FR2985923A1 - Shell, useful for manufacturing bladed elements of turboshaft engine of aircraft by lost-wax casting, comprises casting arms distributed about central axis, where shell is designed so that introduction of metal elements is only via arms - Google Patents

Shell, useful for manufacturing bladed elements of turboshaft engine of aircraft by lost-wax casting, comprises casting arms distributed about central axis, where shell is designed so that introduction of metal elements is only via arms Download PDF

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Publication number
FR2985923A1
FR2985923A1 FR1250676A FR1250676A FR2985923A1 FR 2985923 A1 FR2985923 A1 FR 2985923A1 FR 1250676 A FR1250676 A FR 1250676A FR 1250676 A FR1250676 A FR 1250676A FR 2985923 A1 FR2985923 A1 FR 2985923A1
Authority
FR
France
Prior art keywords
shell
elements
bladed
casting
central axis
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.)
Granted
Application number
FR1250676A
Other languages
French (fr)
Other versions
FR2985923B1 (en
Inventor
Didier Guerche
Thibault Dalon
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
SNECMA 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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR1250676A priority Critical patent/FR2985923B1/en
Priority to CN201310027351.7A priority patent/CN103212670B/en
Publication of FR2985923A1 publication Critical patent/FR2985923A1/en
Application granted granted Critical
Publication of FR2985923B1 publication Critical patent/FR2985923B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/08—Features with respect to supply of molten metal, e.g. ingates, circular gates, skim gates
    • B22C9/082—Sprues, pouring cups

Abstract

The shell comprises a set of bladed shell elements (1b) for obtaining bladed elements of a turboshaft engine, a metal distributor (12b) having a central axis (14b), and a set of metal casting arms (20b) distributed about the central axis, where each of the casting arm includes a first end connected to the distributor. The shell is designed so that the introduction of metal elements in the bladed shell elements is only via the casting arms each of which includes a second end connected to one of the bladed shell members and offset from the first end in a direction of the central axis. The shell comprises a set of bladed shell elements (1b) for obtaining bladed elements of a turboshaft engine, a metal distributor (12b) having a central axis (14b), and a set of metal casting arms (20b) distributed about the central axis of the distributor, where each of the casting arm includes a first end connected to the distributor. The shell is designed so that the introduction of metal elements in the bladed shell elements is only via the casting arms, each of which includes a second end connected to one of the bladed shell members and offset from the first end in a direction of the central axis of the distributor. Each bladed shell element comprises a blade portion (2b) between a first end portion defining a footprint of a platform and a second end portion delimiting a cavity of the platform. The second end of each casting arm is connected to the first end portion of one of the bladed shell elements. The second end portion is offset from the first end portion in the direction of the central axis of the distributor in the same direction as the offset of the second end of the arm relative to the casting at its first end. The casting arms are right or curved. The shell further comprises a central support extending from the metal splitter according to the direction of the central axis. The bladed shell elements are distributed around the central support. The shell is made of ceramics. The blade portion defines blades. An independent claim is included for a method for manufacturing bladed elements of a turboshaft engine of an aircraft.
FR1250676A 2012-01-24 2012-01-24 CARAPLE FOR THE PRODUCTION BY LOST WAXED MOLDING OF AIRCRAFT TURBOMACHINE AIRCRAFT COMPONENTS INCLUDING INCLINED CASTING ARMS Active FR2985923B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1250676A FR2985923B1 (en) 2012-01-24 2012-01-24 CARAPLE FOR THE PRODUCTION BY LOST WAXED MOLDING OF AIRCRAFT TURBOMACHINE AIRCRAFT COMPONENTS INCLUDING INCLINED CASTING ARMS
CN201310027351.7A CN103212670B (en) 2012-01-24 2013-01-24 For being manufactured the shell mould of aircraft turbine turbines vane element by lost wax casting

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1250676A FR2985923B1 (en) 2012-01-24 2012-01-24 CARAPLE FOR THE PRODUCTION BY LOST WAXED MOLDING OF AIRCRAFT TURBOMACHINE AIRCRAFT COMPONENTS INCLUDING INCLINED CASTING ARMS

Publications (2)

Publication Number Publication Date
FR2985923A1 true FR2985923A1 (en) 2013-07-26
FR2985923B1 FR2985923B1 (en) 2016-02-05

Family

ID=45954900

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1250676A Active FR2985923B1 (en) 2012-01-24 2012-01-24 CARAPLE FOR THE PRODUCTION BY LOST WAXED MOLDING OF AIRCRAFT TURBOMACHINE AIRCRAFT COMPONENTS INCLUDING INCLINED CASTING ARMS

Country Status (2)

Country Link
CN (1) CN103212670B (en)
FR (1) FR2985923B1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103433433A (en) * 2013-08-21 2013-12-11 丹阳市华明光学器材有限公司 Mold and method for manufacturing door closer shell
FR3033720A1 (en) * 2015-03-16 2016-09-23 Snecma FOUNDRY MOLD
FR3056994A1 (en) * 2016-09-30 2018-04-06 Safran CRYSTALLIZATION OVEN FOR THE PRODUCTION OF TURBOREACTOR BLADES WITH ONBOARD THERMAL SCREEN

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3006616B1 (en) * 2013-06-05 2016-03-04 Snecma TURBOMACHINE WAVE PREFORM
FR3023195B1 (en) * 2014-07-07 2016-08-19 Snecma IMPROVED PROCESS FOR THE PRODUCTION OF A CARAPACE FOR PERFORMED WHEAT MOLDING OF AIRCRAFT TURBOMACHINE AIRCRAFT ELEMENTS
CN104308082B (en) * 2014-10-29 2016-05-18 西安航空动力股份有限公司 A kind of pouring procedure of hollow turborotor
CN104308076B (en) * 2014-10-29 2016-09-07 西安航空动力股份有限公司 The wax-pattern combination of the hollow turborotor of a kind of tetrad and fine casting method thereof
CN104368764B (en) * 2014-11-14 2016-07-06 西北工业大学 Hot investment casting single crystal turbine blade model process bar
CN107755635A (en) * 2017-09-12 2018-03-06 东方电气集团东方汽轮机有限公司 A kind of method for solving combustion engine shrouded blade leaf top R angles fire check
CN109351951B (en) * 2018-11-29 2020-12-22 中国科学院金属研究所 Process method for reducing loosening defect of single crystal blade platform
CN109434025A (en) * 2018-11-29 2019-03-08 沈阳航发精密铸造有限公司 A kind of process for eliminating supramarginal plate crackle metallurgical imperfection

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5072771A (en) * 1988-03-28 1991-12-17 Pcc Airfoils, Inc. Method and apparatus for casting a metal article
US20040167270A1 (en) * 2003-02-25 2004-08-26 Dane Chang Fugitive pattern for casting
EP1604753A1 (en) * 2004-05-06 2005-12-14 United Technologies Corporation Investment casting
EP2092996A1 (en) * 2008-02-14 2009-08-26 United Technologies Corporation Method and apparatus for as-cast seal on turbine blades

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4523032B2 (en) * 2005-02-22 2010-08-11 株式会社日立メタルプレシジョン Compressor impeller manufacturing method
US7231955B1 (en) * 2006-01-30 2007-06-19 United Technologies Corporation Investment casting mold design and method for investment casting using the same
FR2923524B1 (en) * 2007-11-12 2013-12-06 Snecma MOLDED METALLIC BLADE AND METHOD OF FABRICATING THE BLADE
FR2933884B1 (en) * 2008-07-16 2012-07-27 Snecma PROCESS FOR MANUFACTURING AN AUBING PIECE
CN201524792U (en) * 2009-10-10 2010-07-14 广东文灿压铸有限公司 Die casting mould for impellers

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5072771A (en) * 1988-03-28 1991-12-17 Pcc Airfoils, Inc. Method and apparatus for casting a metal article
US20040167270A1 (en) * 2003-02-25 2004-08-26 Dane Chang Fugitive pattern for casting
EP1604753A1 (en) * 2004-05-06 2005-12-14 United Technologies Corporation Investment casting
EP2092996A1 (en) * 2008-02-14 2009-08-26 United Technologies Corporation Method and apparatus for as-cast seal on turbine blades

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103433433A (en) * 2013-08-21 2013-12-11 丹阳市华明光学器材有限公司 Mold and method for manufacturing door closer shell
CN103433433B (en) * 2013-08-21 2015-03-25 丹阳市华明光学器材有限公司 Mold and method for manufacturing door closer shell
FR3033720A1 (en) * 2015-03-16 2016-09-23 Snecma FOUNDRY MOLD
FR3056994A1 (en) * 2016-09-30 2018-04-06 Safran CRYSTALLIZATION OVEN FOR THE PRODUCTION OF TURBOREACTOR BLADES WITH ONBOARD THERMAL SCREEN

Also Published As

Publication number Publication date
CN103212670A (en) 2013-07-24
FR2985923B1 (en) 2016-02-05
CN103212670B (en) 2016-12-28

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