WO2011102014A1 - ガスタービンケーシング構造 - Google Patents
ガスタービンケーシング構造 Download PDFInfo
- Publication number
- WO2011102014A1 WO2011102014A1 PCT/JP2010/065467 JP2010065467W WO2011102014A1 WO 2011102014 A1 WO2011102014 A1 WO 2011102014A1 JP 2010065467 W JP2010065467 W JP 2010065467W WO 2011102014 A1 WO2011102014 A1 WO 2011102014A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- half casing
- casing
- gas turbine
- lower half
- upper half
- Prior art date
Links
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- 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
- F05D2240/00—Components
- F05D2240/55—Seals
-
- 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
- F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
- F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
Definitions
- the present invention relates to a gas turbine casing structure.
- the gas turbine casing of the gas turbine in which components such as the rotor and nozzle diaphragm are housed is a horizontal structure with a flange structure to facilitate the installation and inspection of these components and to prevent gas leakage during operation. It is comprised by the 2 split bolt fastening structure (for example, refer the following patent document 1).
- FIG. 3 is a schematic view showing a conventional gas turbine casing structure.
- bolt is shown.
- the gas turbine casing structure is divided into two parts, an upper half casing 100 and a lower half casing 101.
- the upper half casing 100 and the lower half casing 101 are constituted by shell portions 100a and 101a and flange portions 100b and 101b.
- the upper half casing 100 and the lower half casing 101 are coupled to each other by fastening with a bolt 102, an upper nut 103, and a lower nut 104.
- the flange of the gas turbine casing is divided into two parts, a flange part 100b of the upper half casing 100 and a flange part 101b of the lower half casing 101, and the flange parts 100b, 101b are provided with a large number of bolt holes 100c, 101c.
- the bolts 102 are disposed in the respective bolt holes 100 c and 101 c and fastened by the upper nut 103 and the lower nut 104.
- FIG. 5 is a schematic view showing a conventional gas turbine casing structure having a raised flange portion.
- bolt is shown.
- the height of the flange portion 100b of the upper half casing 100 and the flange portion 101b of the lower half casing 101 are increased, and the thickness of the shell portions 100a and 101a is increased at the center of the thickness.
- Fastening with the bolt 102, the upper nut 103, and the lower nut 104 is advantageous because the moment at the time of applying pressure as shown by an arrow P in FIG. 5 can be reduced.
- an object of the present invention is to provide a gas turbine casing structure that can prevent gas leakage when pressure is applied.
- a gas turbine casing structure for solving the above-described problem is In the gas turbine casing structure in which the flange portion is divided in two horizontally into an upper half casing and a lower half casing, Bolts installed across the upper half casing and the lower half casing on the inner surfaces of the upper half casing and the lower half casing; An upper nut installed on the inner surface of the upper half casing and attached to the bolt; A gas turbine casing structure comprising: a lower nut installed on an inner surface of the lower half casing and attached to the bolt.
- a gas turbine casing structure for solving the above problems is as follows: In the gas turbine casing structure in which the flange portion is divided in two horizontally into an upper half casing and a lower half casing, The upper half casing and the lower half casing can operate separately between the groove formed in the flange portion of the upper half casing and the groove formed in the flange portion of the lower half casing. A separate member; A seal member installed on each of the upper surface, the lower surface, the upper side surface on the inner surface side of the upper half casing, and the concave portion formed on the lower side surface on the inner surface side of the lower half casing.
- a gas turbine casing structure characterized by that.
- a gas turbine casing structure according to a third aspect of the present invention for solving the above problem is the gas turbine casing structure according to the second aspect of the present invention.
- the seal member is arranged at a position where the upper half casing and the lower half casing come into contact with each other and can be sealed when pressure is applied.
- FIG. 1 is a schematic view showing a cross section of a gas turbine casing structure according to this embodiment.
- 1A is a schematic diagram showing a cross section in the axial direction of the bolt
- FIG. 1B shows a cross-sectional view taken along the arrow AA in FIG. 1A. It is a schematic diagram.
- the gas turbine casing structure according to the present embodiment is divided into an upper half casing 10 and a lower half casing 11 in the horizontal direction at the flange portion.
- the upper half casing 10 and the lower half casing 11 are constituted by shell portions 10a and 11a and flange portions 10b and 11b.
- a bolt installation groove 10c for installing the bolt 12 across the inner surface of the flange portion 10b of the upper half casing 10 and the inner surface of the flange portion 11b of the lower half casing 11 is provided. 11c is formed.
- a recess 10d for installing the upper nut 13 is formed above the bolt installation groove 10c on the inner surface of the flange portion 10b of the upper half casing 10, and a bolt installation groove 11c on the inner surface of the flange portion 11b of the lower half casing 11 is provided.
- a recess 11d for installing the lower nut 14 is formed in the upper part.
- the lower wall surface of the recess 10d for installing the upper nut 13 of the upper half casing 10 is a seat surface 10e of the upper nut 13, and the lower half
- the upper wall surface of the recess 11 d for installing the lower nut 15 of the casing 11 is a seat surface 11 e of the lower nut 14.
- the upper half casing 10 and the lower half casing 11 are joined by fastening the bolt 12 and the upper nut 13 on the inner surface of the upper half casing 10 and fastening the lower nut 14 on the inner surface of the lower half casing 11. is doing.
- the bolts 12 are arranged on the inner surfaces of the upper half casing 10 and the lower half casing 11 so as to be outside the flange portion as in the conventional gas turbine casing structure. Compared with the case where the bolt is arranged, the moment force at the time of pressure load can be minimized. Thereby, the opening amount of the flange part 10b of the upper half casing 10 and the flange part 11b of the lower half casing 11 can be made small.
- the bolt holes 100c and 101c penetrate the flanges 10b and 11b as in the conventional gas turbine casing structure. Therefore, leakage of gas from the bolt holes 100c and 101c can be eliminated.
- FIG. 2 is a schematic view showing a cross section of the gas turbine casing structure according to this embodiment.
- FIG. 2 is a schematic diagram showing a cross section in the axial direction of the bolt.
- the gas turbine casing structure includes an upper half casing 20 and a lower half casing 21.
- the upper half casing 20 and the lower half casing 21 are configured by shell portions 20a and 21a and flange portions 20b and 21b.
- a bolt hole 20 c is formed in the flange portion 20 b of the upper half casing 20, and a bolt hole 21 c is formed in the flange portion 21 b of the lower half casing 21.
- the upper half casing 20 and the lower half casing 21 are coupled to each other by fastening with bolts 22, upper nuts 23 and lower nuts 24 installed in the bolt holes 20c and 21c.
- the groove 20d is formed inside the flange portion 20b of the upper half casing 20
- the groove 21d is formed inside the flange portion 21b of the lower half casing 21, and the flange portion 20b. , 21b, and a separate member 24 that can operate separately.
- the separate member 25 has a recess 25 a formed on the upper surface, a recess 25 b formed on the lower surface, a recess 25 c formed on the upper side surface on the inner surface side of the upper half casing 20, and the inner surface side of the lower half casing 21. Concave portion 25d is formed on the lower side surface.
- Seal members 26 are installed in the recesses 25a, 25b, 25c, and 25d of the separate member 25, respectively. In this embodiment, a metal E seal is used as the seal member 26.
- FIG. 3 is a schematic view showing a cross section of the gas turbine casing structure according to this embodiment when pressure is applied.
- FIG. 3 is a schematic diagram showing a cross section in the axial direction of the bolt. Further, in FIG. 3, for the sake of understanding, the expression is exaggerated from the actual one.
- the separate member 25 inserted between the groove 20d and the groove 21d is subjected to the flange portion 20b when pressure is applied as indicated by an arrow P in FIG. , 21b, and the seal member 26 comes into contact with the upper half casing 20 and the lower half casing 21 to perform sealing. That is, the seal member 26 is disposed at a position where it can be sealed in contact with the upper half casing 20 and the lower half casing 21 in advance when pressure is applied.
- the sealing of the gas can be reliably performed by installing the sealing member 26 in the concave portion of the separate member 25 inserted between the groove 20d and the groove 21d. it can.
- the gas turbine casing structure of the present invention it is possible to provide a gas turbine casing structure that can prevent gas leakage when pressure is applied.
- the present invention can be used for a gas turbine casing structure of a gas turbine, for example.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gasket Seals (AREA)
Abstract
Description
図3に示すように、ガスタービンケーシング構造は、上側半ケーシング100と下側半ケーシング101とに2分割されている。上側半ケーシング100及び下側半ケーシング101は、シェル部100a,101aとフランジ部100b,101bとにより構成されている。上側半ケーシング100と下側半ケーシング101との結合は、ボルト102と上側ナット103及び下側ナット104とにより締結して行われる。
図5に示すように、ガスの漏れを防ぐためには、上側半ケーシング100のフランジ部100bと下側半ケーシング101のフランジ部101bの高さを高くし、シェル部100a,101aの肉厚中央でボルト102と上側ナット103及び下側ナット104により締結する方が図5中に矢印Pで示すような圧力付加時のモーメントを小さくすることができるため有利である。
フランジ部において水平方向に上側半ケーシングと下側半ケーシングとに2分割されるガスタービンケーシング構造において、
前記上側半ケーシングと前記下側半ケーシングの内面に前記上側半ケーシングと前記下側半ケーシングに亘って設置されるボルトと、
前記上側半ケーシングの内面に設置され前記ボルトに取り付けられる上側ナットと、
前記下側半ケーシングの内面に設置され前記ボルトに取り付けられる下側ナットと
を備える
ことを特徴とするガスタービンケーシング構造。
フランジ部において水平方向に上側半ケーシングと下側半ケーシングとに2分割されるガスタービンケーシング構造において、
前記上側半ケーシングのフランジ部に形成された溝と、前記下側半ケーシングのフランジ部に形成された溝との間に、前記上側半ケーシングと前記下側半ケーシングと別々に動作することができる別体部材と、
前記別体部材の上面と、下面と、前記上側半ケーシング内面側の上部側面と、前記下側半ケーシングの内面側の下部側面とに形成された凹部とにそれぞれ設置されるシール部材と
を備える
ことを特徴とするガスタービンケーシング構造。
前記シール部材は、圧力付加時に前記上側半ケーシングと前記下側半ケーシングと接触してシールが可能となる位置に配置される
ことを特徴とする。
図1は、本実施例に係るガスタービンケーシング構造の断面を示した模式図である。なお、図1(a)は、ボルトの軸方向における断面を示した模式図であり、図1(b)は、図1(a)中に矢印A-Aで示す断面における矢視図を示した模式図である。
図2は、本実施例に係るガスタービンケーシング構造の断面を示した模式図である。なお、図2は、ボルトの軸方向における断面を示した模式図である。
10a シェル部
10b フランジ部
10c ボルト設置溝
10d 凹部
10e 座面
11 下側半ケーシング
11a シェル部
11b フランジ部
11c ボルト設置溝
11d 凹部
11e 座面
12 ボルト
13 上側ナット
14 下側ナット
20 上側半ケーシング
20a シェル部
20b フランジ部
20c ボルト穴
20d 溝
21 下側半ケーシング
21a シェル部
21b フランジ部
21c ボルト穴
21d 溝
22 ボルト
23 上側ナット
24 下側ナット
25 別体部材
25a、25b,25c,25d 凹部
26 シール部材
Claims (3)
- フランジ部において水平方向に上側半ケーシングと下側半ケーシングとに2分割されるガスタービンケーシング構造において、
前記上側半ケーシングと前記下側半ケーシングの内面に前記上側半ケーシングと前記下側半ケーシングに亘って設置されるボルトと、
前記上側半ケーシングの内面に設置され前記ボルトに取り付けられる上側ナットと、
前記下側半ケーシングの内面に設置され前記ボルトに取り付けられる下側ナットと
を備える
ことを特徴とするガスタービンケーシング構造。 - フランジ部において水平方向に上側半ケーシングと下側半ケーシングとに2分割されるガスタービンケーシング構造において、
前記上側半ケーシングのフランジ部に形成された溝と、前記下側半ケーシングのフランジ部に形成された溝との間に、前記上側半ケーシングと前記下側半ケーシングと別々に動作することができる別体部材と、
前記別体部材の上面と、下面と、前記上側半ケーシング内面側の上部側面と、前記下側半ケーシングの内面側の下部側面とに形成された凹部とにそれぞれ設置されるシール部材と
を備える
ことを特徴とするガスタービンケーシング構造。 - 前記シール部材は、圧力付加時に前記上側半ケーシングと前記下側半ケーシングと接触してシールが可能となる位置に配置される
ことを特徴とする請求項2に記載のガスタービンケーシング構造。
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10846146A EP2538054A1 (en) | 2010-02-19 | 2010-09-09 | Structure for gas turbine casing |
KR1020137008283A KR101308765B1 (ko) | 2010-02-19 | 2010-09-09 | 가스 터빈 케이싱 구조 |
US13/383,637 US9234440B2 (en) | 2010-02-19 | 2010-09-09 | Structure for gas turbine casing |
CN201080034151.9A CN102472168B (zh) | 2010-02-19 | 2010-09-09 | 燃气轮机外壳结构 |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2010034218A JP2011169246A (ja) | 2010-02-19 | 2010-02-19 | ガスタービンケーシング構造 |
JP2010-034218 | 2010-02-19 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2011102014A1 true WO2011102014A1 (ja) | 2011-08-25 |
Family
ID=44482629
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2010/065467 WO2011102014A1 (ja) | 2010-02-19 | 2010-09-09 | ガスタービンケーシング構造 |
Country Status (6)
Country | Link |
---|---|
US (1) | US9234440B2 (ja) |
EP (1) | EP2538054A1 (ja) |
JP (1) | JP2011169246A (ja) |
KR (2) | KR20120034675A (ja) |
CN (1) | CN102472168B (ja) |
WO (1) | WO2011102014A1 (ja) |
Families Citing this family (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2011169246A (ja) | 2010-02-19 | 2011-09-01 | Mitsubishi Heavy Ind Ltd | ガスタービンケーシング構造 |
CN102877901B (zh) * | 2012-10-23 | 2015-07-15 | 中国航空动力机械研究所 | 机匣连接结构及具有其的燃气涡轮发动机 |
EP3008294A1 (en) * | 2013-07-25 | 2016-04-20 | Siemens Aktiengesellschaft | Sealing arrangement for a turbomachine |
KR101733626B1 (ko) * | 2014-01-15 | 2017-05-24 | 두산중공업 주식회사 | 고압 터빈의 수압시험장치 및 수압시험방법 |
DE102014214703A1 (de) * | 2014-07-25 | 2016-01-28 | Siemens Aktiengesellschaft | Vorrichtung zum Ausrichten eines Leitschaufelträgers zu einem Gehäuse einer Turbine |
JP6441611B2 (ja) * | 2014-08-25 | 2018-12-19 | 三菱日立パワーシステムズ株式会社 | ガスタービンの排気部材及び排気室メンテナンス方法 |
JP6706961B2 (ja) * | 2016-04-12 | 2020-06-10 | 株式会社日立インダストリアルプロダクツ | ボルト締結構造およびこれを用いたターボ機械 |
FR3055681B1 (fr) * | 2016-09-05 | 2019-04-19 | Safran Aircraft Engines | Piece a passage(s) interne(s) pour la solidarisation par vissage a une autre piece |
KR101821503B1 (ko) | 2016-11-04 | 2018-01-23 | 두산중공업 주식회사 | 터빈의 내부케이싱 플랜지의 흐름 가이드 구조 |
US20200248589A1 (en) * | 2019-01-31 | 2020-08-06 | Elliott Company | Oval Steam Turbine Casing |
EP3719163A1 (de) * | 2019-04-02 | 2020-10-07 | Siemens Aktiengesellschaft | Befestigungsmittel für ein turbinen- oder ventilgehäuse |
Citations (2)
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JP2005061273A (ja) * | 2003-08-08 | 2005-03-10 | Ishikawajima Harima Heavy Ind Co Ltd | ガスタービンのケーシング |
JP2007120462A (ja) | 2005-10-31 | 2007-05-17 | Toshiba Corp | 蒸気タービンケーシング締結装置および蒸気タービン |
Family Cites Families (11)
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JPS59196911A (ja) * | 1983-04-22 | 1984-11-08 | Toshiba Corp | ケ−シングの結合装置 |
JPH078825Y2 (ja) | 1991-03-20 | 1995-03-06 | 川崎重工業株式会社 | ガスタービンのシール隔壁構造 |
JPH09133026A (ja) | 1995-11-13 | 1997-05-20 | Hitachi Ltd | ガスタービン及びそのケーシング |
JPH1026006A (ja) | 1996-07-09 | 1998-01-27 | Mitsubishi Heavy Ind Ltd | 一重車室蒸気タービン |
JP2002038906A (ja) | 2000-07-26 | 2002-02-06 | Toshiba Corp | 蒸気タービン |
FR2829525B1 (fr) * | 2001-09-13 | 2004-03-12 | Snecma Moteurs | Assemblage de secteurs d'un distributeur de turbine a un carter |
FR2831600B1 (fr) * | 2001-10-25 | 2004-01-02 | Snecma Moteurs | Dispositif d'arret en rotation d'un secteur porteur d'aubes fixes dans une virole d'une turbomachine |
EP1731714A1 (de) | 2005-06-08 | 2006-12-13 | Siemens Aktiengesellschaft | Spaltsperrvorrichtung und Verwendung einer solchen |
JP5030480B2 (ja) * | 2006-06-09 | 2012-09-19 | 三菱重工業株式会社 | 車室構造 |
US8047781B2 (en) * | 2007-09-25 | 2011-11-01 | General Electric Company | Bolt assembly for steam turbine engines and method of assembling the same |
JP2011169246A (ja) | 2010-02-19 | 2011-09-01 | Mitsubishi Heavy Ind Ltd | ガスタービンケーシング構造 |
-
2010
- 2010-02-19 JP JP2010034218A patent/JP2011169246A/ja not_active Withdrawn
- 2010-09-09 KR KR1020117031042A patent/KR20120034675A/ko active Search and Examination
- 2010-09-09 WO PCT/JP2010/065467 patent/WO2011102014A1/ja active Application Filing
- 2010-09-09 US US13/383,637 patent/US9234440B2/en not_active Expired - Fee Related
- 2010-09-09 KR KR1020137008283A patent/KR101308765B1/ko not_active IP Right Cessation
- 2010-09-09 CN CN201080034151.9A patent/CN102472168B/zh not_active Expired - Fee Related
- 2010-09-09 EP EP10846146A patent/EP2538054A1/en not_active Withdrawn
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2005061273A (ja) * | 2003-08-08 | 2005-03-10 | Ishikawajima Harima Heavy Ind Co Ltd | ガスタービンのケーシング |
JP2007120462A (ja) | 2005-10-31 | 2007-05-17 | Toshiba Corp | 蒸気タービンケーシング締結装置および蒸気タービン |
Also Published As
Publication number | Publication date |
---|---|
KR20120034675A (ko) | 2012-04-12 |
US20120163963A1 (en) | 2012-06-28 |
KR101308765B1 (ko) | 2013-09-17 |
JP2011169246A (ja) | 2011-09-01 |
CN102472168B (zh) | 2014-03-19 |
KR20130038961A (ko) | 2013-04-18 |
EP2538054A1 (en) | 2012-12-26 |
US9234440B2 (en) | 2016-01-12 |
CN102472168A (zh) | 2012-05-23 |
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