FR3039213B1 - Turbomachine comportant au moins deux generateurs de gaz et une distribution de flux variable dans la turbine de puissance - Google Patents

Turbomachine comportant au moins deux generateurs de gaz et une distribution de flux variable dans la turbine de puissance

Info

Publication number
FR3039213B1
FR3039213B1 FR1556950A FR1556950A FR3039213B1 FR 3039213 B1 FR3039213 B1 FR 3039213B1 FR 1556950 A FR1556950 A FR 1556950A FR 1556950 A FR1556950 A FR 1556950A FR 3039213 B1 FR3039213 B1 FR 3039213B1
Authority
FR
France
Prior art keywords
turbomachine
generators
gas
flow distribution
variable flow
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.)
Active
Application number
FR1556950A
Other languages
English (en)
Other versions
FR3039213A1 (fr
Inventor
Nicolas Jerome Jean Tantot
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR1556950A priority Critical patent/FR3039213B1/fr
Priority to CN201680046332.0A priority patent/CN107849928B/zh
Priority to PCT/FR2016/051882 priority patent/WO2017013360A1/fr
Priority to US15/745,704 priority patent/US10082040B2/en
Priority to EP16756722.1A priority patent/EP3325776B1/fr
Publication of FR3039213A1 publication Critical patent/FR3039213A1/fr
Application granted granted Critical
Publication of FR3039213B1 publication Critical patent/FR3039213B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • 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
    • F02K3/12—Plants including a gas turbine driving a compressor or a ducted fan characterised by having more than one gas turbine
    • 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
    • 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
    • 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
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • F02C9/22—Control of working fluid flow by throttling; by adjusting vanes by adjusting turbine vanes
    • 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
    • F02K1/52—Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing
    • 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
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/09—Purpose of the control system to cope with emergencies
    • F05D2270/093—Purpose of the control system to cope with emergencies of one engine in a multi-engine system
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
    • F05D2270/101—Compressor surge or stall
    • F05D2270/102—Compressor surge or stall caused by working fluid flow velocity profile distortion

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
FR1556950A 2015-07-22 2015-07-22 Turbomachine comportant au moins deux generateurs de gaz et une distribution de flux variable dans la turbine de puissance Active FR3039213B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR1556950A FR3039213B1 (fr) 2015-07-22 2015-07-22 Turbomachine comportant au moins deux generateurs de gaz et une distribution de flux variable dans la turbine de puissance
CN201680046332.0A CN107849928B (zh) 2015-07-22 2016-07-21 包括具有可变供给部的被整合至后部机身中的涡轮发动机的航空器
PCT/FR2016/051882 WO2017013360A1 (fr) 2015-07-22 2016-07-21 Aeronef comportant une turbomachine integree au fuselage arriere a alimentation variable
US15/745,704 US10082040B2 (en) 2015-07-22 2016-07-21 Aircraft comprising a turbine engine incorporated into the rear fuselage with variable supply
EP16756722.1A EP3325776B1 (fr) 2015-07-22 2016-07-21 Aeronef comportant une turbomachine integree au fuselage arriere a alimentation variable

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1556950A FR3039213B1 (fr) 2015-07-22 2015-07-22 Turbomachine comportant au moins deux generateurs de gaz et une distribution de flux variable dans la turbine de puissance

Publications (2)

Publication Number Publication Date
FR3039213A1 FR3039213A1 (fr) 2017-01-27
FR3039213B1 true FR3039213B1 (fr) 2017-07-28

Family

ID=54291469

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1556950A Active FR3039213B1 (fr) 2015-07-22 2015-07-22 Turbomachine comportant au moins deux generateurs de gaz et une distribution de flux variable dans la turbine de puissance

Country Status (1)

Country Link
FR (1) FR3039213B1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10723470B2 (en) 2017-06-12 2020-07-28 Raytheon Technologies Corporation Aft fan counter-rotating turbine engine
GB201818681D0 (en) 2018-11-16 2019-01-02 Rolls Royce Plc Boundary layer ingestion fan system
GB201818684D0 (en) 2018-11-16 2019-01-02 Rolls Royce Plc Boundary layer ingestion fan system
GB201818683D0 (en) 2018-11-16 2019-01-02 Rolls Royce Plc Boundary layer ingestion fan system
GB201818686D0 (en) 2018-11-16 2019-01-02 Rolls Royce Plc Boundary layer ingestion fan system
GB201818680D0 (en) 2018-11-16 2019-01-02 Rolls Royce Plc Boundary layer ingestion fan system
GB201818682D0 (en) 2018-11-16 2019-01-02 Rolls Royce Plc Boundary layer ingestion fan system
GB201818687D0 (en) 2018-11-16 2019-01-02 Rolls Royce Plc Boundary layer ingestion fan system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2601194A (en) * 1941-12-01 1952-06-17 Power Jets Res & Dev Ltd Multiunit gas turbine power plant for aircraft propulsion
GB1175376A (en) * 1966-11-30 1969-12-23 Rolls Royce Gas Turbine Power Plants.
CA1020365A (en) * 1974-02-25 1977-11-08 James E. Johnson Modulating bypass variable cycle turbofan engine
FR2997681B1 (fr) * 2012-11-08 2015-05-15 Snecma Avion propulse par un turboreacteur a soufflantes contrarotatives

Also Published As

Publication number Publication date
FR3039213A1 (fr) 2017-01-27

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