FR3148254B1 - Ensemble pour turbomachine d’aéronef, l’ensemble étant équipé d’un système anti-accrétion - Google Patents

Ensemble pour turbomachine d’aéronef, l’ensemble étant équipé d’un système anti-accrétion Download PDF

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Publication number
FR3148254B1
FR3148254B1 FR2304231A FR2304231A FR3148254B1 FR 3148254 B1 FR3148254 B1 FR 3148254B1 FR 2304231 A FR2304231 A FR 2304231A FR 2304231 A FR2304231 A FR 2304231A FR 3148254 B1 FR3148254 B1 FR 3148254B1
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France
Prior art keywords
assembly
inlet orifice
flow path
valve
door
Prior art date
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Active
Application number
FR2304231A
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English (en)
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FR3148254A1 (fr
Inventor
Romain Nicolas Lagarde
Baptiste René Roger Batonnet
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
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Publication date
Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR2304231A priority Critical patent/FR3148254B1/fr
Publication of FR3148254A1 publication Critical patent/FR3148254A1/fr
Application granted granted Critical
Publication of FR3148254B1 publication Critical patent/FR3148254B1/fr
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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
    • F02K3/02—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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/02—De-icing means for engines having icing phenomena
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine 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
    • F02C9/18—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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • 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
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation
    • 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
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L’invention concerne un ensemble pour turbomachine, notamment d’aéronef, comprenant :- une virole interne (46) et une virole externe configurées pour délimiter respectivement extérieurement une première veine et intérieurement une deuxième veine d’écoulement des gaz ; et- au moins un conduit de décharge d’air (60) s’étendant entre les viroles interne et externe et débouchant dans la première veine à travers un orifice d’entrée (62) équipé d’une vanne de décharge (70), chaque vanne comporte une porte (72) mobile en rotation autour d’un axe de pivotement (74) entre une position de fermeture et une position d’ouverture de l’orifice d’entrée ;caractérisé en ce que chaque conduit de décharge comprend un système anti-accrétion dans le conduit comprenant une pluralité de griffes (82) s’étendant dans une direction sensiblement perpendiculaire à la porte vers l’orifice d’entrée lorsque la porte de la vanne est en position d’ouverture de l’orifice d’entrée. Figure pour l'abrégé : Figure 3
FR2304231A 2023-04-26 2023-04-26 Ensemble pour turbomachine d’aéronef, l’ensemble étant équipé d’un système anti-accrétion Active FR3148254B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2304231A FR3148254B1 (fr) 2023-04-26 2023-04-26 Ensemble pour turbomachine d’aéronef, l’ensemble étant équipé d’un système anti-accrétion

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2304231A FR3148254B1 (fr) 2023-04-26 2023-04-26 Ensemble pour turbomachine d’aéronef, l’ensemble étant équipé d’un système anti-accrétion
FR2304231 2023-04-26

Publications (2)

Publication Number Publication Date
FR3148254A1 FR3148254A1 (fr) 2024-11-01
FR3148254B1 true FR3148254B1 (fr) 2025-05-02

Family

ID=87036028

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2304231A Active FR3148254B1 (fr) 2023-04-26 2023-04-26 Ensemble pour turbomachine d’aéronef, l’ensemble étant équipé d’un système anti-accrétion

Country Status (1)

Country Link
FR (1) FR3148254B1 (fr)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8240126B2 (en) * 2008-03-22 2012-08-14 Pratt & Whitney Rocketdyne, Inc. Valve system for a gas turbine engine
FR3018096B1 (fr) * 2014-03-03 2019-03-29 Safran Aircraft Engines Conduit de decharge pour une turbomachine
FR3107086B1 (fr) * 2020-02-10 2023-04-14 Safran Aircraft Engines Vanne de décharge avec porte et ailette actionnées de manière coordonnée
FR3115837B1 (fr) * 2020-11-03 2025-09-19 Safran Aircraft Engines Ensemble pour turbomachine d’aeronef a double flux, l’ensemble etant equipe d’ailettes de decharge d’air pilotees en incidence

Also Published As

Publication number Publication date
FR3148254A1 (fr) 2024-11-01

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