FR3130897B1 - AIRCRAFT TURBOMACHINE - Google Patents

AIRCRAFT TURBOMACHINE Download PDF

Info

Publication number
FR3130897B1
FR3130897B1 FR2113847A FR2113847A FR3130897B1 FR 3130897 B1 FR3130897 B1 FR 3130897B1 FR 2113847 A FR2113847 A FR 2113847A FR 2113847 A FR2113847 A FR 2113847A FR 3130897 B1 FR3130897 B1 FR 3130897B1
Authority
FR
France
Prior art keywords
aircraft turbomachine
annular
straightener vanes
rotor blade
walls
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
FR2113847A
Other languages
French (fr)
Other versions
FR3130897A1 (en
Inventor
Luque Raul Martinez
Damien Bernard Emeric Guegan
De Montesquieu Antoine Claude Baudouin Raoul Marie Secondat
Laurent Soulat
Michaël Franck Antoine Schvallinger
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 FR2113847A priority Critical patent/FR3130897B1/en
Publication of FR3130897A1 publication Critical patent/FR3130897A1/en
Application granted granted Critical
Publication of FR3130897B1 publication Critical patent/FR3130897B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • 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
    • 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
    • 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
    • F02C9/48—Control of fuel supply conjointly with another control of the plant
    • F02C9/50—Control of fuel supply conjointly with another control of the plant with control of working fluid flow
    • F02C9/52—Control of fuel supply conjointly with another control of the plant with control of working fluid flow by bleeding or by-passing the working fluid
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes

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)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Turbomachine (10) d’aéronef, comportant : - deux parois annulaires coaxiales (12, 14), - un aubage de rotor (30), - un séparateur annulaire (24) disposé en aval de l’aubage de rotor (30) et entre les deux parois (12, 14), et comportant en amont un bec annulaire (24a), - des aubes de redresseur fixes (42) reliées au bec (24a), et - des aubes de redresseur à calage variable (44) en aval des aubes de redresseur fixes (42). Figure pour l'abrégé : Figure 3aAircraft turbomachine (10), comprising: - two coaxial annular walls (12, 14), - a rotor blade (30), - an annular separator (24) arranged downstream of the rotor blade (30) and between the two walls (12, 14), and comprising upstream an annular nozzle (24a), - fixed straightener vanes (42) connected to the nozzle (24a), and - straightener vanes with variable pitch (44) in downstream of the fixed straightener vanes (42). Figure for abstract: Figure 3a

FR2113847A 2021-12-17 2021-12-17 AIRCRAFT TURBOMACHINE Active FR3130897B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2113847A FR3130897B1 (en) 2021-12-17 2021-12-17 AIRCRAFT TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2113847 2021-12-17
FR2113847A FR3130897B1 (en) 2021-12-17 2021-12-17 AIRCRAFT TURBOMACHINE

Publications (2)

Publication Number Publication Date
FR3130897A1 FR3130897A1 (en) 2023-06-23
FR3130897B1 true FR3130897B1 (en) 2023-11-24

Family

ID=81448614

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2113847A Active FR3130897B1 (en) 2021-12-17 2021-12-17 AIRCRAFT TURBOMACHINE

Country Status (1)

Country Link
FR (1) FR3130897B1 (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11802525B2 (en) 2022-01-07 2023-10-31 General Electric Company Outlet guide vane
US11859515B2 (en) 2022-03-04 2024-01-02 General Electric Company Gas turbine engines with improved guide vane configurations
US11946378B2 (en) 2022-04-13 2024-04-02 General Electric Company Transient control of a thermal transport bus
US11927142B2 (en) 2022-07-25 2024-03-12 General Electric Company Systems and methods for controlling fuel coke formation

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3841091A (en) * 1973-05-21 1974-10-15 Gen Electric Multi-mission tandem propulsion system
US20110167784A1 (en) * 2009-09-25 2011-07-14 James Edward Johnson Method of operating a convertible fan engine
WO2015088833A1 (en) * 2013-12-12 2015-06-18 United Technologies Corporation Systems and methods controlling fan pressure ratios
US20190078536A1 (en) * 2017-09-12 2019-03-14 Rolls-Royce North American Technologies Inc. Flow path splitter for turbofan gas turbine engines

Also Published As

Publication number Publication date
FR3130897A1 (en) 2023-06-23

Similar Documents

Publication Publication Date Title
FR3130897B1 (en) AIRCRAFT TURBOMACHINE
BRPI0407675A (en) confluent exhaust nozzle
FR3130896B1 (en) AIRCRAFT TURBOMACHINE
DE502008002145D1 (en) GAS TURBINE WITH A NACHLEITRANK AND WITH A MIXER
RU2010146502A (en) HYDRO TURBINES WITH MIXERS AND EJECTORS
RU2015101349A (en) PLANT FOR TRANSFORMING A FLUID FLOW TO ENERGY
US10989074B2 (en) Turbine exhaust hood
RU2016135698A (en) HYDROTURBINE ASSEMBLY
EP1710397A3 (en) Bowed nozzle vane
WO2011054812A3 (en) Turbomachine with axial compression or expansion
KR102403377B1 (en) Exhaust diffuser
PL415184A1 (en) Exhaust nozzle for the engine with gas turbine
EP2586977A3 (en) Turbine of a turbomachine
FR3039219B1 (en) AIRCRAFT COMPRISING TWO CONTRAROTATIVE BLOWERS AT THE BACK OF A FUSELAGE WITH SETTING THE BLADES OF THE DOWNSTREAM BLOWER
EP2028345A3 (en) Steam turbine
AR079090A1 (en) CYCLONE SEPARATOR WITH VOLUTE DEPARTURE DUCT
RU2014144080A (en) COMBUSTION CHAMBER WITH FORCED FLOW REVERSE
JP2012047085A (en) Turbine impeller
FR3087819B1 (en) AIRCRAFT TURBOMACHINE EQUIPPED WITH AN ELECTRIC MACHINE
RU2010144991A (en) SUPPORT FOR THE FIXED TURBO MACHINE BLADES (OPTIONS) AND THE SYSTEM OF REDUCING THE STRAIN OF THE FLOW IN THE TURBO MACHINE
EP3020951B1 (en) Gas turbine engine duct with profiled region
MX338204B (en) Supersonic compressor rotor and method of compressing a fluid.
US20140154057A1 (en) Francis turbine or a francis pump or a francis pump turbine
CN104001604A (en) Jet pipe structure for jet mill
RU2433280C1 (en) Active turbine nozzle assembly

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20230623

PLFP Fee payment

Year of fee payment: 3