FR3101671B1 - TURBOMACHINE COMPRISING MEANS FOR REDUCING THE PRIMARY VEIN AIR FLOW DRIVEN BY ELECTRIC MOTORS - Google Patents

TURBOMACHINE COMPRISING MEANS FOR REDUCING THE PRIMARY VEIN AIR FLOW DRIVEN BY ELECTRIC MOTORS Download PDF

Info

Publication number
FR3101671B1
FR3101671B1 FR1911012A FR1911012A FR3101671B1 FR 3101671 B1 FR3101671 B1 FR 3101671B1 FR 1911012 A FR1911012 A FR 1911012A FR 1911012 A FR1911012 A FR 1911012A FR 3101671 B1 FR3101671 B1 FR 3101671B1
Authority
FR
France
Prior art keywords
primary
cross
section
turbomachine
reducing
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
FR1911012A
Other languages
French (fr)
Other versions
FR3101671A1 (en
Inventor
Joseph Jean Marie Burguburu
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
Safran Aircraft Engines 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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1911012A priority Critical patent/FR3101671B1/en
Publication of FR3101671A1 publication Critical patent/FR3101671A1/en
Application granted granted Critical
Publication of FR3101671B1 publication Critical patent/FR3101671B1/en
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
    • 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
    • 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
    • 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
    • F02C7/26—Starting; Ignition
    • F02C7/262—Restarting after flame-out
    • 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
    • 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

Abstract

L’invention concerne une turbomachine (10) d’aéronef, comprenant un ensemble comportant une soufflante (12), au moins un compresseur (14, 16), une chambre de combustion (18) et au moins une turbine (20, 22), l’ensemble définissant une veine primaire (28) dans laquelle un flux primaire (P) circule, caractérisée en ce que la turbomachine comporte également des moyens d’obturation (36) de la veine primaire, et des moyens électriques de commande (38) configurés pour commander les moyens d’obturation de sorte à faire varier la section transversale de la veine primaire entre une première position extrême dans laquelle la section transversale de la veine primaire est maximale et le débit du flux primaire circulant à travers la section transversale de la veine primaire est maximal et une seconde position extrême dans laquelle la section transversale de la veine primaire est minimale et le débit du flux primaire circulant à travers la section transversale de la veine primaire est minimal. Figure pour l'abrégé : Figure 1The invention relates to an aircraft turbomachine (10), comprising an assembly comprising a fan (12), at least one compressor (14, 16), a combustion chamber (18) and at least one turbine (20, 22) , the assembly defining a primary stream (28) in which a primary flow (P) circulates, characterized in that the turbine engine also comprises means for closing off (36) the primary stream, and electrical control means (38 ) configured to control the closure means so as to vary the cross section of the primary stream between a first extreme position in which the cross section of the primary stream is maximum and the flow rate of the primary flow circulating through the cross section of the primary vein is maximal and a second extreme position in which the cross section of the primary vein is minimal and the flow rate of the primary flow circulating through the cross section of the primary vein is minimal. Figure for abstract: Figure 1

FR1911012A 2019-10-04 2019-10-04 TURBOMACHINE COMPRISING MEANS FOR REDUCING THE PRIMARY VEIN AIR FLOW DRIVEN BY ELECTRIC MOTORS Active FR3101671B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1911012A FR3101671B1 (en) 2019-10-04 2019-10-04 TURBOMACHINE COMPRISING MEANS FOR REDUCING THE PRIMARY VEIN AIR FLOW DRIVEN BY ELECTRIC MOTORS

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1911012A FR3101671B1 (en) 2019-10-04 2019-10-04 TURBOMACHINE COMPRISING MEANS FOR REDUCING THE PRIMARY VEIN AIR FLOW DRIVEN BY ELECTRIC MOTORS
FR1911012 2019-10-04

Publications (2)

Publication Number Publication Date
FR3101671A1 FR3101671A1 (en) 2021-04-09
FR3101671B1 true FR3101671B1 (en) 2022-05-06

Family

ID=69173003

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1911012A Active FR3101671B1 (en) 2019-10-04 2019-10-04 TURBOMACHINE COMPRISING MEANS FOR REDUCING THE PRIMARY VEIN AIR FLOW DRIVEN BY ELECTRIC MOTORS

Country Status (1)

Country Link
FR (1) FR3101671B1 (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1096185A (en) * 1977-08-26 1981-02-24 Barton H. Snow Method and apparatus for windmill starts
US7097421B2 (en) * 2004-10-08 2006-08-29 United Technologies Corporation Vernier duct blocker
US7475545B2 (en) * 2005-04-29 2009-01-13 General Electric Company Fladed supersonic missile turbojet
US8622687B2 (en) * 2009-09-25 2014-01-07 General Electric Company Method of operating adaptive core engines
US10060286B2 (en) * 2013-04-08 2018-08-28 United Technologies Corporation Geared annular airflow actuation system for variable cycle gas turbine engines

Also Published As

Publication number Publication date
FR3101671A1 (en) 2021-04-09

Similar Documents

Publication Publication Date Title
JP7042840B2 (en) Self-adaptive gas turbine combustor
FR2445438A1 (en) TURBOFLOW MOTOR COMPRISING AN IMPROVED MECHANISM FOR ACTUATING BLIND BLADES
FR3083207B1 (en) POWERTRAIN ASSEMBLY FOR AN AIRCRAFT INCLUDING A NON-HOODED ROTOR
EP0266235A1 (en) Turbo machine with an automatic controlling device for the turbine ventilation flows
US10544737B2 (en) Method and system for mitigation of cavity resonance
FR2422036A1 (en) COOLING DEVICE FOR THE MOVABLE ELEMENTS OF A GAS TURBINE ENGINE
FR2402771A1 (en) GAS TURBINE ENGINE
FR3082230B1 (en) NON-HOODED ROTOR AIRCRAFT ENGINE WITH STATOR VANE ADAPTATION
EP0442884A1 (en) Turbocharger apparatus.
FR3060061B1 (en) FREE TURBINE TURBOMACHINE FOR AIRCRAFT
FR3116302B1 (en) Free-turbine turbomachine comprising electrical machines assisting a gas generator and a free turbine
FR3101671B1 (en) TURBOMACHINE COMPRISING MEANS FOR REDUCING THE PRIMARY VEIN AIR FLOW DRIVEN BY ELECTRIC MOTORS
FR2417639A1 (en) REFRIGERANT DEVICE FOR GAS TURBINE ENGINE DISTRIBUTOR VANE
FR3100268B1 (en) DOUBLE-FLOW TURBOMACHINE FOR AN AIRCRAFT
FR3084910B1 (en) EFFICIENT AIRCRAFT ENGINE
CA2106270A1 (en) Turbine Engine air Supply Regulating System, Centrifugal Compressor Comprising a Regulating System, and Auxiliairy Power Unit Comprising Said Compressor
FR3087819B1 (en) AIRCRAFT TURBOMACHINE EQUIPPED WITH AN ELECTRIC MACHINE
FR2433106A1 (en) AIR INTAKE DEVICE ON A COMPRESSOR OF A GAS TURBINE ENGINE
FR3039216B1 (en) PROPELLENT ASSEMBLY FOR AN AIRCRAFT COMPRISING A DRIVE INVERTER
FR2389759A1 (en)
FR3096407B1 (en) Gas turbine engine
FR3096663B1 (en) Closed circuit for cooling the engine of an aircraft powertrain
FR3088966B1 (en) Double-flow turbojet arrangement with epicyclic or planetary reduction gear
GB2564935A (en) Turbomachine including a cooling and turbine clearance control system and an air supply scoop for said system
FR3076865B1 (en) REAR ASSEMBLY OF AN AIRCRAFT TURBOREACTOR NACELLE INCLUDING A SLIDING GRID DRIVE INVERTER

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20210409

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5