BR112017012300A2 - método para fabricar uma pá de motor de turbina, meio para moldagem para a fabricação de uma pá, turbina de motor de turbina e motor de turbina - Google Patents

método para fabricar uma pá de motor de turbina, meio para moldagem para a fabricação de uma pá, turbina de motor de turbina e motor de turbina

Info

Publication number
BR112017012300A2
BR112017012300A2 BR112017012300-2A BR112017012300A BR112017012300A2 BR 112017012300 A2 BR112017012300 A2 BR 112017012300A2 BR 112017012300 A BR112017012300 A BR 112017012300A BR 112017012300 A2 BR112017012300 A2 BR 112017012300A2
Authority
BR
Brazil
Prior art keywords
turbine engine
blade
making
turbine
wall
Prior art date
Application number
BR112017012300-2A
Other languages
English (en)
Other versions
BR112017012300B1 (pt
Inventor
Coyez Dominique
Bariaud Christian
Benichou Sami
Marcel Auguste Hanny Jean-Claude
Original Assignee
Safran Aircraft Engines
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 filed Critical Safran Aircraft Engines
Publication of BR112017012300A2 publication Critical patent/BR112017012300A2/pt
Publication of BR112017012300B1 publication Critical patent/BR112017012300B1/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
    • 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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/10—Cores; Manufacture or installation of cores
    • B22C9/108—Installation of cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/22—Moulds for peculiarly-shaped castings
    • B22C9/24—Moulds for peculiarly-shaped castings for hollow articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D29/00—Removing castings from moulds, not restricted to casting processes covered by a single main group; Removing cores; Handling ingots
    • B22D29/001—Removing cores
    • B22D29/002—Removing cores by leaching, washing or dissolving
    • 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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

trata-se de um método para fabricar uma pá de motor de turbina (25) que compreende um lado de pressão e um lado de sucção separados um do outro por um espaço interno para a circulação de ar de resfriamento, sendo que a dita pá (25) compreende uma ponta (s) com uma parede de encerramento (29) que une as paredes de lado de pressão e lado de sucção na região dessa ponta (s) de modo a definir um formato de poço, sendo que a dita parede de encerramento inclui furos atravessantes. a parede de encerramento (29) obtida por moldagem tem uma espessura nominal considerável com cavidades (36, 37) que reduzem de modo localizado essa espessura em cada furo atravessante de modo a facilitar a remoção por corrosão química de hastes de alumínio que definem os ditos furos. visto que a parede de encerramento (29) tem, desse modo, uma grande espessura nominal, a mesma pode ser, então, usinada de modo a formar padrões elevados ou formatos complexos dentro do poço.
BR112017012300-2A 2014-12-17 2015-12-15 Método para fabricar uma pá de motor de turbina BR112017012300B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1462614A FR3030333B1 (fr) 2014-12-17 2014-12-17 Procede de fabrication d'une aube de turbomachine comportant un sommet pourvu d'une baignoire de type complexe
FR1462614 2014-12-17
PCT/FR2015/053517 WO2016097586A1 (fr) 2014-12-17 2015-12-15 Procédé de fabrication d'une aube de turbomachine comportant un sommet pourvu d'une baignoire de type complexe

Publications (2)

Publication Number Publication Date
BR112017012300A2 true BR112017012300A2 (pt) 2018-05-02
BR112017012300B1 BR112017012300B1 (pt) 2021-07-13

Family

ID=53191754

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112017012300-2A BR112017012300B1 (pt) 2014-12-17 2015-12-15 Método para fabricar uma pá de motor de turbina

Country Status (9)

Country Link
US (1) US10533426B2 (pt)
EP (1) EP3233328B1 (pt)
JP (1) JP6681904B2 (pt)
CN (1) CN107206473B (pt)
BR (1) BR112017012300B1 (pt)
CA (1) CA2971289C (pt)
FR (1) FR3030333B1 (pt)
RU (1) RU2706256C2 (pt)
WO (1) WO2016097586A1 (pt)

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FR3037829B1 (fr) * 2015-06-29 2017-07-21 Snecma Noyau pour le moulage d'une aube ayant des cavites superposees et comprenant un trou de depoussierage traversant une cavite de part en part
US11041395B2 (en) 2019-06-26 2021-06-22 Raytheon Technologies Corporation Airfoils and core assemblies for gas turbine engines and methods of manufacture
US11053803B2 (en) 2019-06-26 2021-07-06 Raytheon Technologies Corporation Airfoils and core assemblies for gas turbine engines and methods of manufacture
CN111379594B (zh) * 2020-04-06 2022-10-28 中国航发沈阳发动机研究所 一种涡轮转子叶片凹槽形叶顶结构及其设计方法
CN112916811B (zh) * 2021-01-22 2023-05-16 成都航宇超合金技术有限公司 带气膜孔的空心涡轮叶片的铸造方法

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US4893987A (en) * 1987-12-08 1990-01-16 General Electric Company Diffusion-cooled blade tip cap
US5599166A (en) * 1994-11-01 1997-02-04 United Technologies Corporation Core for fabrication of gas turbine engine airfoils
US5975851A (en) * 1997-12-17 1999-11-02 United Technologies Corporation Turbine blade with trailing edge root section cooling
RU2126308C1 (ru) * 1998-01-23 1999-02-20 Государственное предприятие Всероссийский научно-исследовательский институт авиационных материалов Способ изготовления составного керамического стержня для литья полых изделий
DE19821770C1 (de) * 1998-05-14 1999-04-15 Siemens Ag Verfahren und Vorrichtung zur Herstellung eines metallischen Hohlkörpers
DE50013334D1 (de) * 2000-09-14 2006-09-28 Siemens Ag Vorrichtung und Verfahren zur Herstellung einer Schaufel für eine Turbine sowie entsprechend hergestellte Schaufel
US6637500B2 (en) * 2001-10-24 2003-10-28 United Technologies Corporation Cores for use in precision investment casting
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FR2889088B1 (fr) * 2005-07-29 2008-08-22 Snecma Noyau pour aubes de turbomachine
US8500396B2 (en) * 2006-08-21 2013-08-06 General Electric Company Cascade tip baffle airfoil
US7674093B2 (en) * 2006-12-19 2010-03-09 General Electric Company Cluster bridged casting core
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US8066052B2 (en) * 2007-06-07 2011-11-29 United Technologies Corporation Cooled wall thickness control
JP5451463B2 (ja) * 2010-03-08 2014-03-26 ゼネラル・エレクトリック・カンパニイ タービン翼形部及びその先端構造体を製造する方法
FR2957828B1 (fr) * 2010-03-26 2012-10-05 Snecma Extraction des tiges d'alumine utilisees pour le maintien du noyau lors de la fabrication d'aubes de turbine.
FR2997442B1 (fr) * 2012-10-31 2018-05-18 Safran Aircraft Engines Aube pourvue d'une ailerette pouvant etre fabriquee par fonderie a la cire perdue
CN103317087A (zh) * 2013-05-24 2013-09-25 沈阳黎明航空发动机(集团)有限责任公司 硅基陶瓷型芯和铝基陶瓷型壳的锥形嵌入式定位方法
CN103990761B (zh) * 2014-05-29 2016-01-20 西安交通大学 一种带有冲击孔结构的空心涡轮叶片制造方法

Also Published As

Publication number Publication date
EP3233328B1 (fr) 2021-01-27
JP2018506671A (ja) 2018-03-08
WO2016097586A1 (fr) 2016-06-23
CA2971289A1 (fr) 2016-06-23
RU2017125136A (ru) 2019-01-18
CN107206473A (zh) 2017-09-26
JP6681904B2 (ja) 2020-04-15
RU2706256C2 (ru) 2019-11-15
US10533426B2 (en) 2020-01-14
RU2017125136A3 (pt) 2019-06-21
CN107206473B (zh) 2019-07-12
CA2971289C (fr) 2022-06-21
US20170328222A1 (en) 2017-11-16
FR3030333A1 (fr) 2016-06-24
FR3030333B1 (fr) 2017-01-20
EP3233328A1 (fr) 2017-10-25
BR112017012300B1 (pt) 2021-07-13

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Legal Events

Date Code Title Description
B06U Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]
B07A Application suspended after technical examination (opinion) [chapter 7.1 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 15/12/2015, OBSERVADAS AS CONDICOES LEGAIS.