FR3131601B1 - PROPULSIVE ASSEMBLY FOR AN AIRCRAFT - Google Patents

PROPULSIVE ASSEMBLY FOR AN AIRCRAFT Download PDF

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Publication number
FR3131601B1
FR3131601B1 FR2300003A FR2300003A FR3131601B1 FR 3131601 B1 FR3131601 B1 FR 3131601B1 FR 2300003 A FR2300003 A FR 2300003A FR 2300003 A FR2300003 A FR 2300003A FR 3131601 B1 FR3131601 B1 FR 3131601B1
Authority
FR
France
Prior art keywords
nacelle
generator
aircraft
vein
nozzle
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
FR2300003A
Other languages
French (fr)
Other versions
FR3131601A1 (en
Inventor
Luque Raul Martinez
Michaël Franck Antoine Schvallinger
De Montesquieu Antoine Claude Baudouin Raoul Marie Secondat
Laurent Soulat
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 FR2300003A priority Critical patent/FR3131601B1/en
Publication of FR3131601A1 publication Critical patent/FR3131601A1/en
Application granted granted Critical
Publication of FR3131601B1 publication Critical patent/FR3131601B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • 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
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • 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
    • 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
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • 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
    • F05D2250/90—Variable geometry

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L’ensemble (1) propulsif pour un aéronef comporte une nacelle (3) entourant une turbomachine (2) à plusieurs flux qui comporte un générateur (4) de gaz, une hélice (16) accélérant un flux d’air (FO) dans la nacelle (3), un élément annulaire (18) entre le générateur (4) et la nacelle (3) définissant une première (20) et une deuxième veine (21), comportant un bec (19) séparant le flux (F0) en un flux d’air (F1) dans la première veine (20) et en un flux d’air (F2) dans la seconde veine (21), l’ensemble (1) comportant un aubage (22) de stator monté entre le bec (19) et l’hélice (16), et un aubage (24) de stator entre le générateur (4) et l’élément annulaire (18), monté entre le bec (19) et un aubage de rotor d’un compresseur (8) du générateur (4), ou entre l’élément annulaire (18) et la nacelle (3). Figure pour l'abrégé : Figure 7The propulsion assembly (1) for an aircraft comprises a nacelle (3) surrounding a multi-flow turbomachine (2) which comprises a gas generator (4), a propeller (16) accelerating an air flow (FO) in the nacelle (3), an annular element (18) between the generator (4) and the nacelle (3) defining a first (20) and a second vein (21), comprising a nozzle (19) separating the flow (F0) in an air flow (F1) in the first vein (20) and in an air flow (F2) in the second vein (21), the assembly (1) comprising a stator blade (22) mounted between the nozzle (19) and the propeller (16), and a stator blade (24) between the generator (4) and the annular element (18), mounted between the nozzle (19) and a rotor blade of a compressor (8) of the generator (4), or between the annular element (18) and the nacelle (3). Figure for abstract: Figure 7

FR2300003A 2021-12-17 2023-01-02 PROPULSIVE ASSEMBLY FOR AN AIRCRAFT Active FR3131601B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2300003A FR3131601B1 (en) 2021-12-17 2023-01-02 PROPULSIVE ASSEMBLY FOR AN AIRCRAFT

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR2113844A FR3130758B1 (en) 2021-12-17 2021-12-17 PROPULSIVE ASSEMBLY FOR AN AIRCRAFT
FR2113844 2021-12-17
FR2300003A FR3131601B1 (en) 2021-12-17 2023-01-02 PROPULSIVE ASSEMBLY FOR AN AIRCRAFT

Related Parent Applications (1)

Application Number Title Priority Date Filing Date
FR2113844A Division FR3130758B1 (en) 2021-12-17 2021-12-17 PROPULSIVE ASSEMBLY FOR AN AIRCRAFT

Publications (2)

Publication Number Publication Date
FR3131601A1 FR3131601A1 (en) 2023-07-07
FR3131601B1 true FR3131601B1 (en) 2024-02-23

Family

ID=81448855

Family Applications (3)

Application Number Title Priority Date Filing Date
FR2113844A Active FR3130758B1 (en) 2021-12-17 2021-12-17 PROPULSIVE ASSEMBLY FOR AN AIRCRAFT
FR2300003A Active FR3131601B1 (en) 2021-12-17 2023-01-02 PROPULSIVE ASSEMBLY FOR AN AIRCRAFT
FR2300004A Active FR3131600B1 (en) 2021-12-17 2023-01-02 PROPULSIVE ASSEMBLY FOR AN AIRCRAFT

Family Applications Before (1)

Application Number Title Priority Date Filing Date
FR2113844A Active FR3130758B1 (en) 2021-12-17 2021-12-17 PROPULSIVE ASSEMBLY FOR AN AIRCRAFT

Family Applications After (1)

Application Number Title Priority Date Filing Date
FR2300004A Active FR3131600B1 (en) 2021-12-17 2023-01-02 PROPULSIVE ASSEMBLY FOR AN AIRCRAFT

Country Status (1)

Country Link
FR (3) FR3130758B1 (en)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4275560A (en) * 1978-12-27 1981-06-30 General Electric Company Blocker door actuation system
US4446696A (en) * 1981-06-29 1984-05-08 General Electric Company Compound propulsor
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

Also Published As

Publication number Publication date
FR3131600B1 (en) 2024-02-23
FR3130758B1 (en) 2024-03-08
FR3131601A1 (en) 2023-07-07
FR3130758A1 (en) 2023-06-23
FR3131600A1 (en) 2023-07-07

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