum system or ram jet engines
EP1828547B1 (en) 2004-12-01 2011-11-30 United Technologies Corporation Turbofan comprising a plurality of individually controlled inlet guide vanes and corresponding controlling method
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
WO2006110122A2 (en) 2004-12-01 2006-10-19 United Technologies Corporation Inflatable bleed valve for a turbine engine and a method of operating therefore
WO2006059970A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
EP1825113B1 (en) 2004-12-01 2012-10-24 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
WO2006059972A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
WO2006110123A2 (en) * 2004-12-01 2006-10-19 United Technologies Corporation Vectoring transition duct for turbine engine
WO2006059985A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Axial compressor for tip turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
CN105134407B (en) * 2015-08-20 2017-08-01 南京航空航天大学 Venturi offset fluidic vectoring nozzle and control method with VTOL function

Also Published As

Publication number Publication date
GB1351000A (en) 1974-04-24
DE2037049A1 (en) 1972-02-03
FR2099597B3 (en) 1973-04-27

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Legal Events

Date Code Title Description
ST Notification of lapse