FR3094045B1 - Turbomachine comprising a bypass line for cleaning fluids - Google Patents

Turbomachine comprising a bypass line for cleaning fluids Download PDF

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Publication number
FR3094045B1
FR3094045B1 FR1902975A FR1902975A FR3094045B1 FR 3094045 B1 FR3094045 B1 FR 3094045B1 FR 1902975 A FR1902975 A FR 1902975A FR 1902975 A FR1902975 A FR 1902975A FR 3094045 B1 FR3094045 B1 FR 3094045B1
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FR
France
Prior art keywords
turbomachine
cleaning fluids
stream
bypass line
primary stream
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
FR1902975A
Other languages
French (fr)
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FR3094045A1 (en
Inventor
Alméric Pierre Louis Garnier
Josselin Xavier Coupard
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 FR1902975A priority Critical patent/FR3094045B1/en
Publication of FR3094045A1 publication Critical patent/FR3094045A1/en
Application granted granted Critical
Publication of FR3094045B1 publication Critical patent/FR3094045B1/en
Active legal-status Critical Current
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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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/002—Cleaning of turbomachines
    • 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
    • F02K3/075—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

Abstract

L’invention concerne une turbomachine à double flux d’un aéronef, la turbomachine comprenant une veine primaire et une veine secondaire, la turbomachine comprenant en outre un carter de moyeu interne définissant une paroi extérieure de la veine primaire et une paroi intérieure de la veine secondaire,le carter de moyeu interne comprenant une conduite de contournement permettant le passage de fluides de nettoyage,la conduite de contournement présentant une première extrémité et une deuxième extrémité qui débouchent dans la veine primaire respectivement en amont et en aval d’une chambre de combustion de la turbomachine dans un sens d’écoulement des fluides de nettoyage. Figure pour l’abrégé : Fig.3The invention relates to a turbomachine of an aircraft, the turbomachine comprising a primary stream and a secondary stream, the turbomachine further comprising an internal hub casing defining an exterior wall of the primary stream and an interior wall of the stream secondary, the inner hub casing comprising a bypass pipe allowing the passage of cleaning fluids, the bypass pipe having a first end and a second end which open into the primary stream respectively upstream and downstream of a combustion chamber of the turbomachine in a direction of flow of the cleaning fluids. Figure for the abstract: Fig.3

FR1902975A 2019-03-22 2019-03-22 Turbomachine comprising a bypass line for cleaning fluids Active FR3094045B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1902975A FR3094045B1 (en) 2019-03-22 2019-03-22 Turbomachine comprising a bypass line for cleaning fluids

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1902975A FR3094045B1 (en) 2019-03-22 2019-03-22 Turbomachine comprising a bypass line for cleaning fluids
FR1902975 2019-03-22

Publications (2)

Publication Number Publication Date
FR3094045A1 FR3094045A1 (en) 2020-09-25
FR3094045B1 true FR3094045B1 (en) 2022-12-16

Family

ID=67185436

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1902975A Active FR3094045B1 (en) 2019-03-22 2019-03-22 Turbomachine comprising a bypass line for cleaning fluids

Country Status (1)

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FR (1) FR3094045B1 (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2640685B1 (en) * 1988-12-15 1991-02-08 Snecma TURBOREACTOR COMPRESSOR DISCHARGE VALVE
US5261228A (en) * 1992-06-25 1993-11-16 General Electric Company Apparatus for bleeding air
GB201504010D0 (en) * 2015-03-10 2015-04-22 Rolls Royce Plc Gas bleed arrangement
US10578028B2 (en) * 2015-08-18 2020-03-03 General Electric Company Compressor bleed auxiliary turbine
BE1024315B1 (en) * 2016-06-28 2018-01-30 Safran Aero Boosters Sa Propulsion system for aircraft

Also Published As

Publication number Publication date
FR3094045A1 (en) 2020-09-25

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