JP2008082323A - Two-shaft gas turbine - Google Patents

Two-shaft gas turbine Download PDF

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JP2008082323A
JP2008082323A JP2007128757A JP2007128757A JP2008082323A JP 2008082323 A JP2008082323 A JP 2008082323A JP 2007128757 A JP2007128757 A JP 2007128757A JP 2007128757 A JP2007128757 A JP 2007128757A JP 2008082323 A JP2008082323 A JP 2008082323A
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pressure turbine
intermediate duct
turbine
strut
struts
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Masato Kataoka
正人 片岡
Eisaku Ito
栄作 伊藤
Vincent Laurello
ヴィンセント・ロウレロ
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Mitsubishi Heavy Industries Ltd
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    • 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
    • F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
    • F01D25/162—Bearing supports

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  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

<P>PROBLEM TO BE SOLVED: To provide a two-shaft gas turbine capable of improving turbine performance and reducing the size by reducing the pressure loss of a gas flow passage and shortening the length of the flow passage by effective integration of a strut cover and a first-stage stator vane of a low pressure turbine. <P>SOLUTION: The bearing case connects an annular gas flow passage outlet 15 in a high pressure turbine 12 and an annular gas flow passage inlet 16 of the low pressure turbine 13 by an annular intermediate duct 17, and a bearing 19 for journaling a rotor 18 of the high pressure turbine is mounted on the bearing case 20. The bearing case 20 is supported by a plurality of struts 23 interposed in a circumference direction by passing the intermediate duct between an outer circumference surface of the bearing case and an inner circumference surface of a cabin wall for surrounding the intermediate duct. The strut cover 22 which the struts of the intermediate duct can pass through has a function of the first-stage stator vane in the low pressure turbine. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

本発明は、同一軸線上に配列された複数の軸からなるガスタービンに関する。   The present invention relates to a gas turbine including a plurality of shafts arranged on the same axis.

ガスタービンは、空気圧縮機と燃焼器とタービンとを備えて構成されている（図示略）。このガスタービンによれば、空気圧縮機で圧縮された圧縮空気が、燃焼器に供給され、別途供給されてくる燃料と混合して燃焼される。燃焼によって発生された燃焼ガスは、タービンへと供給される。このタービン内で燃焼ガスのエネルギーが引き出され、空気圧縮機の回転駆動力と、発電機（図示略）に発電させるための駆動力とに供される。そして、このタービンに回転駆動力を発生させた後の燃焼ガスは、排気ディフューザを介して排気される。   The gas turbine includes an air compressor, a combustor, and a turbine (not shown). According to this gas turbine, the compressed air compressed by the air compressor is supplied to the combustor, and is mixed with the separately supplied fuel and burned. The combustion gas generated by the combustion is supplied to the turbine. The energy of the combustion gas is extracted in the turbine and used for the rotational driving force of the air compressor and the driving force for causing the generator (not shown) to generate power. The combustion gas after the rotational driving force is generated in the turbine is exhausted through the exhaust diffuser.

ところで、ジェットエンジンをはじめ、ジェットエンジン転用型のガスタービンとして、例えば図７に示すように、高圧タービン１００における円環状のガス流路出口１０１と低圧タービン１０２における円環状のガス流路入口１０３とを円環状の中間ダクト１０４で連結すると共に、前記高圧タービン１００のロータを軸支するジャーナル軸受１０５を、同ジャーナル軸受１０５の外周面と前記中間ダクト１０４を囲繞する車室壁１０６の内周面との間に、同中間ダクト１０４をストラットカバー１０７を介して貫通して、円周方向でかつ放射状に複数本介設されるストラット１０８により支持するようにした二軸ガスタービンが良く知られている（特許文献１〜３参照）。   By the way, as a jet engine diversion type gas turbine including a jet engine, as shown in FIG. 7, for example, an annular gas passage outlet 101 in the high-pressure turbine 100 and an annular gas passage inlet 103 in the low-pressure turbine 102 Are connected by an annular intermediate duct 104, and a journal bearing 105 that supports the rotor of the high-pressure turbine 100 is connected to an outer peripheral surface of the journal bearing 105 and an inner peripheral surface of a casing wall 106 that surrounds the intermediate duct 104. A two-shaft gas turbine is well known in which the intermediate duct 104 passes through the strut cover 107 and is supported by a plurality of struts 108 that are provided in the circumferential direction and radially. (See Patent Documents 1 to 3).

即ち、前記高圧タービン１００は、空気圧縮機（図示略）を駆動するための高温・高圧の燃焼ガスを発生させるガス発生機（ガスジェネレータ）として、また、低圧タービン１０２は、発電機等の負荷（図示略）を駆動してエネルギーを回収するパワータービンとしてそれぞれ機能するのである。尚、図７中１０９は低圧タービン１０２の一段静翼で、１１０は一段動翼である。   That is, the high-pressure turbine 100 is a gas generator (gas generator) that generates high-temperature and high-pressure combustion gas for driving an air compressor (not shown), and the low-pressure turbine 102 is a load such as a generator. It functions as a power turbine that recovers energy by driving (not shown). In FIG. 7, reference numeral 109 denotes a single-stage stationary blade of the low-pressure turbine 102, and 110 denotes a single-stage moving blade.

特開２００４−１９０６６４号公報JP 2004-190664 A 米国特許第４９８９４０６号明細書US Pat. No. 4,889,406 米国特許第４１９７７０２号明細書U.S. Pat. No. 4,197,702

しかしながら、上述したような従来の二軸ガスタービンにあっては、高圧タービン１００と低圧タービン１０２の一連のガス流路に、ストラット１０８が高温ガスに加熱されるのを防ぐ複数個のストラットカバー１０７が介在されるため、これらが低圧タービン１０２のガス流路入口１０３に、一段動翼１１０に対して、そのガス流れに沿って多数配される一段静翼１０９と共に、ガス流路内で空気力学上の損失を与えるという問題点があった。   However, in the conventional twin-shaft gas turbine as described above, a plurality of strut covers 107 that prevent the struts 108 from being heated to high-temperature gas in a series of gas flow paths of the high-pressure turbine 100 and the low-pressure turbine 102. Are interposed in the gas flow path inlet 103 of the low-pressure turbine 102, together with the first stage stationary blades 109 arranged along the gas flow with respect to the first stage moving blade 110, and aerodynamics in the gas flow path. There was a problem of giving the above loss.

また、ストラットカバー１０７と一段静翼１０９がタンデムに配されることから、ガス流路長が増大し、延いては低圧タービン１０２のロータ軸方向の長さが増大してガスタービンの大型化を招いていたという欠点もあった。   In addition, since the strut cover 107 and the one-stage stationary blade 109 are arranged in tandem, the gas flow path length increases, and the length of the low-pressure turbine 102 in the rotor axial direction increases, thereby increasing the size of the gas turbine. There was also a drawback of being invited.

そこで、本発明の目的は、ストラットカバーと低圧タービンの一段静翼との効果的な統合により、ガス流路の圧力損失を低減すると共に流路長を短縮して、タービン性能の向上とコンパクト化が図れる二軸ガスタービンを提供することにある。   Therefore, the object of the present invention is to improve the turbine performance and make it compact by reducing the pressure loss of the gas flow path and shortening the flow path length by effectively integrating the strut cover and the first stage stationary blade of the low pressure turbine. An object of the present invention is to provide a two-shaft gas turbine capable of achieving the above.

上記の課題を解決するための本発明に係る二軸ガスタービンは、高圧タービンにおける円環状のガス流路出口と低圧タービンにおける円環状のガス流路入口とを円環状の中間ダクトで連結すると共に、前記高圧タービンのロータを軸支する軸受が装着された軸受ケースを、同軸受ケースの外周面と前記中間ダクトを囲繞する車室壁の内周面との間に、同中間ダクトを貫通して、円周方向に複数本介設されるストラットにより支持するようにした二軸ガスタービンにおいて、前記中間ダクトの前記ストラットが貫通し得るストラットカバーに、前記低圧タービンにおける一段静翼の機能を持たせたことを特徴とする。   A twin-shaft gas turbine according to the present invention for solving the above-described problems is formed by connecting an annular gas flow path outlet in a high-pressure turbine and an annular gas flow path inlet in a low-pressure turbine with an annular intermediate duct. A bearing case on which a bearing for supporting the rotor of the high-pressure turbine is mounted is inserted between the outer peripheral surface of the bearing case and the inner peripheral surface of the casing wall surrounding the intermediate duct. In a two-shaft gas turbine that is supported by a plurality of struts provided in the circumferential direction, the strut cover through which the struts of the intermediate duct can pass has a function of a one-stage stationary blade in the low-pressure turbine. It is characterized by that.

また、前記中間ダクトは、円周方向へ複数個に分割形成されてその各々に前記ストラットカバーを設けると共に、これらストラットカバーの内の任意の数のストラットカバーに前記ストラットを貫通させることを特徴とする。   The intermediate duct is divided into a plurality of parts in the circumferential direction, each of which is provided with the strut cover, and the struts are penetrated through an arbitrary number of the strut covers. To do.

また、前記中間ダクトは２０個に分割形成され、その内の１０個のストラットカバーに一個おきに前記ストラットを貫通させることを特徴とする。   Further, the intermediate duct is divided into 20 pieces, and the struts are inserted through every other 10 strut covers.

また、前記ストラットカバーは、その前縁部における断面外形状が、ガス流れ方向に沿って肉厚が徐々に増大する翼形形状をなしていることを特徴とする。   Further, the strut cover is characterized in that an outer cross-sectional shape at a front edge portion thereof has an airfoil shape in which the thickness gradually increases along the gas flow direction.

本発明の構成によれば、中間ダクトのストラットカバーに低圧タービン１３における一段静翼（ノズル翼）の機能を付加したので、低圧タービンのガス流路入口には、従来有った一段静翼（ノズル翼）を配する必要がなく、直に一段動翼を配することができる。これにより、高圧タービンから低圧タービンに至るガス流路の圧力損失を効果的に低減すると共に低圧タービンにおける流路長を短縮して、タービン性能の向上とコンパクト化が図れる。   According to the configuration of the present invention, since the function of the first stage stationary blade (nozzle blade) in the low pressure turbine 13 is added to the strut cover of the intermediate duct, the conventional one stage stationary blade ( There is no need to arrange a nozzle blade), and a single stage moving blade can be arranged directly. As a result, the pressure loss in the gas flow path from the high pressure turbine to the low pressure turbine can be effectively reduced, and the flow path length in the low pressure turbine can be shortened to improve the turbine performance and make it compact.

以下、本発明に係る二軸ガスタービンを実施例により図面を用いて詳細に説明する。   Hereinafter, a twin-shaft gas turbine according to the present invention will be described in detail with reference to the drawings by way of examples.

図１は本発明の一実施例を示す二軸ガスタービンの要部断面図、図２Ａは中間ダクト部の断面図、図２Ｂは中間ダクト部の斜視断面図、図３Ａは中間ダクト部の分解断面図、図３Ｂは中間ダクト部の分解斜視断面図、図４Ａは中間ダクト部の作用状態を示す分解断面図、図４Ｂは中間ダクト部の作用状態を示す分解斜視断面図、図５は二軸ガスタービンの全体構成概略図、図６は図１のVI−VI線断面図である。   1 is a cross-sectional view of a main portion of a twin-shaft gas turbine showing an embodiment of the present invention, FIG. 2A is a cross-sectional view of an intermediate duct portion, FIG. 2B is a perspective cross-sectional view of the intermediate duct portion, and FIG. 3B is an exploded perspective sectional view of the intermediate duct portion, FIG. 4A is an exploded sectional view showing the operational state of the intermediate duct portion, FIG. 4B is an exploded perspective sectional view showing the operational state of the intermediate duct portion, and FIG. FIG. 6 is a cross-sectional view taken along line VI-VI in FIG. 1.

図５に示すように、二軸ガスタービンは、空気圧縮機１０と燃焼器１１とガスジェネレータとしての高圧タービン１２及びパワータービンとしての低圧タービン１３とを備えて構成される。   As shown in FIG. 5, the twin-shaft gas turbine includes an air compressor 10, a combustor 11, a high-pressure turbine 12 as a gas generator, and a low-pressure turbine 13 as a power turbine.

この二軸ガスタービンによれば、空気圧縮機１０で圧縮された圧縮空気が、燃焼器１１に供給され、別途供給されてくる燃料と混合して燃焼される。燃焼によって発生された燃焼ガスは、高圧タービン１２及び低圧タービン１３へと供給される。そして、高圧タービン１２で発生された高温・高圧の燃焼ガスで空気圧縮機１０が例えば５０００rpmで回転駆動される一方、低圧タービン１３では例えば３０００rpmで発電機１４が回転駆動されて燃焼ガスのエネルギーが回収される。   According to this two-shaft gas turbine, the compressed air compressed by the air compressor 10 is supplied to the combustor 11 and mixed with the separately supplied fuel and burned. The combustion gas generated by the combustion is supplied to the high pressure turbine 12 and the low pressure turbine 13. The air compressor 10 is driven to rotate at, for example, 5000 rpm by high-temperature and high-pressure combustion gas generated by the high-pressure turbine 12, while the generator 14 is driven to rotate at, for example, 3000 rpm in the low-pressure turbine 13. Collected.

図１及び図２Ａ，図２Ｂに示すように、前記高圧タービン１２における円環状のガス流路出口１５と低圧タービン１３における円環状のガス流路入口１６とが円環状の中間ダクト１７で連結されると共に、前記高圧タービン１２のロータ１８を軸支する軸受１９が装着された軸受ケース２０が、同軸受ケース２０の外周面と前記中間ダクト１７を囲繞する中間車室壁２１の内周面との間に、同中間ダクト１７をストラットカバー２２を介して貫通して、円周方向でかつ放射状に複数本介設されるストラット２３により支持されるようになっている。   As shown in FIGS. 1, 2 </ b> A, and 2 </ b> B, an annular gas passage outlet 15 in the high pressure turbine 12 and an annular gas passage inlet 16 in the low pressure turbine 13 are connected by an annular intermediate duct 17. In addition, a bearing case 20 to which a bearing 19 that supports the rotor 18 of the high-pressure turbine 12 is mounted includes an outer peripheral surface of the bearing case 20 and an inner peripheral surface of an intermediate casing wall 21 that surrounds the intermediate duct 17. In between, the intermediate duct 17 is penetrated through the strut cover 22, and is supported by a plurality of struts 23 provided in the circumferential direction and radially.

前記高圧タービン１２のガス流路には、二段に亙って、車室内壁２４Ａに支持された静翼２５とロータ１８に支持された動翼２６とが交互に配設されている。図中２４Ｂは高圧タービン１２の車室外壁で前記中間車室壁２１とボルト結合される。一方、前記低圧タービン１３のガス流路には、複数段に亙って、車室内壁２７Ａに支持された静翼２８とロータ（図示略）に支持された動翼２９とが交互に配設されている。図中２７Ｂは低圧タービン１３の車室外壁で前記中間車室壁２１とボルト結合される。   In the gas flow path of the high-pressure turbine 12, the stationary blades 25 supported by the vehicle interior wall 24A and the moving blades 26 supported by the rotor 18 are alternately arranged in two stages. In the figure, reference numeral 24B denotes a casing outer wall of the high-pressure turbine 12 and is bolted to the intermediate casing wall 21. On the other hand, in the gas flow path of the low-pressure turbine 13, a stationary blade 28 supported by the vehicle interior wall 27A and a moving blade 29 supported by a rotor (not shown) are alternately arranged over a plurality of stages. Has been. In the figure, reference numeral 27B denotes a casing outer wall of the low-pressure turbine 13 and is bolted to the intermediate casing wall 21.

前記ストラット２３は、その両端部がスタッドボルト３０及びナット３１と複数本の締付ボルト（図示略）で、それぞれ軸受ケース２０と中間車室壁２１に固定される。   Both ends of the strut 23 are fixed to the bearing case 20 and the intermediate casing wall 21 by stud bolts 30, nuts 31, and a plurality of fastening bolts (not shown), respectively.

そして、本実施例では、前記中間ダクト１７の前記ストラット２３が貫通し得るストラットカバー２２が、前記低圧タービン１３における一段静翼の機能を有している。従って、低圧タービン１３におけるガス流路入口１６には、通常であれば、一段静翼が配されるのであるが、本実施例では、一段動翼２９が配されている。   In this embodiment, the strut cover 22 through which the strut 23 of the intermediate duct 17 can penetrate has a function of a one-stage stationary blade in the low-pressure turbine 13. Therefore, normally, a single-stage stationary blade is disposed at the gas flow path inlet 16 in the low-pressure turbine 13, but in the present embodiment, a single-stage moving blade 29 is disposed.

具体的には、前記中間ダクト１７は、円周方向へ例えば２０個に分割形成されてその各々に前記ストラットカバー２２を一体的に形成すると共に、これらストラットカバー２２の内の例えば１０個のストラットカバー２２に前記ストラット２３を貫通させている。つまり、ストラットカバー２２の一つおきにストラット２３を貫通させているのである。   Specifically, the intermediate duct 17 is divided into, for example, 20 pieces in the circumferential direction, and the strut cover 22 is formed integrally with each of the intermediate ducts 17. For example, 10 struts of these strut covers 22 are formed. The strut 23 is passed through the cover 22. That is, every other strut cover 22 has the struts 23 penetrated.

前記分割された中間ダクト１７の各セグメントは、その内周側が取付部材３２ａ，３２ｂを介して軸受ケース２０に支持され、外周側がサポート部材３３ａ，３３ｂを介して中間車室壁２１に支持される。図示例では、ガス流れ上流側のサポート部材３３ａは連結部材３４を介して間接的に中間車室壁２１に支持されている。   Each segment of the divided intermediate duct 17 is supported by the bearing case 20 on the inner peripheral side via the mounting members 32a and 32b, and supported on the intermediate casing wall 21 by the support members 33a and 33b. . In the illustrated example, the support member 33 a on the upstream side of the gas flow is indirectly supported by the intermediate casing wall 21 via the connecting member 34.

図６に示すように、前記ストラットカバー２２は、その前縁部における断面外形状が、ガス流れ方向に沿って肉厚が徐々に増大する翼形形状をなしている。つまり、前縁部でのガス流れを壁面に沿って滑らかに沿わせることで衝撃波の発生を回避し、低圧タービン１３の一段動翼２９に対し、ノズル翼としての機能をフルに発揮し得るようになっている。   As shown in FIG. 6, the strut cover 22 has an airfoil shape in which the outer shape of the cross section at the front edge portion gradually increases in thickness along the gas flow direction. In other words, the generation of shock waves can be avoided by causing the gas flow at the front edge portion to smoothly follow the wall surface, and the nozzle blades can be fully exerted on the single-stage blade 29 of the low-pressure turbine 13. It has become.

尚、図３Ａ，図３Ｂは、図２Ａ，図２Ｂの状態から中間車室壁２１を分離した状態を示し、また、図４Ａ，図４Ｂは、図３Ａ，図３Ｂの状態からストラット２３を引き抜いた状態を示し、二軸ガスタービンの組付時やストラット２３及び／又は中間ダクト１７の各セグメントの交換時等の作業手順を知るためのものである。   3A and 3B show a state where the intermediate casing wall 21 is separated from the state shown in FIGS. 2A and 2B. FIGS. 4A and 4B show the struts 23 pulled out from the state shown in FIGS. 3A and 3B. This is for knowing the work procedure such as when the twin-shaft gas turbine is assembled or when the segments of the strut 23 and / or the intermediate duct 17 are replaced.

このようにして、本実施例では、中間ダクト１７のストラットカバー２２に低圧タービン１３における一段静翼（ノズル翼）の機能を付加したので、低圧タービン１３のガス流路入口１６には、従来有った一段静翼（ノズル翼）を配する必要がなく、直に一段動翼２９を配することができる。   In this way, in the present embodiment, the function of the one-stage stationary blade (nozzle blade) in the low pressure turbine 13 is added to the strut cover 22 of the intermediate duct 17, so that the gas flow path inlet 16 of the low pressure turbine 13 has a conventional one. It is not necessary to arrange a single-stage stationary blade (nozzle blade), and the single-stage moving blade 29 can be disposed directly.

これにより、高圧タービン１２から低圧タービン１３に至るガス流路の圧力損失を効果的に低減すると共に低圧タービン１３における流路長を短縮して、タービン性能の向上とコンパクト化が図れる。   Thereby, the pressure loss of the gas flow path from the high-pressure turbine 12 to the low-pressure turbine 13 can be effectively reduced, and the flow path length in the low-pressure turbine 13 can be shortened to improve the turbine performance and make it compact.

また、本実施例では、中間ダクト１７を円周方向へ複数個に分割形成し、その各々にストラットカバー２２を一体的に形成すると共に、これらストラットカバー２２の内の任意の数のストラットカバー２２にストラット２３を貫通させているので、ストラット２３の設置数を適宜変更することができると共に、ストラット２３や分割形成された中間ダクト１７の各セグメントの交換作業等も容易に行える。   Further, in this embodiment, the intermediate duct 17 is divided into a plurality of parts in the circumferential direction, and the strut cover 22 is integrally formed on each of them, and any number of the strut covers 22 among these strut covers 22 is formed. Since the struts 23 are penetrated, the number of the struts 23 can be changed as appropriate, and the replacement work of the segments of the struts 23 and the divided intermediate duct 17 can be easily performed.

尚、本発明は上記実施例に限定されず、本発明の要旨を逸脱しない範囲で、中間ダクト１７の分割数やストラット２３の本数変更やストラットカバー２２の断面外形状変更等各種変更が可能であることはいうまでもない。   The present invention is not limited to the above-described embodiments, and various modifications such as changing the number of divisions of the intermediate duct 17, the number of struts 23, and changing the cross-sectional shape of the strut cover 22 are possible without departing from the spirit of the present invention. Needless to say.

本発明の一実施例を示す二軸ガスタービンの要部断面図である。It is principal part sectional drawing of the biaxial gas turbine which shows one Example of this invention. 中間ダクト部の断面図である。It is sectional drawing of an intermediate | middle duct part. 中間ダクト部の斜視断面図である。It is a perspective sectional view of an intermediate duct part. 中間ダクト部の分解断面図である。It is an exploded sectional view of an intermediate duct part. 中間ダクト部の分解斜視断面図である。It is a disassembled perspective sectional view of an intermediate duct part. 中間ダクト部の作用状態を示す分解断面図である。It is a disassembled sectional view which shows the action state of an intermediate | middle duct part. 中間ダクト部の作用状態を示す分解斜視断面図である。It is a disassembled perspective sectional view which shows the action state of an intermediate | middle duct part. 二軸ガスタービンの全体構成概略図である。1 is an overall configuration schematic diagram of a two-shaft gas turbine. 図１のVI−VI線断面図である。It is the VI-VI sectional view taken on the line of FIG. 従来の二軸ガスタービンの要部断面図である。It is principal part sectional drawing of the conventional biaxial gas turbine.

符号の説明Explanation of symbols

１０ 空気圧縮機、１１ 燃焼器、１２ 高圧タービン、１３ 低圧タービン、１４ 発電機、１５ ガス流路出口、１６ ガス流路入口、１７ 中間ダクト、１８ ロータ、１９ 軸受、２０ 軸受ケース、２１ 中間車室壁、２２ ストラットカバー、２３ ストラット、２４Ａ 高圧タービンの車室内壁、２４Ｂ 高圧タービンの車室外壁、２５ 静翼、２６ 動翼、２７Ａ 低圧タービンの車室内壁、２７Ｂ 低圧タービンの車室外壁、２８ 静翼、２９ 動翼、３０ スタッドボルト、３１ ナット、３２ａ，３２ｂ 取付部材、３３ａ，３３ｂ サポート部材、３４ 連結部材。   DESCRIPTION OF SYMBOLS 10 Air compressor, 11 Combustor, 12 High pressure turbine, 13 Low pressure turbine, 14 Generator, 15 Gas flow path outlet, 16 Gas flow path inlet, 17 Intermediate duct, 18 Rotor, 19 Bearing, 20 Bearing case, 21 Intermediate wheel Chamber Wall, 22 Strut Cover, 23 Strut, 24A High Pressure Turbine Interior Wall, 24B High Pressure Turbine Interior Wall, 25 Stator Blade, 26 Moving Blade, 27A Low Pressure Turbine Interior Wall, 27B Low Pressure Turbine Interior Wall, 28 Stator blade, 29 Rotor blade, 30 Stud bolt, 31 Nut, 32a, 32b Mounting member, 33a, 33b Support member, 34 Connecting member.

Claims (4)

高圧タービンにおける円環状のガス流路出口と低圧タービンにおける円環状のガス流路入口とを円環状の中間ダクトで連結すると共に、
前記高圧タービンのロータを軸支する軸受が装着された軸受ケースを、同軸受ケースの外周面と前記中間ダクトを囲繞する車室壁の内周面との間に、同中間ダクトを貫通して、円周方向に複数本介設されるストラットにより支持するようにした二軸ガスタービンにおいて、
前記中間ダクトの前記ストラットが貫通し得るストラットカバーに、前記低圧タービンにおける一段静翼の機能を持たせたことを特徴とする二軸ガスタービン。 An annular gas passage outlet in the high pressure turbine and an annular gas passage inlet in the low pressure turbine are connected by an annular intermediate duct,
A bearing case mounted with a bearing that supports the rotor of the high-pressure turbine is passed through the intermediate duct between the outer peripheral surface of the bearing case and the inner peripheral surface of the casing wall surrounding the intermediate duct. In a two-shaft gas turbine that is supported by a plurality of struts interposed in the circumferential direction,
A two-shaft gas turbine characterized in that a strut cover through which the strut of the intermediate duct can pass has a function of a single stage stationary blade in the low-pressure turbine. 前記中間ダクトは、円周方向へ複数個に分割形成されてその各々に前記ストラットカバーを設けると共に、これらストラットカバーの内の任意の数のストラットカバーに前記ストラットを貫通させることを特徴とする請求項１に記載の二軸ガスタービン。   The intermediate duct is divided into a plurality of parts in a circumferential direction, each of which is provided with the strut cover, and the struts penetrate through an arbitrary number of strut covers. Item 2. The twin-shaft gas turbine according to item 1. 前記中間ダクトは２０個に分割形成され、その内の１０個のストラットカバーに一個おきに前記ストラットを貫通させることを特徴とする請求項２に記載の二軸ガスタービン。   3. The twin-shaft gas turbine according to claim 2, wherein the intermediate duct is divided into 20 parts, and the struts are passed through every other 10 strut covers. 5. 前記ストラットカバーは、その前縁部における断面外形状が、ガス流れ方向に沿って肉厚が徐々に増大する翼形形状をなしていることを特徴とする請求項１に記載の二軸ガスタービン。   2. The twin-shaft gas turbine according to claim 1, wherein the strut cover has an airfoil shape in which an outer cross-sectional shape at a front edge portion thereof gradually increases in thickness along a gas flow direction. .
JP2007128757A 2006-09-28 2007-05-15 Two-shaft gas turbine Pending JP2008082323A (en)

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