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IN2012DN02042A - - Google Patents

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Publication number
IN2012DN02042A
IN2012DN02042A IN2042DEN2012A IN2012DN02042A IN 2012DN02042 A IN2012DN02042 A IN 2012DN02042A IN 2042DEN2012 A IN2042DEN2012 A IN 2042DEN2012A IN 2012DN02042 A IN2012DN02042 A IN 2012DN02042A
Authority
IN
India
Prior art keywords
turbine
compressor
generator
combustion
combustion chamber
Prior art date
Application number
Inventor
Drachsler Antoine
Michel Perbos Alain
Silet Joel
Original Assignee
Turbomeca
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 Turbomeca filed Critical Turbomeca
Publication of IN2012DN02042A publication Critical patent/IN2012DN02042A/en

Links

Classifications

    • 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
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • 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
    • F02C3/045—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
    • F02C3/05—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module the compressor and the turbine being of the radial flow type
    • 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
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • F02C3/103—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor the compressor being of the centrifugal type
    • 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
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/145—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chamber being in the reverse flow-type
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/311—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being in 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/312—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being parallel to each other
    • 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)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

The invention relates to a free-turbine turboshaft engine including, on the one hand, a gas generator comprising at least one compressor (1) supplied with air, a combustion chamber (5) receiving the compressed air at the output of said compressor (1), and at least one generator turbine (7) mechanically connected to said compressor (1) by a drive shaft (15) and driven by the gases from the combustion of fuel carried out in said combustion chamber (5), and including, on the other hand, a free turbine (11) supplied by the gases from said combustion after passing through said generator turbine (7) and which drives a power shaft (12) positioned non-coaxially relative to the drive shaft (15) of the gas generator and supplying the power of the turboshaft engine via a reduction gear (13). According to the invention, the combustion chamber (5) is a substantially cylindrical or frusto-conical chamber, coaxial with the axis of the generator turbine and comprising a single injector (6).
IN2042DEN2012 2009-09-17 2010-09-29 IN2012DN02042A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0956412A FR2950109B1 (en) 2009-09-17 2009-09-17 TURBOMOTEUR WITH PARALLEL TREES
PCT/FR2010/052057 WO2011033244A1 (en) 2009-09-17 2010-09-29 Turboshaft engine with parallel shafts

Publications (1)

Publication Number Publication Date
IN2012DN02042A true IN2012DN02042A (en) 2015-08-21

Family

ID=42145186

Family Applications (1)

Application Number Title Priority Date Filing Date
IN2042DEN2012 IN2012DN02042A (en) 2009-09-17 2010-09-29

Country Status (11)

Country Link
US (1) US9297305B2 (en)
EP (1) EP2478198B1 (en)
JP (1) JP5686811B2 (en)
KR (1) KR101779627B1 (en)
CN (1) CN102822473A (en)
CA (1) CA2774453C (en)
FR (1) FR2950109B1 (en)
IN (1) IN2012DN02042A (en)
PL (1) PL2478198T3 (en)
RU (1) RU2583186C2 (en)
WO (1) WO2011033244A1 (en)

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US9217370B2 (en) 2011-02-18 2015-12-22 Dynamo Micropower Corporation Fluid flow devices with vertically simple geometry and methods of making the same
FR2979964B1 (en) * 2011-09-08 2014-04-11 Turbomeca DAMPING VIBRATION OF A PINION BY VISCOELASTIC PATCH
FR3007069B1 (en) * 2013-06-12 2015-07-17 Snecma HIGH PRESSURE TURBINE TOURILLON, AND TURBOREACTOR INCLUDING SUCH A TOURILLON
FR3015574B1 (en) * 2013-12-20 2019-05-03 Safran Helicopter Engines METHOD FOR AUTOMATICALLY CONTROLLING THE OPERATING REGIME OF A TURBOMOTOR OF A HELICOPTER, CORRESPONDING CONTROL DEVICE AND HELICOPTER EQUIPPED WITH SUCH A DEVICE
US10030580B2 (en) 2014-04-11 2018-07-24 Dynamo Micropower Corporation Micro gas turbine systems and uses thereof
US10202856B2 (en) * 2014-09-02 2019-02-12 United Technologies Corporation Decoupled gas turbine engine
NL2013537B1 (en) * 2014-09-26 2016-09-29 Innecs B V Apparatus for expanding a compressed combustion gas.
FR3035447B1 (en) * 2015-04-27 2017-04-14 Turbomeca TURBOMOTEUR FOR AN AIRCRAFT EQUIPPED WITH AN AUTOMATIC ACTIVATION CENTER
US9611787B2 (en) 2015-05-18 2017-04-04 General Electric Company Accessory apparatus and method of assembling accessories with a turbine engine
US10794273B2 (en) * 2015-07-01 2020-10-06 Raytheon Technologies Corporation Advanced distributed engine architecture-design alternative
EP4538181A3 (en) 2015-09-15 2025-06-18 Sikorsky Aircraft Corporation Drive system arrangement for rotorcraft
US10883424B2 (en) 2016-07-19 2021-01-05 Pratt & Whitney Canada Corp. Multi-spool gas turbine engine architecture
US11035293B2 (en) 2016-09-15 2021-06-15 Pratt & Whitney Canada Corp. Reverse flow gas turbine engine with offset RGB
US10533559B2 (en) * 2016-12-20 2020-01-14 Pratt & Whitney Canada Corp. Reverse flow engine architecture
US10738709B2 (en) 2017-02-09 2020-08-11 Pratt & Whitney Canada Corp. Multi-spool gas turbine engine
US10808624B2 (en) 2017-02-09 2020-10-20 Pratt & Whitney Canada Corp. Turbine rotor with low over-speed requirements
US10746188B2 (en) 2017-03-14 2020-08-18 Pratt & Whitney Canada Corp. Inter-shaft bearing connected to a compressor boost system
US10215052B2 (en) 2017-03-14 2019-02-26 Pratt & Whitney Canada Corp. Inter-shaft bearing arrangement
US11788464B2 (en) * 2019-05-30 2023-10-17 Joseph Michael Teets Advanced 2-spool turboprop engine

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Also Published As

Publication number Publication date
WO2011033244A1 (en) 2011-03-24
CN102822473A (en) 2012-12-12
RU2583186C2 (en) 2016-05-10
CA2774453A1 (en) 2011-03-24
KR101779627B1 (en) 2017-09-18
FR2950109B1 (en) 2012-07-27
US20120167591A1 (en) 2012-07-05
FR2950109A1 (en) 2011-03-18
KR20130047681A (en) 2013-05-08
RU2012115106A (en) 2013-10-27
EP2478198B1 (en) 2017-06-21
EP2478198A1 (en) 2012-07-25
CA2774453C (en) 2018-01-02
US9297305B2 (en) 2016-03-29
PL2478198T3 (en) 2017-10-31
JP2013527357A (en) 2013-06-27
JP5686811B2 (en) 2015-03-18

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