BR112015023057A2 - turbomáquina, tal como um turborreator ou um turbopropulsor de avião - Google Patents

turbomáquina, tal como um turborreator ou um turbopropulsor de avião

Info

Publication number
BR112015023057A2
BR112015023057A2 BR112015023057A BR112015023057A BR112015023057A2 BR 112015023057 A2 BR112015023057 A2 BR 112015023057A2 BR 112015023057 A BR112015023057 A BR 112015023057A BR 112015023057 A BR112015023057 A BR 112015023057A BR 112015023057 A2 BR112015023057 A2 BR 112015023057A2
Authority
BR
Brazil
Prior art keywords
turbojet
turbomachine
panel
airplane turboprop
fan
Prior art date
Application number
BR112015023057A
Other languages
English (en)
Other versions
BR112015023057A8 (pt
Inventor
Rognin Florent
Sonois Gérome
Galiano Jérémy
Plante Romain
Original Assignee
Snecma
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 Snecma filed Critical Snecma
Publication of BR112015023057A2 publication Critical patent/BR112015023057A2/pt
Publication of BR112015023057A8 publication Critical patent/BR112015023057A8/pt

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2250/28—Three-dimensional patterned
    • F05D2250/283—Three-dimensional patterned honeycomb
    • 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
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B11/00—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
    • F16B11/006—Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding by gluing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

resumo “turbomáquina, tal como um turborreator ou um turbopropulsor de avião” a presente invenção trata de uma turbomáquina, tal como turborreator ou um turbopropulsor de avião, que compreende um cárter (10) de ventoinha a parede (12) sensivelmente cilíndrica que circunda as pás da ventoinha, e pelo menos dois painéis anulares (18, 20) de isolação acústica montados radialmente no interior da referida parede (12), sendo que um primeiro painel (18) está montado a montante da ventoinha, um segundo painel (20) está situado a jusante do primeiro painel (18) e que porta uma camada interna (42) em material suscetível de ser submetido à abrasão situada diante das extremidades radialmente externas des pás da ventoinha, caracterizada pelo fato que os dois painéis anulares (18, 20) formam um único conjunto estrutural.
BR112015023057A 2013-03-15 2014-03-12 turbomáquina BR112015023057A8 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1352353A FR3003303B1 (fr) 2013-03-15 2013-03-15 Turbomachine, telle qu'un turboreacteur ou un turbopropulseur d'avion
PCT/FR2014/050566 WO2014140483A1 (fr) 2013-03-15 2014-03-12 Turbomachine, telle qu'un turboréacteur ou un turbopropulseur d'avion

Publications (2)

Publication Number Publication Date
BR112015023057A2 true BR112015023057A2 (pt) 2017-07-18
BR112015023057A8 BR112015023057A8 (pt) 2019-12-03

Family

ID=48225059

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112015023057A BR112015023057A8 (pt) 2013-03-15 2014-03-12 turbomáquina

Country Status (9)

Country Link
US (1) US20160032834A1 (pt)
EP (1) EP2971738A1 (pt)
JP (1) JP2016513773A (pt)
CN (2) CN105051360A (pt)
BR (1) BR112015023057A8 (pt)
CA (1) CA2905793A1 (pt)
FR (1) FR3003303B1 (pt)
RU (1) RU2015138543A (pt)
WO (1) WO2014140483A1 (pt)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3059362B1 (fr) * 2016-11-30 2021-01-01 Safran Aircraft Engines Carter de turbomachine comportant une structure acoustique et un element abradable
US10662813B2 (en) * 2017-04-13 2020-05-26 General Electric Company Turbine engine and containment assembly for use in a turbine engine
US10458281B2 (en) * 2017-06-12 2019-10-29 United Technologies Corporation Resilient mounting assembly for a turbine engine
FR3068007B1 (fr) * 2017-06-23 2021-07-16 Safran Nacelles Dispositif de traitement acoustique pour nacelle de turboreacteur d'aeronef
CN107795557B (zh) * 2017-11-10 2020-02-14 中国航发航空科技股份有限公司 一种用于发动机转子叶片榫头的粘胶成型装置及粘胶方法
FR3085447B1 (fr) * 2018-09-04 2020-09-11 Safran Aircraft Engines Carter de soufflante pour une turbomachine d'aeronef integrant directement des portions abradable et ayant des proprietes acoustiques
FR3086785B1 (fr) 2018-09-28 2022-01-21 Airbus Operations Sas Ensemble comportant deux panneaux acoustiques juxtaposes dans lequel les panneaux comportent une face resistive qui s'etend jusqu'a une paroi d'extremite
FR3095025B1 (fr) * 2019-04-12 2021-03-05 Safran Aircraft Engines Joint d’étanchéité à labyrinthe comportant un élément abradable à densité variable de cellules

Family Cites Families (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL250167A (pt) 1959-07-17
FR1260495A (fr) 1960-06-23 1961-05-05 Thomson Houston Comp Francaise Perfectionnements aux machines électriques
US5482429A (en) * 1994-04-29 1996-01-09 United Technologies Corporation Fan blade containment assembly
US5662757A (en) * 1994-10-17 1997-09-02 General Electric Company Method of removing an abradable shroud assembly for turbomachinery
US5776579A (en) * 1996-03-28 1998-07-07 The Boeing Company Structural bonding with encapsulated foaming adhesive
US6364603B1 (en) * 1999-11-01 2002-04-02 Robert P. Czachor Fan case for turbofan engine having a fan decoupler
GB0119608D0 (en) * 2001-08-11 2001-10-03 Rolls Royce Plc A guide vane assembly
US6619913B2 (en) * 2002-02-15 2003-09-16 General Electric Company Fan casing acoustic treatment
US6652222B1 (en) * 2002-09-03 2003-11-25 Pratt & Whitney Canada Corp. Fan case design with metal foam between Kevlar
GB2407343B (en) * 2003-10-22 2006-04-19 Rolls Royce Plc An acoustic liner for a gas turbine engine casing
FR2866074B1 (fr) * 2004-02-11 2006-04-28 Snecma Moteurs Architecture d'un turboreacteur ayant une double soufflante a l'avant
FR2866387B1 (fr) * 2004-02-12 2008-03-14 Snecma Moteurs Adaptation aerodynamique de la soufflante arriere d'un turboreacteur double soufflante
FR2931205B1 (fr) * 2008-05-16 2010-05-14 Aircelle Sa Ensemble propulsif pour aeronef, et structure d'entree d'air pour un tel ensemble
GB2478144A (en) * 2010-02-26 2011-08-31 Rolls Royce Plc Panelled assembly, eg for a gas turbine engine ducted fan casing
FR2975943B1 (fr) * 2011-06-01 2013-05-17 Aircelle Sa Procede de fabrication d'un panneau d'attenuation acoustique
FR2979385A1 (fr) * 2011-08-22 2013-03-01 Snecma Panneau d'isolation acoustique pour turbomachine et turbomachine comportant un tel panneau
US9194299B2 (en) * 2012-12-21 2015-11-24 United Technologies Corporation Anti-torsion assembly

Also Published As

Publication number Publication date
WO2014140483A1 (fr) 2014-09-18
CN105051360A (zh) 2015-11-11
RU2015138543A (ru) 2017-04-19
FR3003303B1 (fr) 2017-06-30
EP2971738A1 (fr) 2016-01-20
CN106979040A (zh) 2017-07-25
US20160032834A1 (en) 2016-02-04
CA2905793A1 (fr) 2014-09-18
BR112015023057A8 (pt) 2019-12-03
FR3003303A1 (fr) 2014-09-19
JP2016513773A (ja) 2016-05-16

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Legal Events

Date Code Title Description
B06F Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]
B08F Application dismissed because of non-payment of annual fees [chapter 8.6 patent gazette]

Free format text: REFERENTE A 6A ANUIDADE.

B08K Patent lapsed as no evidence of payment of the annual fee has been furnished to inpi [chapter 8.11 patent gazette]

Free format text: REFERENTE AO DESPACHO 8.6 PUBLICADO NA RPI 2557 DE 07/01/2020.