BR112013011513A2 - ''sistema integrado de restritor de fluxo e motor de turbina a gás'' - Google Patents

''sistema integrado de restritor de fluxo e motor de turbina a gás''

Info

Publication number
BR112013011513A2
BR112013011513A2 BR112013011513A BR112013011513A BR112013011513A2 BR 112013011513 A2 BR112013011513 A2 BR 112013011513A2 BR 112013011513 A BR112013011513 A BR 112013011513A BR 112013011513 A BR112013011513 A BR 112013011513A BR 112013011513 A2 BR112013011513 A2 BR 112013011513A2
Authority
BR
Brazil
Prior art keywords
gas turbine
turbine engine
flow restrictor
integrated gas
engine flow
Prior art date
Application number
BR112013011513A
Other languages
English (en)
Inventor
Michel Anthony Ruthemeyer
Original Assignee
Gen Electric Campany
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 Gen Electric Campany filed Critical Gen Electric Campany
Publication of BR112013011513A2 publication Critical patent/BR112013011513A2/pt

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • 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
    • F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/13—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having variable working fluid interconnections between turbines or compressors or stages of different rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • F02C7/143—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid before or between the compressor stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F02C7/185—Cooling means for reducing the temperature of the cooling air or gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • 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
    • 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
    • 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
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure
    • 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
    • F28—HEAT EXCHANGE IN GENERAL
    • F28D—HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT
    • F28D11/00—Heat-exchange apparatus employing moving conduits
    • F28D11/02—Heat-exchange apparatus employing moving conduits the movement being rotary, e.g. performed by a drum or roller
    • F28D11/04—Heat-exchange apparatus employing moving conduits the movement being rotary, e.g. performed by a drum or roller performed by a tube or a bundle of tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F1/00—Tubular elements; Assemblies of tubular elements
    • F28F1/02—Tubular elements of cross-section which is non-circular
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F28—HEAT EXCHANGE IN GENERAL
    • F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
    • F28F13/00—Arrangements for modifying heat-transfer, e.g. increasing, decreasing
    • F28F13/06—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media
    • F28F13/08—Arrangements for modifying heat-transfer, e.g. increasing, decreasing by affecting the pattern of flow of the heat-exchange media by varying the cross-section of the flow channels
    • 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
    • F05D2260/50—Kinematic linkage, i.e. transmission of position
    • F05D2260/56—Kinematic linkage, i.e. transmission of position using cams or eccentrics
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Fluid Mechanics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)
BR112013011513A 2010-11-22 2011-11-09 ''sistema integrado de restritor de fluxo e motor de turbina a gás'' BR112013011513A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US12/951,178 US8961114B2 (en) 2010-11-22 2010-11-22 Integrated variable geometry flow restrictor and heat exchanger
PCT/US2011/059664 WO2012071166A2 (en) 2010-11-22 2011-11-08 Integrated variable geometry flow restrictor and heat exchanger

Publications (1)

Publication Number Publication Date
BR112013011513A2 true BR112013011513A2 (pt) 2016-08-09

Family

ID=45048225

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112013011513A BR112013011513A2 (pt) 2010-11-22 2011-11-09 ''sistema integrado de restritor de fluxo e motor de turbina a gás''

Country Status (7)

Country Link
US (1) US8961114B2 (pt)
EP (1) EP2643557B1 (pt)
JP (1) JP5968329B2 (pt)
CN (1) CN103502580B (pt)
BR (1) BR112013011513A2 (pt)
CA (1) CA2817526A1 (pt)
WO (1) WO2012071166A2 (pt)

Families Citing this family (48)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013147953A1 (en) * 2011-12-30 2013-10-03 Rolls-Royce North American Technologies Inc. Aircraft propulsion gas turbine engine with heat exchange
EP2971724B1 (en) * 2013-03-13 2020-05-06 Rolls-Royce North American Technologies, Inc. Compact actuation system for a gas turbine engine exhaust nozzle
EP2971739B1 (en) * 2013-03-14 2020-03-18 Rolls-Royce North American Technologies, Inc. Gas turbine engine flow duct having two rows of integrated heat exchangers
EP2971604B1 (en) * 2013-03-15 2020-06-10 Rolls-Royce North American Technologies, Inc. Heat exchanger integrated with a gas turbine engine and adaptive flow control
GB201305432D0 (en) * 2013-03-26 2013-05-08 Rolls Royce Plc A gas turbine engine cooling arrangement
EP3017169B1 (en) * 2013-07-05 2019-11-27 United Technologies Corporation Gas turbine engine system for modulating flow of fan by-pass air and core engine air and corresponding method
US10072584B2 (en) 2013-12-03 2018-09-11 United Technologies Corporation Multi-bypass stream gas turbine engine with enlarged bypass flow area
WO2015138020A2 (en) * 2013-12-18 2015-09-17 United Technologies Corporation Heat exchanger flow control assembly
US10443428B2 (en) 2014-02-19 2019-10-15 United Technologies Corporation Gas turbine engine having minimum cooling airflow
US9574518B2 (en) * 2014-06-02 2017-02-21 The Boeing Company Turbofan engine with variable exhaust cooling
US10907500B2 (en) * 2015-02-06 2021-02-02 Raytheon Technologies Corporation Heat exchanger system with spatially varied additively manufactured heat transfer surfaces
US9896998B2 (en) 2015-02-20 2018-02-20 Pratt & Whitney Canada Corp. Compound engine assembly with modulated flow
US9932892B2 (en) 2015-02-20 2018-04-03 Pratt & Whitney Canada Corp. Compound engine assembly with coaxial compressor and offset turbine section
US9879591B2 (en) 2015-02-20 2018-01-30 Pratt & Whitney Canada Corp. Engine intake assembly with selector valve
US9797297B2 (en) 2015-02-20 2017-10-24 Pratt & Whitney Canada Corp. Compound engine assembly with common inlet
FR3034466B1 (fr) * 2015-04-03 2018-03-16 Safran Helicopter Engines Limiteur de debit
US10107200B2 (en) 2015-04-30 2018-10-23 General Electric Company Turbine engine thermal management
DE102015224701A1 (de) * 2015-12-09 2017-06-14 Rolls-Royce Deutschland Ltd & Co Kg Fluggasturbine mit variabler Austrittsdüse eines Nebenstromkanals
US11125160B2 (en) * 2015-12-28 2021-09-21 General Electric Company Method and system for combination heat exchanger
US10533784B2 (en) 2016-03-16 2020-01-14 Hamilton Sundstrand Corporation Pack-and-A-half architecture for environmental control systems
JP2017223212A (ja) * 2016-06-16 2017-12-21 早川　秀樹 エンジンと多目的ファンモーターターボ
US10494949B2 (en) * 2016-08-05 2019-12-03 General Electric Company Oil cooling systems for a gas turbine engine
US10371063B2 (en) * 2016-11-29 2019-08-06 General Electric Company Turbine engine and method of cooling thereof
US10495108B2 (en) * 2017-01-31 2019-12-03 Honeywell International Inc. Variable vane devices containing rotationally-driven translating vane structures and methods for the production thereof
DE102017104036A1 (de) * 2017-02-27 2018-08-30 Rolls-Royce Deutschland Ltd & Co Kg Konvergent-divergente Schubdüse für ein Turbofan-Triebwerk eines Überschallflugzeugs und Verfahren zur Einstellung der Düsenhalsfläche in einer Schubdüse eines Turbofan-Triebwerks
US10364750B2 (en) 2017-10-30 2019-07-30 General Electric Company Thermal management system
US10941706B2 (en) 2018-02-13 2021-03-09 General Electric Company Closed cycle heat engine for a gas turbine engine
US11143104B2 (en) 2018-02-20 2021-10-12 General Electric Company Thermal management system
US11015534B2 (en) 2018-11-28 2021-05-25 General Electric Company Thermal management system
US11512667B2 (en) 2019-02-25 2022-11-29 Rolls-Royce North American Technologies Inc. Anti-unstart for combined cycle high mach vehicles
US11378009B2 (en) 2019-05-15 2022-07-05 Raytheon Technologies Corporation Multi-mode heat rejection system for a gas turbine engine
US11168584B2 (en) * 2019-06-28 2021-11-09 The Boeing Company Thermal management system using shape memory alloy actuator
FR3099204B1 (fr) * 2019-07-24 2022-12-23 Safran Aircraft Engines Etage redresseur de turbomachine avec passage de fuite d’air de refroidissement a section variable suivant orientation des aubes
US11492971B2 (en) 2019-09-06 2022-11-08 Raytheon Technologies Corporation Turbine engine system with heat exchanger in bypassable secondary duct
US11519368B2 (en) 2020-01-07 2022-12-06 Raytheon Technologies Corporation Heat exchanger supply plenum
US11703283B2 (en) 2020-01-24 2023-07-18 Hamilton Sundstrand Corporation Radial configuration for heat exchanger core
US11460252B2 (en) 2020-01-24 2022-10-04 Hamilton Sundstrand Corporation Header arrangement for additively manufactured heat exchanger
US11453160B2 (en) 2020-01-24 2022-09-27 Hamilton Sundstrand Corporation Method of building a heat exchanger
US11441850B2 (en) 2020-01-24 2022-09-13 Hamilton Sundstrand Corporation Integral mounting arm for heat exchanger
US11781506B2 (en) 2020-06-03 2023-10-10 Rtx Corporation Splitter and guide vane arrangement for gas turbine engines
US11371374B2 (en) * 2020-07-22 2022-06-28 Raytheon Technologies Corporation Seal runner flow damper
US11459909B2 (en) * 2020-09-15 2022-10-04 Pratt & Whitney Canada Corp. Rotating heat exchanger
EP4015796A3 (en) * 2020-12-18 2022-08-17 The Boeing Company Systems and methods for expanding an operating speed range of a high speed flight vehicle
US11965697B2 (en) * 2021-03-02 2024-04-23 General Electric Company Multi-fluid heat exchanger
CN112963861B (zh) * 2021-03-11 2022-08-30 哈尔滨工业大学 一种换热面积可分配式双燃料预冷器
US11525399B1 (en) * 2021-06-17 2022-12-13 Pratt & Whitney Canada Corp. Oil system with flow restrictor
US11946415B2 (en) * 2021-09-09 2024-04-02 General Electric Company Waste heat recovery system
CN115182815B (zh) * 2022-05-31 2024-04-19 中国航发四川燃气涡轮研究院 具有可变几何的多涵道变循环加力燃烧室

Family Cites Families (47)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3528250A (en) * 1969-04-16 1970-09-15 Gen Motors Corp Bypass engine with afterburning and compressor bleed air heat exchanger in bypass duct
US3735588A (en) * 1971-07-21 1973-05-29 Curtiss Wright Corp Heat exchanger leakage baffle and positioning means
CA1020365A (en) 1974-02-25 1977-11-08 James E. Johnson Modulating bypass variable cycle turbofan engine
US4069661A (en) 1975-06-02 1978-01-24 The United States Of America As Represented By The United States National Aeronautics And Space Administration Variable mixer propulsion cycle
US4064692A (en) 1975-06-02 1977-12-27 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Variable cycle gas turbine engines
US4010608A (en) 1975-06-16 1977-03-08 General Electric Company Split fan work gas turbine engine
US4068471A (en) 1975-06-16 1978-01-17 General Electric Company Variable cycle engine with split fan section
US4072008A (en) 1976-05-04 1978-02-07 General Electric Company Variable area bypass injector system
US4222233A (en) 1977-08-02 1980-09-16 General Electric Company Auxiliary lift propulsion system with oversized front fan
US4175384A (en) 1977-08-02 1979-11-27 General Electric Company Individual bypass injector valves for a double bypass variable cycle turbofan engine
US4187675A (en) 1977-10-14 1980-02-12 The United States Of America As Represented By The Secretary Of The Air Force Compact air-to-air heat exchanger for jet engine application
US4214851A (en) 1978-04-20 1980-07-29 General Electric Company Structural cooling air manifold for a gas turbine engine
US4292802A (en) 1978-12-27 1981-10-06 General Electric Company Method and apparatus for increasing compressor inlet pressure
US4409788A (en) 1979-04-23 1983-10-18 General Electric Company Actuation system for use on a gas turbine engine
US5694767A (en) 1981-11-02 1997-12-09 General Electric Company Variable slot bypass injector system
GB2210935B (en) 1987-10-10 1992-05-27 Rolls Royce Plc Variable stator vane assembly
US5307624A (en) 1990-04-04 1994-05-03 General Electric Company Variable area bypass valve assembly
US5269133A (en) 1991-06-18 1993-12-14 General Electric Company Heat exchanger for cooling a gas turbine
US5287697A (en) 1992-01-02 1994-02-22 General Electric Company Variable area bypass injector seal
JPH0566253U (ja) * 1992-02-17 1993-09-03 石川島播磨重工業株式会社 ターボファンエンジンのバイパス比可変構造
CA2091473A1 (en) * 1992-04-20 1993-10-21 Mark J. Wagner Bypass injector valve for variable cycle aircraft engines
US5259187A (en) 1993-02-05 1993-11-09 General Electric Company Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes
US6374612B1 (en) * 2000-09-21 2002-04-23 Caterpillar Inc. Interstage cooling of a multi-compressor turbocharger
AU2001213231A1 (en) 2000-11-10 2002-05-21 Marek Kovac Bypass gas turbine engine and cooling method for working fluid
ITTO20010446A1 (it) 2001-05-11 2002-11-11 Fiatavio Spa Paletta per uno statore di una turbina a geometria variabile, in particolare per motori aeronautici.
US6901739B2 (en) * 2003-10-07 2005-06-07 General Electric Company Gas turbine engine with variable pressure ratio fan system
US7254937B2 (en) 2004-04-21 2007-08-14 General Electric Company Gas turbine heat exchanger assembly and method for fabricating same
US7475532B2 (en) * 2005-08-29 2009-01-13 General Electric Company Valve assembly for a gas turbine engine
US7730714B2 (en) 2005-11-29 2010-06-08 General Electric Company Turbofan gas turbine engine with variable fan outlet guide vanes
US8127828B2 (en) * 2006-03-17 2012-03-06 United Technologies Corporation Air-oil heat exchanger
GB0607771D0 (en) 2006-04-20 2006-05-31 Rolls Royce Plc A heat exchanger arrangement
GB2437295B (en) * 2006-04-20 2008-06-25 Rolls Royce Plc Aeroengine ventilation system
US7765788B2 (en) 2006-07-06 2010-08-03 United Technologies Corporation Cooling exchanger duct
US7758303B1 (en) 2006-07-31 2010-07-20 General Electric Company FLADE fan with different inner and outer airfoil stagger angles at a shroud therebetween
US20080028763A1 (en) 2006-08-03 2008-02-07 United Technologies Corporation Thermal management system with thrust recovery for a gas turbine engine fan nacelle assembly
US8387362B2 (en) * 2006-10-19 2013-03-05 Michael Ralph Storage Method and apparatus for operating gas turbine engine heat exchangers
US7765789B2 (en) 2006-12-15 2010-08-03 General Electric Company Apparatus and method for assembling gas turbine engines
EP1944475B1 (en) * 2007-01-08 2015-08-12 United Technologies Corporation Heat exchange system
US7721549B2 (en) 2007-02-08 2010-05-25 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle with cam drive ring actuation system
WO2008108847A1 (en) 2007-03-05 2008-09-12 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle with drive ring actuation system
US7837436B2 (en) 2007-05-25 2010-11-23 General Electric Company Method and apparatus for regulating fluid flow through a turbine engine
US7870741B2 (en) 2007-05-25 2011-01-18 General Electric Company Turbine engine valve assembly and method of assembling the same
US7942632B2 (en) 2007-06-20 2011-05-17 United Technologies Corporation Variable-shape variable-stagger inlet guide vane flap
US7836680B2 (en) 2007-06-20 2010-11-23 United Technologies Corporation Aircraft combination engines thermal management system
US8333552B2 (en) 2008-06-20 2012-12-18 General Electric Company Combined acoustic absorber and heat exchanging outlet guide vanes
US8127532B2 (en) 2008-11-26 2012-03-06 The Boeing Company Pivoting fan nozzle nacelle
US8162603B2 (en) 2009-01-30 2012-04-24 General Electric Company Vane frame for a turbomachine and method of minimizing weight thereof

Also Published As

Publication number Publication date
JP5968329B2 (ja) 2016-08-10
US20120128467A1 (en) 2012-05-24
JP2014501871A (ja) 2014-01-23
CA2817526A1 (en) 2012-05-31
WO2012071166A2 (en) 2012-05-31
EP2643557A2 (en) 2013-10-02
EP2643557B1 (en) 2017-01-11
WO2012071166A3 (en) 2013-06-20
US8961114B2 (en) 2015-02-24
CN103502580B (zh) 2016-06-01
CN103502580A (zh) 2014-01-08

Similar Documents

Publication Publication Date Title
BR112013011513A2 (pt) ''sistema integrado de restritor de fluxo e motor de turbina a gás''
BR112014007288A2 (pt) motor de turbina a gás
BR112013030379A2 (pt) ''motor de turbina a gás compreendendo três corpos rotativos''
BR112014031175A2 (pt) motor de turbina a gás e conduto de fluido.
BR112014016305A8 (pt) motor de turbina a gás
BR112014016277A8 (pt) motor de turbina a gás
BR112014007878A2 (pt) motor de turbina a gás
BR112014016303A2 (pt) motor de turbina a gás
BR112014016273A8 (pt) motor de turbina a gás
BR112013006893A2 (pt) sistema de mecanismo motor e método
BRPI0916416A2 (pt) sistema de turbirna flutuante
BR112014026533A2 (pt) montagem de motor de turbina a gás.
BRPI0822487A2 (pt) sistema de gerador de turbina eólica
BR112012000954A2 (pt) conjunto turbocompressor com um sistema de resfriamento
DE502007001624D1 (de) Integriertes Motorkühlsystem
BR112014016281A2 (pt) motor de turbina a gás
BR112014016300A2 (pt) motor de turbina a gás
BR112013005595A2 (pt) aparelho de propulsão e motor de turbina a gás de aeronave
BRPI0717616A2 (pt) Sistema de refrigeração de motor
BRPI0921691A2 (pt) motor a gás
BR112014026534A2 (pt) motor de turbina a gãs e sistema de controle de válvula de ar
BRPI0822363A2 (pt) Nacela de motor turbojato
FR2976974B1 (fr) Dispositif d'assemblage de panneaux acoustiques d'une nacelle de turbomachine
BR112012001083A2 (pt) sistema de refrigeração de gás de exaustão de turbina a gás
EP2655833A4 (en) Gas turbine engine flow path member

Legal Events

Date Code Title Description
B08F Application fees: dismissal - article 86 of industrial property law

Free format text: REFERENTE A 7A ANUIDADE.

B08K Lapse as no evidence of payment of the annual fee has been furnished to inpi (acc. art. 87)

Free format text: EM VIRTUDE DO ARQUIVAMENTO PUBLICADO NA RPI 2487 DE 04-09-2018 E CONSIDERANDO AUSENCIA DE MANIFESTACAO DENTRO DOS PRAZOS LEGAIS, INFORMO QUE CABE SER MANTIDO O ARQUIVAMENTO DO PEDIDO DE PATENTE, CONFORME O DISPOSTO NO ARTIGO 12, DA RESOLUCAO 113/2013.