CA2051133A1 - Gas turbine, gas turbine blade used therefor and manufacturing method for gas turbine blade - Google Patents

Gas turbine, gas turbine blade used therefor and manufacturing method for gas turbine blade

Info

Publication number
CA2051133A1
CA2051133A1 CA2051133A CA2051133A CA2051133A1 CA 2051133 A1 CA2051133 A1 CA 2051133A1 CA 2051133 A CA2051133 A CA 2051133A CA 2051133 A CA2051133 A CA 2051133A CA 2051133 A1 CA2051133 A1 CA 2051133A1
Authority
CA
Canada
Prior art keywords
gas turbine
turbine blade
turbine
less
manufacturing
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
CA2051133A
Other languages
French (fr)
Other versions
CA2051133C (en
Inventor
Akira Yoshinari
Tosiaki Saito
Katsumi Iijima
Tadami Ishida
Ryozo Hashida
Kimio Kano
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.)
Tohoku Electric Power Co Inc
Hitachi Ltd
Original Assignee
Akira Yoshinari
Tosiaki Saito
Katsumi Iijima
Tadami Ishida
Ryozo Hashida
Kimio Kano
Hitachi, Ltd.
Tohoku Electric Power Co. Inc.
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 Akira Yoshinari, Tosiaki Saito, Katsumi Iijima, Tadami Ishida, Ryozo Hashida, Kimio Kano, Hitachi, Ltd., Tohoku Electric Power Co. Inc. filed Critical Akira Yoshinari
Publication of CA2051133A1 publication Critical patent/CA2051133A1/en
Application granted granted Critical
Publication of CA2051133C publication Critical patent/CA2051133C/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D3/00—Pig or like casting
    • 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
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/607—Monocrystallinity

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Crystals, And After-Treatments Of Crystals (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A heavy-duty gas turbine includes a compressor; a combustion liner; a turbine blade in a single stage or multi-stages; and a turbine nozzle provided in correspondence to the turbine blade. The turbine blade has a dovetail secured to a turbine disk and has an overall length of not less than 180 mm, and it is made of a single-crystal Ni-base alloy whose .gamma. phase is a single crystal.
Operating gas temperature is not less than 1400°C, and metal temperature of a first blade is not less than 1000°C
under working stress.
CA002051133A 1990-09-14 1991-09-11 Gas turbine, gas turbine blade used therefor and manufacturing method for gas turbine blade Expired - Fee Related CA2051133C (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2-245210 1990-09-14
JP2245210A JP2729531B2 (en) 1990-09-14 1990-09-14 Gas turbine blade, method of manufacturing the same, and gas turbine

Publications (2)

Publication Number Publication Date
CA2051133A1 true CA2051133A1 (en) 1992-03-15
CA2051133C CA2051133C (en) 2000-08-29

Family

ID=17130269

Family Applications (1)

Application Number Title Priority Date Filing Date
CA002051133A Expired - Fee Related CA2051133C (en) 1990-09-14 1991-09-11 Gas turbine, gas turbine blade used therefor and manufacturing method for gas turbine blade

Country Status (6)

Country Link
EP (1) EP0475428B1 (en)
JP (1) JP2729531B2 (en)
KR (1) KR0185206B1 (en)
CN (1) CN1034828C (en)
CA (1) CA2051133C (en)
DE (1) DE69128580T2 (en)

Families Citing this family (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0560296B1 (en) * 1992-03-09 1998-01-14 Hitachi Metals, Ltd. Highly hot corrosion resistant and high-strength superalloy, highly hot corrosion resistant and high-strength casting having single crystal structure, gas turbine and combined cycle power generation system
EP0637476B1 (en) * 1993-08-06 2000-02-23 Hitachi, Ltd. Blade for gas turbine, manufacturing method of the same, and gas turbine including the blade
JPH0959747A (en) * 1995-08-25 1997-03-04 Hitachi Ltd High strength heat resistant cast steel, steam turbine casing, steam turbine electric power plant, and steam turbine
JP3209902B2 (en) * 1995-11-06 2001-09-17 キャノン・マスキーガン・コーポレーション High temperature corrosion resistant single crystal nickel-based superalloys
KR100530759B1 (en) * 1999-02-18 2005-11-23 삼성테크윈 주식회사 Gas turbine engine for the aircraft
DE10100790C2 (en) * 2001-01-10 2003-07-03 Mtu Aero Engines Gmbh Nickel-based alloy for the cast-technical production of solidified components
US7526965B2 (en) * 2006-12-30 2009-05-05 General Electric Company Method for evaluating burnishing element condition
JP5232492B2 (en) 2008-02-13 2013-07-10 株式会社日本製鋼所 Ni-base superalloy with excellent segregation
US20100071812A1 (en) * 2008-09-25 2010-03-25 General Electric Company Unidirectionally-solidification process and castings formed thereby
JP5063550B2 (en) * 2008-09-30 2012-10-31 株式会社日立製作所 Nickel-based alloy and gas turbine blade using the same
KR101023783B1 (en) * 2009-08-05 2011-03-21 한국전력공사 Stator vane set structure of gas turbine compressor
US8226886B2 (en) * 2009-08-31 2012-07-24 General Electric Company Nickel-based superalloys and articles
US9039375B2 (en) * 2009-09-01 2015-05-26 General Electric Company Non-axisymmetric airfoil platform shaping
US8641381B2 (en) * 2010-04-14 2014-02-04 General Electric Company System and method for reducing grain boundaries in shrouded airfoils
JP5396445B2 (en) * 2011-08-29 2014-01-22 株式会社日立製作所 gas turbine
US10287897B2 (en) 2011-09-08 2019-05-14 General Electric Company Turbine rotor blade assembly and method of assembling same
KR101427801B1 (en) * 2011-12-30 2014-09-25 두산중공업 주식회사 Blade for gas turbin compressor and manufacturing method thereof
US20130177438A1 (en) * 2012-01-06 2013-07-11 General Electric Company Sectioned rotor, a steam turbine having a sectioned rotor and a method for producing a sectioned rotor
US9097128B2 (en) * 2012-02-28 2015-08-04 General Electric Company Seals for rotary devices and methods of producing the same
CN104411921A (en) * 2012-06-30 2015-03-11 通用电气公司 A turbine blade sealing structure
CA2922760C (en) 2013-09-11 2018-10-09 General Electric Company Ply architecture for integral platform and damper retaining features in cmc turbine blades
US10830357B2 (en) 2015-04-24 2020-11-10 Raytheon Technologies Corporation Single crystal grain structure seals and method of forming
CN105108061A (en) * 2015-09-30 2015-12-02 东方电气集团东方汽轮机有限公司 Method of eliminating stray grain defect in single crystal blade
EP3677697A1 (en) * 2019-01-07 2020-07-08 Siemens Aktiengesellschaft Co-alloy for additive manufacturing and method
FR3105048B1 (en) * 2019-12-20 2022-08-05 Safran MANUFACTURING SOLUTION FOR A MONOBLOC BLADE DISC
CN114872909B (en) * 2022-05-06 2023-03-24 中国航发四川燃气涡轮研究院 Aircraft type turbine blade cooling channel heat exchange structure

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1030829A (en) * 1965-04-27 1966-05-25 Rolls Royce Aerofoil blade for use in a hot fluid stream
US4371404A (en) * 1980-01-23 1983-02-01 United Technologies Corporation Single crystal nickel superalloy
FR2503188A1 (en) * 1981-04-03 1982-10-08 Onera (Off Nat Aerospatiale) MONOCRYSTALLINE SUPERALLIAGE WITH MATRIX MATRIX BASED ON NICKEL, PROCESS FOR IMPROVING WORKPIECES IN THIS SUPERALLIATION AND PARTS OBTAINED THEREBY

Also Published As

Publication number Publication date
EP0475428B1 (en) 1998-01-07
JP2729531B2 (en) 1998-03-18
EP0475428A1 (en) 1992-03-18
DE69128580D1 (en) 1998-02-12
DE69128580T2 (en) 1998-04-30
CN1060890A (en) 1992-05-06
KR920006057A (en) 1992-04-27
CA2051133C (en) 2000-08-29
KR0185206B1 (en) 1999-04-01
CN1034828C (en) 1997-05-07
JPH04124237A (en) 1992-04-24

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Legal Events

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