FR2961552B1 - IMPACT COOLED CAVITY TURBINE TURBINE BLADE - Google Patents

IMPACT COOLED CAVITY TURBINE TURBINE BLADE

Info

Publication number
FR2961552B1
FR2961552B1 FR1054894A FR1054894A FR2961552B1 FR 2961552 B1 FR2961552 B1 FR 2961552B1 FR 1054894 A FR1054894 A FR 1054894A FR 1054894 A FR1054894 A FR 1054894A FR 2961552 B1 FR2961552 B1 FR 2961552B1
Authority
FR
France
Prior art keywords
turbine
blade
elements
turbine blade
cooled cavity
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
FR1054894A
Other languages
French (fr)
Other versions
FR2961552A1 (en
Inventor
Huu Thanh Tran
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 FR1054894A priority Critical patent/FR2961552B1/en
Priority to PCT/FR2011/051363 priority patent/WO2011161357A1/en
Publication of FR2961552A1 publication Critical patent/FR2961552A1/en
Application granted granted Critical
Publication of FR2961552B1 publication Critical patent/FR2961552B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F01D5/186—Film cooling
    • 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
    • B22C9/10—Cores; Manufacture or installation of cores
    • 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
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Abstract

The invention relates to a ceramic core for producing the inner cavities of a turbine blade by means of the lost-wax foundry technique, said ceramic core comprising at least two adjacent elements (6, 7) for creating two substantially parallel cavities for circulating the air for cooling said blade, said elements being separated from each other by a spacing for forming an inter-cavity wall, wherein a first element (6) is connected to the rest of the core by means of attachment elements (10), and a second element (7) is connected to a column base (8) for forming a cooling-air supply pipe, characterized in that said attachment elements (10) are exclusively located at the ends of the first element (6).
FR1054894A 2010-06-21 2010-06-21 IMPACT COOLED CAVITY TURBINE TURBINE BLADE Active FR2961552B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1054894A FR2961552B1 (en) 2010-06-21 2010-06-21 IMPACT COOLED CAVITY TURBINE TURBINE BLADE
PCT/FR2011/051363 WO2011161357A1 (en) 2010-06-21 2011-06-15 Core for the manufacture of a turbine blade having impact-cooled leading edge cavity

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1054894A FR2961552B1 (en) 2010-06-21 2010-06-21 IMPACT COOLED CAVITY TURBINE TURBINE BLADE

Publications (2)

Publication Number Publication Date
FR2961552A1 FR2961552A1 (en) 2011-12-23
FR2961552B1 true FR2961552B1 (en) 2014-01-31

Family

ID=43549195

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1054894A Active FR2961552B1 (en) 2010-06-21 2010-06-21 IMPACT COOLED CAVITY TURBINE TURBINE BLADE

Country Status (2)

Country Link
FR (1) FR2961552B1 (en)
WO (1) WO2011161357A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108698117A (en) * 2016-02-12 2018-10-23 赛峰集团 It is a kind of formed turbo blade dedusting hole method and relevant ceramic core

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2986982A1 (en) * 2012-02-22 2013-08-23 Snecma FOUNDRY CORE ASSEMBLY FOR MANUFACTURING A TURBOMACHINE BLADE, METHOD FOR MANUFACTURING A BLADE AND AUBE ASSOCIATED
FR3034128B1 (en) 2015-03-23 2017-04-14 Snecma CERAMIC CORE FOR MULTI-CAVITY TURBINE BLADE
FR3046736B1 (en) 2016-01-15 2021-04-23 Safran REFRACTORY CORE INCLUDING A MAIN BODY AND A SHELL
US10422229B2 (en) 2017-03-21 2019-09-24 United Technologies Corporation Airfoil cooling
FR3137316A1 (en) 2022-06-29 2024-01-05 Safran Aircraft Engines Ceramic core for hollow turbine blade with external holes

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4249291A (en) * 1979-06-01 1981-02-10 General Electric Company Method for forming a liquid cooled airfoil for a gas turbine
US5271715A (en) * 1992-12-21 1993-12-21 United Technologies Corporation Cooled turbine blade
US5498133A (en) * 1995-06-06 1996-03-12 General Electric Company Pressure regulated film cooling
US6340047B1 (en) * 1999-03-22 2002-01-22 General Electric Company Core tied cast airfoil
US6370752B1 (en) * 2000-04-21 2002-04-16 General Electric Company Method for repositioning or repairing holes
US7008186B2 (en) * 2003-09-17 2006-03-07 General Electric Company Teardrop film cooled blade
US20050265839A1 (en) * 2004-05-27 2005-12-01 United Technologies Corporation Cooled rotor blade
FR2874186B1 (en) 2004-08-12 2008-01-25 Snecma Moteurs Sa PROCESS FOR THE PRODUCTION BY LOST WAX MOLDING OF PARTS COMPRISING AT LEAST ONE CAVITY.
US7441331B2 (en) * 2004-08-26 2008-10-28 United Technologies Corporation Turbine engine component manufacture methods
FR2875425B1 (en) 2004-09-21 2007-03-30 Snecma Moteurs Sa PROCESS FOR MANUFACTURING A TURBOMACHINE BLADE, CORE ASSEMBLY FOR CARRYING OUT THE PROCESS
US7452186B2 (en) * 2005-08-16 2008-11-18 United Technologies Corporation Turbine blade including revised trailing edge cooling
US7249934B2 (en) * 2005-08-31 2007-07-31 General Electric Company Pattern cooled turbine airfoil
US7674093B2 (en) * 2006-12-19 2010-03-09 General Electric Company Cluster bridged casting core

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108698117A (en) * 2016-02-12 2018-10-23 赛峰集团 It is a kind of formed turbo blade dedusting hole method and relevant ceramic core

Also Published As

Publication number Publication date
WO2011161357A1 (en) 2011-12-29
FR2961552A1 (en) 2011-12-23

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