FR2985925A1 - Shell, useful for manufacturing bladed elements of turboshaft engine of aircraft by lost-wax casting, comprises thermal isolation coating carried out using set of thermal isolation strips for recovering part of external surface of shell - Google Patents

Shell, useful for manufacturing bladed elements of turboshaft engine of aircraft by lost-wax casting, comprises thermal isolation coating carried out using set of thermal isolation strips for recovering part of external surface of shell Download PDF

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Publication number
FR2985925A1
FR2985925A1 FR1250681A FR1250681A FR2985925A1 FR 2985925 A1 FR2985925 A1 FR 2985925A1 FR 1250681 A FR1250681 A FR 1250681A FR 1250681 A FR1250681 A FR 1250681A FR 2985925 A1 FR2985925 A1 FR 2985925A1
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France
Prior art keywords
shell
strip
bladed
elements
thermal isolation
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
FR1250681A
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French (fr)
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FR2985925B1 (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
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Priority to FR1250681A priority Critical patent/FR2985925B1/en
Publication of FR2985925A1 publication Critical patent/FR2985925A1/en
Application granted granted Critical
Publication of FR2985925B1 publication Critical patent/FR2985925B1/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
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
  • Powder Metallurgy (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

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), 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, and a thermal isolation coating carried out using a set of thermal isolation strips for recovering a part of an external surface of the shell. The thermal insulation strips surrounds each of the bladed shell elements along a radial portion of the shell elements. 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), 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, and a thermal isolation coating carried out using a set of thermal isolation strips for recovering a part of an external surface of the shell. The thermal insulation strips surround each of the bladed shell elements along a radial portion of the bladed shell elements and surround the shell. The coating presents a thermal gradient of resistance according to a radial direction of the bladed shell elements. The strips have same thermal resistance. 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 blade portion includes a zone of trailing edge and a zone of leading edge opposite to the zone of trailing edge. Each bladed shell element includes a metal tank connected to the second end part so as to extend from the zone of leading edge in remote. The thermal isolation stripes comprises: a first strip associated with each bladed shell element and surrounding its associated bladed shell element over an entire length according to a radial direction of the bladed shell elements; a second strip that is associated with each bladed shell element, partially recovers the first strip, surrounds its associated element on the radial portion and includes the first end part and the blade portion; a third strip surrounding a periphery of the shell to cover the casting arms, the first end part and a higher radial portion of the blade portion; a fourth strip partially recovering the third strip and surrounding the periphery of the shell to cover only the casting arms; a fifth strip surrounding the periphery of the shell to cover only the bladed shell elements; a sixth strip surrounding the periphery of the shell and the third strip to cover the radial portion, including the first end part and a portion of the part blade and extending into an annular window; a seventh strip surrounding the periphery of the shell to cover surfaces with the tank radially directed towards outside and radial ends of the second end part; an eighth strip surrounding the periphery of the shell and partially recovering the seventh strip to cover surfaces with the tanks directed radially towards outside; and a ninth strip orthogonally laid out with the central axis on which the ninth strip is centered and from which the ninth strip extends radially until covering a circumferential end of the eighth strip. The second strip is placed in an annular space centered on the central and defined between the tank and the zone of trailing edges. The second strip is centered on the central axis to cover the first strip and to surround an outside of the radial portion of each bladed shell element, and includes only one portion of the blade portion extending from the second end part. The second and third strips having opposite ends define the annular window at which the shell has no band. An independent claim is included for a method for manufacturing bladed elements of a turboshaft engine of an aircraft.
FR1250681A 2012-01-24 2012-01-24 CARAPLE FOR THE MANUFACTURE BY LOST WAX MOLDING OF AIRCRAFT TURBOMACHINE AIRCRAFT COMPONENTS COATED WITH THERMAL INSULATION BANDS Active FR2985925B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1250681A FR2985925B1 (en) 2012-01-24 2012-01-24 CARAPLE FOR THE MANUFACTURE BY LOST WAX MOLDING OF AIRCRAFT TURBOMACHINE AIRCRAFT COMPONENTS COATED WITH THERMAL INSULATION BANDS

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1250681A FR2985925B1 (en) 2012-01-24 2012-01-24 CARAPLE FOR THE MANUFACTURE BY LOST WAX MOLDING OF AIRCRAFT TURBOMACHINE AIRCRAFT COMPONENTS COATED WITH THERMAL INSULATION BANDS

Publications (2)

Publication Number Publication Date
FR2985925A1 true FR2985925A1 (en) 2013-07-26
FR2985925B1 FR2985925B1 (en) 2014-11-28

Family

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Family Applications (1)

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FR1250681A Active FR2985925B1 (en) 2012-01-24 2012-01-24 CARAPLE FOR THE MANUFACTURE BY LOST WAX MOLDING OF AIRCRAFT TURBOMACHINE AIRCRAFT COMPONENTS COATED WITH THERMAL INSULATION BANDS

Country Status (1)

Country Link
FR (1) FR2985925B1 (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105710306A (en) * 2016-02-26 2016-06-29 天津凯星科技有限公司 Mesopore feeding process of thick and large part in turbine shell casting turbine chamber
CN106238679A (en) * 2016-08-29 2016-12-21 中航动力股份有限公司 A kind of method preventing casting wax mould local contraction from deforming
CN108941459A (en) * 2018-09-05 2018-12-07 中国航发动力股份有限公司 A method of it is loose to reduce combustion engine turbine blade
WO2019202281A1 (en) * 2018-04-19 2019-10-24 Safran Aircraft Engines Method for producing a metal bladed element for a turbomachine of an aircraft
CN111570726A (en) * 2020-06-30 2020-08-25 中国航发动力股份有限公司 Guide blade mold and shrinkage design method thereof
WO2021099721A1 (en) * 2019-11-21 2021-05-27 Safran Aircraft Engines Foundry mold, method for manufacturing the mold and foundry method

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS571539A (en) * 1980-06-04 1982-01-06 Hitachi Ltd Casting method and mold
GB2259660A (en) * 1991-09-17 1993-03-24 Rolls Royce Plc A mould for casting components
US20040079510A1 (en) * 2002-10-29 2004-04-29 Pcc Airfoils, Inc. Method and apparatus for use during casting
JP2011045903A (en) * 2009-08-26 2011-03-10 Mitsubishi Heavy Ind Ltd Mold for turbine blade and method for manufacturing turbine blade

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS571539A (en) * 1980-06-04 1982-01-06 Hitachi Ltd Casting method and mold
GB2259660A (en) * 1991-09-17 1993-03-24 Rolls Royce Plc A mould for casting components
US20040079510A1 (en) * 2002-10-29 2004-04-29 Pcc Airfoils, Inc. Method and apparatus for use during casting
JP2011045903A (en) * 2009-08-26 2011-03-10 Mitsubishi Heavy Ind Ltd Mold for turbine blade and method for manufacturing turbine blade

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105710306A (en) * 2016-02-26 2016-06-29 天津凯星科技有限公司 Mesopore feeding process of thick and large part in turbine shell casting turbine chamber
CN106238679A (en) * 2016-08-29 2016-12-21 中航动力股份有限公司 A kind of method preventing casting wax mould local contraction from deforming
CN106238679B (en) * 2016-08-29 2019-11-12 中航动力股份有限公司 A method of prevent casting wax mould local contraction from deforming
WO2019202281A1 (en) * 2018-04-19 2019-10-24 Safran Aircraft Engines Method for producing a metal bladed element for a turbomachine of an aircraft
FR3080385A1 (en) * 2018-04-19 2019-10-25 Safran Aircraft Engines METHOD FOR MANUFACTURING A METALLIC WELDING ELEMENT FOR AN AIRCRAFT TURBOMACHINE
CN108941459A (en) * 2018-09-05 2018-12-07 中国航发动力股份有限公司 A method of it is loose to reduce combustion engine turbine blade
WO2021099721A1 (en) * 2019-11-21 2021-05-27 Safran Aircraft Engines Foundry mold, method for manufacturing the mold and foundry method
FR3103400A1 (en) * 2019-11-21 2021-05-28 Safran Aircraft Engines FOUNDRY MOLD, MOLD MANUFACTURING PROCESS AND FOUNDRY PROCESS
US11745254B2 (en) 2019-11-21 2023-09-05 Safran Aircraft Engines Foundry mold, method for manufacturing the mold and foundry method
CN111570726A (en) * 2020-06-30 2020-08-25 中国航发动力股份有限公司 Guide blade mold and shrinkage design method thereof

Also Published As

Publication number Publication date
FR2985925B1 (en) 2014-11-28

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