FR3109178B1 - Acoustically optimized discharge duct outlet plate - Google Patents

Acoustically optimized discharge duct outlet plate Download PDF

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Publication number
FR3109178B1
FR3109178B1 FR2003658A FR2003658A FR3109178B1 FR 3109178 B1 FR3109178 B1 FR 3109178B1 FR 2003658 A FR2003658 A FR 2003658A FR 2003658 A FR2003658 A FR 2003658A FR 3109178 B1 FR3109178 B1 FR 3109178B1
Authority
FR
France
Prior art keywords
orifice
perforated plate
channel
face
section
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
FR2003658A
Other languages
French (fr)
Other versions
FR3109178A1 (en
Inventor
Norman Bruno André Jodet
Jéremy Paul Francisco Gonzalez
Josselin David Florian Regnard
Paul Clément Guillaume Laffay
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 FR2003658A priority Critical patent/FR3109178B1/en
Publication of FR3109178A1 publication Critical patent/FR3109178A1/en
Application granted granted Critical
Publication of FR3109178B1 publication Critical patent/FR3109178B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/26—Three-dimensional paraboloid
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/27—Three-dimensional hyperboloid
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • 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
    • 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
    • F05D2260/605—Venting into the ambient atmosphere or the like
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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

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)
  • Details Of Valves (AREA)

Abstract

Plaque de sortie de conduit de décharge acoustiquement optimisée Vanne de décharge (20) pour turboréacteur d’aéronef comprenant un conduit (21) destiné à acheminé un flux gazeux (F) et une plaque perforée (22), la plaque perforée (22) étant destinée à être traversée par un flux gazeux (F) entrant dans la plaque perforée (22) via des premiers orifices (26) réalisés dans une première face (24) de la plaque perforée (22) et sortant de la plaque perforée (22) via des seconds orifices (27) réalisés dans une seconde face (25) de la plaque perforée (22) parallèle à ladite première face (24), chaque premier orifice (26) communiquant avec au moins un second orifice (27) via un canal (23), le premier orifice (26) associé à un canal (23) ayant une section plus grande que la section du second orifice (27) auquel ledit canal (23) est associé. La section de chaque canal (23) décroit non linéairement depuis le premier orifice (26) jusqu’au second orifice (27), et la surface totale de la première face (24) occupée par les premiers orifices (26) est au moins égale à 60% de la section du conduit (21). Figure pour l’abrégé : Fig. 3.Acoustically optimized discharge duct outlet plate Discharge valve (20) for an aircraft turbojet comprising a duct (21) intended to convey a gas flow (F) and a perforated plate (22), the perforated plate (22) being intended to be traversed by a gas flow (F) entering the perforated plate (22) via first orifices (26) made in a first face (24) of the perforated plate (22) and exiting the perforated plate (22) via second orifices (27) made in a second face (25) of the perforated plate (22) parallel to said first face (24), each first orifice (26) communicating with at least one second orifice (27) via a channel (23), the first orifice (26) associated with a channel (23) having a section greater than the section of the second orifice (27) with which said channel (23) is associated. The section of each channel (23) decreases non-linearly from the first orifice (26) to the second orifice (27), and the total area of the first face (24) occupied by the first orifices (26) is at least equal at 60% of the section of the duct (21). Figure for abstract: Fig. 3.

FR2003658A 2020-04-10 2020-04-10 Acoustically optimized discharge duct outlet plate Active FR3109178B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2003658A FR3109178B1 (en) 2020-04-10 2020-04-10 Acoustically optimized discharge duct outlet plate

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2003658A FR3109178B1 (en) 2020-04-10 2020-04-10 Acoustically optimized discharge duct outlet plate
FR2003658 2020-04-10

Publications (2)

Publication Number Publication Date
FR3109178A1 FR3109178A1 (en) 2021-10-15
FR3109178B1 true FR3109178B1 (en) 2022-04-29

Family

ID=70614349

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2003658A Active FR3109178B1 (en) 2020-04-10 2020-04-10 Acoustically optimized discharge duct outlet plate

Country Status (1)

Country Link
FR (1) FR3109178B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2694791B1 (en) * 2011-04-05 2018-11-28 The Regents of The University of California Quiet bleed valve for gas turbine engine and method for reducing noise from a bleed valve
PL225152B1 (en) * 2012-12-28 2017-02-28 Gen Electric System for the expansion of the compressor flow, especially in gas turbine engines
FR3016654B1 (en) 2014-01-21 2019-06-07 Safran Aircraft Engines TURBOMACHINE WITH COMPRESSED AIR FLOW
GB201518901D0 (en) * 2015-10-26 2015-12-09 Rolls Royce Plc Bleed valve arrangement

Also Published As

Publication number Publication date
FR3109178A1 (en) 2021-10-15

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