JP2015094268A5 - - Google Patents

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JP2015094268A5
JP2015094268A5 JP2013233618A JP2013233618A JP2015094268A5 JP 2015094268 A5 JP2015094268 A5 JP 2015094268A5 JP 2013233618 A JP2013233618 A JP 2013233618A JP 2013233618 A JP2013233618 A JP 2013233618A JP 2015094268 A5 JP2015094268 A5 JP 2015094268A5
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Japan
Prior art keywords
gas turbine
turbine blade
core
cooling
pin fin
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JP2013233618A
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Japanese (ja)
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JP2015094268A (en
JP6216618B2 (en
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Priority to JP2013233618A priority Critical patent/JP6216618B2/en
Priority claimed from JP2013233618A external-priority patent/JP6216618B2/en
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Publication of JP2015094268A5 publication Critical patent/JP2015094268A5/ja
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Claims (6)

中子を用いて形成された冷却通路を備えたガスタービン翼であって、前記中子には前記冷却通路の一部として少なくともピンフィン通路を形成するための複数のピンフィン形成孔が形成されており、前記中子の隣接する前記ピンフィン形成孔同士の間を接続するブリッジ部を追加工により形成し、追加工された前記中子を用いることで形成された長円型ピンフィンを有するピンフィン通路を備えたことを特徴とするガスタービン翼。 A gas turbine blade having a cooling 却通 path formed by using a core, a plurality of pin fins formed holes for forming at least the pin fin passage as a part of the cooling passage is formed in the core A pin fin passage having an oval pin fin formed by using an additional process to form a bridge portion connecting the pin fin forming holes adjacent to each other in the core. A gas turbine blade characterized by comprising: 請求項１に記載のガスタービン翼において、前記冷却通路として蛇行型冷却通路を備えたことを特徴とするガスタービン翼。 In a gas turbine blade according to claim 1, a gas turbine blade, characterized in that it comprises a serpentine cooling 却通 path as the cold 却通 path. 請求項１又は２に記載のガスタービン翼であって、前記ピンフィン通路の外周側にフィルム冷却孔を備えたことを特徴とするガスタービン翼。 A gas turbine blade according to claim 1 or 2, a gas turbine blade, characterized in that it comprises a film-cooling hole to the outer peripheral side of the Pinfi down communication channel. 請求項１乃至３の何れか一項に記載のガスタービン翼を備えたガスタービン。 A gas turbine comprising the gas turbine blade according to any one of claims 1 to 3. 請求項１に記載のガスタービン翼を、静止した部材に取り付けられる静翼として複数備えたガスタービンであって、
前記複数の静翼は、互いに異なる追加工を施された前記中子を用いることにより製作された異なる数の長円型ピンフィンを有する静翼から構成され、ガスタービンの周方向位置によって、異なる数の長円型ピンフィンを有する前記静翼が配置されていることを特徴とするガスタービン。 A gas turbine comprising a plurality of gas turbine blades according to claim 1 as stationary blades attached to a stationary member,
Wherein the plurality of stator blades is composed of stator blades having a different number of oblong pin fins which are more fabricate the core having been subjected to different additional machining each other and Mochiiruko, by a circumferential position of the gas turbine, A gas turbine comprising the stationary blades having different numbers of oval pin fins. 冷却通路の一部であるピンフィン通路を形成するための複数のピンフィン形成孔が形成された中子を用いたガスタービン翼の製造方法であって、
前記冷却通路に供給する冷却空気量に応じて、前記中子の隣接する前記ピンフィン形成孔同士の間を接続するブリッジ部を追加工により形成する工程と、前記ブリッジ部を形成した中子を用いて鋳造を行なう工程とを備えたことを特徴とするガスタービン翼の製造方法。 A method of manufacturing a gas turbine blade using a core in which a plurality of pin fin formation holes for forming a pin fin passage which is a part of a cooling passage is formed,
In accordance with the amount of cooling air supplied to the cooling passage, a step of forming a bridge portion for connecting between the pin fin forming holes adjacent to each other by an additional process, and a core formed with the bridge portion are used. And a step of casting the gas turbine blade.
JP2013233618A 2013-11-12 2013-11-12 Gas turbine blade manufacturing method Active JP6216618B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP2013233618A JP6216618B2 (en) 2013-11-12 2013-11-12 Gas turbine blade manufacturing method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2013233618A JP6216618B2 (en) 2013-11-12 2013-11-12 Gas turbine blade manufacturing method

Publications (3)

Publication Number Publication Date
JP2015094268A JP2015094268A (en) 2015-05-18
JP2015094268A5 true JP2015094268A5 (en) 2016-10-20
JP6216618B2 JP6216618B2 (en) 2017-10-18

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JP2013233618A Active JP6216618B2 (en) 2013-11-12 2013-11-12 Gas turbine blade manufacturing method

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Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6033391B1 (en) * 2015-11-24 2016-11-30 三菱日立パワーシステムズ株式会社 Gas turbine operation control method, refurbishment method, and gas turbine control device setting change method
CN109441555A (en) * 2018-12-26 2019-03-08 哈尔滨广瀚动力技术发展有限公司 A kind of marine gas turbine turbine rotor blade cooling structure

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3921271A (en) * 1973-01-02 1975-11-25 Gen Electric Air-cooled turbine blade and method of making same
US4515526A (en) * 1981-12-28 1985-05-07 United Technologies Corporation Coolable airfoil for a rotary machine
US4474532A (en) * 1981-12-28 1984-10-02 United Technologies Corporation Coolable airfoil for a rotary machine
US4775296A (en) * 1981-12-28 1988-10-04 United Technologies Corporation Coolable airfoil for a rotary machine
US5337805A (en) * 1992-11-24 1994-08-16 United Technologies Corporation Airfoil core trailing edge region
JP3164972B2 (en) * 1993-08-06 2001-05-14 株式会社日立製作所 Moving blade for gas turbine, method of manufacturing the same, and gas turbine using the same
JPH0828297A (en) * 1994-07-28 1996-01-30 Hitachi Ltd High temperature gas turbine and combined generating plant
JP4092674B2 (en) * 1999-03-02 2008-05-28 日立金属株式会社 Molding method of wax model with ceramic core
US7014424B2 (en) * 2003-04-08 2006-03-21 United Technologies Corporation Turbine element
JP2006097983A (en) * 2004-09-29 2006-04-13 Mitsubishi Heavy Ind Ltd Gas turbine combustor
US7377747B2 (en) * 2005-06-06 2008-05-27 General Electric Company Turbine airfoil with integrated impingement and serpentine cooling circuit
US20080028606A1 (en) * 2006-07-26 2008-02-07 General Electric Company Low stress turbins bucket

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