KR920006057A - Gas turbine and gas turbine blade and manufacturing method of this gas turbine blade - Google Patents

Gas turbine and gas turbine blade and manufacturing method of this gas turbine blade Download PDF

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Publication number
KR920006057A
KR920006057A KR1019910015986A KR910015986A KR920006057A KR 920006057 A KR920006057 A KR 920006057A KR 1019910015986 A KR1019910015986 A KR 1019910015986A KR 910015986 A KR910015986 A KR 910015986A KR 920006057 A KR920006057 A KR 920006057A
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KR
South Korea
Prior art keywords
gas turbine
turbine blade
shank
protrusions
blade according
Prior art date
Application number
KR1019910015986A
Other languages
Korean (ko)
Other versions
KR0185206B1 (en
Inventor
아끼라 요시나리
도시아끼 사이또
가쓰미 이이지마
다다미 이시다
료조 하시다
키미오 가노
Original Assignee
미다 가쓰시게
가부시기가이샤 하다찌 세이사꾸쇼
아께마 데루유끼
도호꾸 덴료꾸 가부시기가이샤
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.)
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Publication date
Application filed by 미다 가쓰시게, 가부시기가이샤 하다찌 세이사꾸쇼, 아께마 데루유끼, 도호꾸 덴료꾸 가부시기가이샤 filed Critical 미다 가쓰시게
Publication of KR920006057A publication Critical patent/KR920006057A/en
Application granted granted Critical
Publication of KR0185206B1 publication Critical patent/KR0185206B1/en

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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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • 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

내용 없음No content

Description

가스터빈 및 가스터빈 블레이드와 이 가스터빈 블레이드의 제조방법Gas turbine and gas turbine blade and manufacturing method of this gas turbine blade

본 내용은 요부공개 건이므로 전문내용을 수록하지 않았음As this is a public information case, the full text was not included.

제1도는 본 발명의 한 실시예에 따른 터빈회전익의 사시도.1 is a perspective view of a turbine rotor blade according to an embodiment of the present invention.

제2도는 제1도에 나타낸 터빈회전익의 제조방법을 나타내는 것으로, 주형의 종단면도.FIG. 2 is a longitudinal sectional view of the mold, showing the method of manufacturing the turbine rotor blade shown in FIG. 1. FIG.

제3도는 본 발명의 다른 실시예의 터빈회전익을 나타내는 정면도.3 is a front view showing a turbine rotor blade of another embodiment of the present invention.

Claims (11)

압축기와; 연소라이너와; 터빈디스크에 고정된 도브테일을 구비하고 180mm이상의 전체 길이를 가지며 단결정인상을 갖는 단결정의 Ni기 합금으로 만들어지는 단일단 또는 복수단의 터빈블레이드와; 상기 터빈블레이드에 대응하여 제공되는터빈노즐을 포함하는 강력한 가스터빈에 있어서, 작동가스온도가 1400℃ 이상이고, 초단 블레이드의 금속온도가 사용응력하에서 1000℃ 이상인 것을 특징으로 하는 가스터빈.A compressor; A combustion liner; It has a dovetail fixed to the turbine disk and has a total length of more than 180mm A single stage or multiple stage turbine blade made of a single crystal Ni-based alloy having a phase; A powerful gas turbine including a turbine nozzle provided corresponding to the turbine blade, wherein the working gas temperature is 1400 ° C. or more, and the metal temperature of the ultra-short blades is 1000 ° C. or more under use stress. 디스크에 고정되는 부분으로 되는 도브테일과; 이 도브테일에 연결되고 도브테일의 측면에 일체로 형성되는 하나 이상의 돌기를 구비하는 생크와; 이 생크에 연결되는 익부를 포함하는 가스터빈블레이드에 있어서, 단결정 구조로 형성되는상에서´이 사실상 석출되는 Ni기 합금으로 상기 가스터빈블레이드를 만드는 것을 특징으로 하는 가스터빈블레이드.A dovetail which is a part fixed to the disk; A shank having at least one protrusion connected to the dovetail and integrally formed at a side of the dovetail; In the gas turbine blade including the blade portion connected to the shank, it is formed of a single crystal structure On A gas turbine blade, wherein the gas turbine blade is made of a Ni-based alloy in which ´ is substantially precipitated. 제2항에 있어서, 상기 생크에 있는 돌기들이 익부가 회전하는 표면을 따라 양 표면에 있는 단일단 또는 복수단의 시일부인 것을 특징으로 하는 가스터빈블레이드.3. The gas turbine blade according to claim 2, wherein the protrusions on the shank are single or multiple stage seals on both surfaces along the surface on which the blades rotate. 제3항에 있어서, 각 시일부의 모서리가 상기 익부를 향하여 구부러지며 가스흐름을 밀폐하기 위하여 노즐에 관하여 미끄러지는 구조를 갖는 것을 특징으로 하는 가스터빈블레이드.4. The gas turbine blade according to claim 3, wherein an edge of each seal portion is bent toward the blade portion and has a structure that slides with respect to the nozzle to seal the gas flow. 제2항에 있어서, 상기 생크부에 있는 돌기가 상기 익부가 회전하는 표면을 교차하는 양표면에 있는 하나의 플랫폼인 것인 것을 특징으로 하는 가스터빈블레이드.3. The gas turbine blade according to claim 2, wherein the protrusion on the shank portion is one platform on both surfaces intersecting a surface on which the blade portion rotates. 제2항에 있어서, 돌기들을 구비하는 상기 생크가 15cm2이상의 단면적을 갖는 것을 특징으로 하는 가스터빈블레이드.The gas turbine blade according to claim 2, wherein the shank having protrusions has a cross-sectional area of 15 cm 2 or more. 제3항에 있어서, 돌기들을 구비하는 상기 생크가 15cm2이상의 단면적을 갖는 것을 특징으로 하는 가스터빈블레이드.4. The gas turbine blade according to claim 3, wherein the shank having protrusions has a cross-sectional area of at least 15 cm 2 . 제4항에 있어서, 돌기들을 구비하는 상기 생크가 15cm2이상의 단면적을 갖는 것을 특징으로 하는 가스터빈블레이드.5. The gas turbine blade according to claim 4, wherein the shank having protrusions has a cross-sectional area of 15 cm 2 or more. 제5항에 있어서, 돌기들을 구비하는 상기 생크가 15cm2이상의 단면적을 갖는 것을 특징으로 하는 가스터빈블레이드.6. The gas turbine blade according to claim 5, wherein the shank having protrusions has a cross-sectional area of at least 15 cm 2 . 제2항에 있어서,´상이상의 단결정기지에서 석출되는 Ni기 합금으로 도브레일과 돌기를 포함하는 상기 익부와 생크를 만드는 것을 특징으로 하는 가스터빈.The method of claim 2, disparity A gas turbine comprising a blade and a shank including a dobrail and a protrusion made of a Ni-based alloy deposited on a single crystal base of a phase. 제3항에 있어서,´상이상의 단결정기지에서 석출되는 Ni기 합금으로 도브레일과 돌기를 포함하는 상기 익부와 생크를 만드는 것을 특징으로 하는 가스터빈.The method of claim 3, disparity A gas turbine comprising a blade and a shank including a dobrail and a protrusion made of a Ni-based alloy deposited on a single crystal base of a phase. ※ 참고사항 : 최초출원 내용에 의하여 공개하는 것임.※ Note: The disclosure is based on the initial application.
KR1019910015986A 1990-09-14 1991-09-13 Gas turbine, gas turbine blade used therefor and manufacturing method for gas turbine blade KR0185206B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP90-245210 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
KR920006057A true KR920006057A (en) 1992-04-27
KR0185206B1 KR0185206B1 (en) 1999-04-01

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KR1019910015986A KR0185206B1 (en) 1990-09-14 1991-09-13 Gas turbine, gas turbine blade used therefor and manufacturing method for gas turbine blade

Country Status (6)

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

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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
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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
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Also Published As

Publication number Publication date
KR0185206B1 (en) 1999-04-01
CA2051133C (en) 2000-08-29
DE69128580D1 (en) 1998-02-12
DE69128580T2 (en) 1998-04-30
EP0475428B1 (en) 1998-01-07
CA2051133A1 (en) 1992-03-15
CN1060890A (en) 1992-05-06
CN1034828C (en) 1997-05-07
JP2729531B2 (en) 1998-03-18
JPH04124237A (en) 1992-04-24
EP0475428A1 (en) 1992-03-18

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