JP2008223540A - Shrinkage fitting fastening structure for gas turbine - Google Patents

Shrinkage fitting fastening structure for gas turbine Download PDF

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JP2008223540A
JP2008223540A JP2007060467A JP2007060467A JP2008223540A JP 2008223540 A JP2008223540 A JP 2008223540A JP 2007060467 A JP2007060467 A JP 2007060467A JP 2007060467 A JP2007060467 A JP 2007060467A JP 2008223540 A JP2008223540 A JP 2008223540A
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shrink
fitting fastening
shaft
fitting
gas turbine
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JP4935435B2 (en
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Koji Haruguchi
幸治 春口
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Toyota Motor Corp
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Abstract

<P>PROBLEM TO BE SOLVED: To provide a shrinkage fitting fastening structure for a gas turbine capable of certainly preventing occurrence of relaxing of the shrinkage fitting fastening structure between a cylindrical fitting fastening part formed on a cylindrical support member at a shaft side of the gas turbine and a cylindrical shrinkage fitting fastening part formed on at least a turbine disk of the gas turbine. <P>SOLUTION: In the shrinkage fitting fastening structure, when a rear shaft 11 and the turbine disk 7 at a latter stage are rotated with the shaft 1 at a high speed, the rear shaft 11 having smaller rigidity in a centrifugal direction than the cylindrical shrinkage fitting fastening part 7 of the turbine disk 7 at the latter stage is relatively largely deflected in the centrifugal direction relative to the shrinkage fitting fastening part 7B arranged at an outer peripheral side of the shrinkage fitting fastening structure. Therefore, an outer peripheral fitting surface 11B of a fitting fastening part 11A at an inner peripheral side of the shrinkage fitting fastening structure is pressed to an inner peripheral fitting surface 7B1 of the shrinkage fitting fastening part 7B at an outer peripheral side, and occurrence of relaxing of the shrinkage fitting fastening structure is certainly prevented. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

本発明は、ガスタービンの焼ばめ締結構造に関し、詳しくは、ガスタービンのシャフト側と少なくともタービンディスク側との間の焼ばめ締結構造に関するものである。   The present invention relates to a shrink-fit fastening structure for a gas turbine, and more particularly to a shrink-fit fastening structure between a shaft side of a gas turbine and at least a turbine disk side.

ガスタービンは、コンプレッサで加圧した気体を燃焼器で燃焼させ、発生した高温高圧の燃焼ガスによりタービンを駆動し、このタービンによりコンプレッサを駆動するように構成されている。   The gas turbine is configured such that gas compressed by a compressor is combusted by a combustor, a turbine is driven by the generated high-temperature and high-pressure combustion gas, and the compressor is driven by this turbine.

このようなガスタービンとして、タービンのシャフトとコンプレッサのシャフトとが同軸の一体構造または連結構造とされたものがある。そして、この種のガスタービンのシャフトに、例えば、複数のインペラを有する少なくとも２段のコンプレッサディスクと、複数のブレードを有する少なくとも２段のタービンディスクとが装着されたものがある。   As such a gas turbine, there is one in which a shaft of a turbine and a shaft of a compressor have a coaxial integral structure or a connection structure. For example, there is a gas turbine shaft of this type in which at least two stages of compressor disks having a plurality of impellers and at least two stages of turbine disks having a plurality of blades are mounted.

ここで、各コンプレッサディスクおよび各タービンディスクは、相互に所定間隔を開けた状態で一体に回転するように、筒状アームや筒状スペーサなどを介して相互に連結されている（例えば特許文献１、２参照）。そして、これらの一体化されたコンプレッサディスクおよびタービンディスクは、前端側のコンプレッサディスクと後端側のタービンディスクとがそれぞれ支持構造を介してシャフトに同心状に支持されることで、シャフトと一体に回転するようになっている。   Here, the compressor disks and the turbine disks are connected to each other via a cylindrical arm, a cylindrical spacer, or the like so as to rotate integrally with a predetermined interval therebetween (for example, Patent Document 1). 2). The integrated compressor disk and turbine disk are integrated with the shaft by supporting the compressor disk on the front end side and the turbine disk on the rear end side concentrically with the shaft via the support structure. It is designed to rotate.

ここで、支持構造としては、シャフトの前後にそれぞれ設けられたテーパ筒状（ロート状ないしラッパ状）または段付き筒状の支持部材の大径部に形成された筒状の嵌合締結部を内周側とし、コンプレッサディスクおよびタービンディスクの側面に形成された筒状アームなどの筒状の焼ばめ締結部を外周側として、筒状の嵌合締結部に筒状の焼ばめ締結部を焼ばめする構造が一般的である。
特開平０７−３２４６３２号公報 特開２００６−１３８３１９号公報 Here, as a support structure, a cylindrical fitting fastening portion formed on a large-diameter portion of a tapered cylindrical (roof or trumpet) or stepped cylindrical support member provided before and after the shaft, respectively. A cylindrical shrink-fitting fastening part on the cylindrical fitting fastening part, with a cylindrical shrink-fitting fastening part such as a cylindrical arm formed on the side surface of the compressor disk and turbine disk on the inner circumferential side A structure in which the material is fitted is generally used.
JP 07-324632 A JP 2006-138319 A

ところで、前述したような支持構造の焼ばめ締結構造においては、シャフト側の筒状支持部材の嵌合締結部や、コンプレッサディスクおよびタービンディスク側の筒状アームなどの焼ばめ締結部の寸法のバラツキにより、焼ばめ力が不足する場合がある。この場合、シャフトと共に各コンプレッサディスクおよび各タービンディスクが高速回転すると、焼ばめ締結構造の外周側の焼ばめ締結部が遠心力により大きく撓んで焼ばめ締結構造が緩む恐れがある。   By the way, in the shrink fit fastening structure of the support structure as described above, the dimensions of the fit fastening portion of the cylindrical support member on the shaft side and the shrink fit fastening portion such as the cylindrical arm on the compressor disc and turbine disc side are provided. There is a case where the shrinkage-fitting power is insufficient due to the variation of. In this case, when each compressor disk and each turbine disk rotate at a high speed together with the shaft, the shrink fit fastening portion on the outer peripheral side of the shrink fit fastening structure may be greatly bent due to centrifugal force, and the shrink fit fastening structure may be loosened.

殊に、高温の燃焼ガスが流通するタービンディスク側の焼ばめ締結構造においては、高温となった外周側の焼ばめ締結部が遠心方向に撓み易くなるため、焼ばめ締結構造に緩みが発生し易くなる。そして、焼ばめ締結構造に緩みが発生すると、シャフトの回転バランスが崩れてシャフトが大きく振動する恐れがある。   In particular, in a shrink-fitting fastening structure on the turbine disk side through which high-temperature combustion gas flows, the shrink-fitting fastening part on the outer peripheral side, which has become hot, is easily bent in the centrifugal direction, so that the shrink-fitting fastening structure is loosened. Is likely to occur. If looseness occurs in the shrink-fitting fastening structure, the rotational balance of the shaft may be lost and the shaft may vibrate greatly.

そこで、本発明は、ガスタービンのシャフト側の筒状支持部材に形成された筒状の嵌合締結部と、ガスタービンの少なくともタービンディスクに形成された筒状の焼ばめ締結部との間の焼ばめ締結構造の緩みの発生を確実に防止することができるガスタービンの焼ばめ締結構造を提供することを課題とする。   Therefore, the present invention provides a gap between a cylindrical fitting fastening portion formed on a cylindrical support member on the shaft side of a gas turbine and a cylindrical shrink fitting fastening portion formed on at least a turbine disk of the gas turbine. It is an object of the present invention to provide a shrink fit fastening structure for a gas turbine capable of reliably preventing the occurrence of loosening of the shrink fit fastening structure.

本発明に係るガスタービンの焼ばめ締結構造は、ガスタービンのシャフト側の筒状支持部材に形成された筒状の嵌合締結部を内周側とし、ガスタービンのコンプレッサディスクおよびタービンディスクの少なくともタービンディスクに形成された筒状の焼ばめ締結部を外周側として、嵌合締結部に焼ばめ締結部を焼ばめする焼ばめ締結構造であって、焼ばめ締結部の遠心方向への剛性が筒状支持部材の遠心方向への剛性よりも相対的に大きく設定されていることを特徴とする。   A gas turbine fastening structure according to the present invention has a cylindrical fitting fastening portion formed on a cylindrical support member on a shaft side of a gas turbine as an inner peripheral side, and includes a compressor disk and a turbine disk of a gas turbine. A shrink fit fastening structure in which a shrink fit fastening portion is fitted into a fitting fastening portion with at least a cylindrical fit fastening portion formed on a turbine disk as an outer peripheral side. The rigidity in the centrifugal direction is set to be relatively larger than the rigidity of the cylindrical support member in the centrifugal direction.

本発明に係るガスタービンの焼ばめ締結構造では、シャフトと共にコンプレッサディスクおよびタービンディスクが高速回転する際、遠心方向への剛性の小さい内周側の筒状支持部材が遠心方向への剛性の大きい外周側の焼ばめ締結部に対し、相対的に大きく遠心方向に撓む。このため、内周側の筒状支持部材の嵌合締結部が外周側の焼ばめ締結部に押圧されるのであり、焼ばめ締結構造の緩みの発生が確実に防止される。   In the shrink-fitting fastening structure of the gas turbine according to the present invention, when the compressor disk and the turbine disk rotate together with the shaft at a high speed, the cylindrical support member on the inner peripheral side having a small rigidity in the centrifugal direction has a large rigidity in the centrifugal direction. It bends in the centrifugal direction relatively greatly with respect to the shrink-fitting fastening portion on the outer peripheral side. For this reason, the fitting fastening part of the cylindrical support member on the inner circumferential side is pressed against the shrink fitting fastening part on the outer circumferential side, and the occurrence of loosening of the shrink fitting fastening structure is reliably prevented.

本発明のガスタービンの焼ばめ締結構造において、焼ばめ締結部は、筒状支持部材よりも遠心方向への剛性が大きくなるように、筒状支持部材の材料よりもヤング率の大きい材料で構成することができる。   In the shrink fit fastening structure of the gas turbine of the present invention, the shrink fit fastening portion has a material having a Young's modulus larger than that of the cylindrical support member so that the rigidity in the centrifugal direction is greater than that of the tubular support member. Can be configured.

ここで、筒状支持部材は、その遠心方向への剛性が低下するように、シャフト側の基端部に向かって漸次薄肉化されているのが好ましい。一方、焼ばめ締結部は、その遠心方向への剛性が増大するように、突出長が筒状支持部材の嵌合締結部の突出長よりも短く設定されているのが好ましい。   Here, it is preferable that the cylindrical support member is gradually thinned toward the base end portion on the shaft side so that the rigidity in the centrifugal direction is lowered. On the other hand, it is preferable that the projection length of the shrink-fitting fastening portion is set shorter than the projection length of the fitting fastening portion of the cylindrical support member so that the rigidity in the centrifugal direction increases.

本発明に係るガスタービンの焼ばめ締結構造によれば、シャフトと共にコンプレッサディスクおよびタービンディスクが高速回転する際、焼ばめ締結構造の内周側の筒状支持部材を外周側の焼ばめ締結部に対して相対的に大きく遠心方向に撓ませてその嵌合締結部を外周側の焼ばめ締結部に押圧させることができ、焼ばめ締結構造の緩みの発生を確実に防止することができる。その結果、シャフトの回転バランスが崩れてシャフトが大きく振動する事態を未然に防止することができる。   According to the shrink-fitting fastening structure for a gas turbine according to the present invention, when the compressor disk and the turbine disk rotate at a high speed together with the shaft, the tubular support member on the inner circumferential side of the shrink-fitting fastening structure is fitted on the outer circumferential side. The fitting portion can be deflected relatively large relative to the fastening portion in the centrifugal direction, and the fitting fastening portion can be pressed against the shrink fitting fastening portion on the outer peripheral side, thereby reliably preventing the occurrence of loosening of the shrink fitting fastening structure. be able to. As a result, it is possible to prevent a situation in which the rotation balance of the shaft is lost and the shaft vibrates greatly.

以下、図面を参照して本発明に係るガスタービンの焼ばめ締結構造の最良の実施形態を説明する。この説明において、同一または同様の構成要素については、同一の符号を付して重複した説明を省略することがある。ここで、参照する図面において、図１は一実施形態に係るガスタービンの焼ばめ締結構造が適用されたガスタービンの概略構造を模式的に示す縦断面図である。   Hereinafter, the best embodiment of the shrink-fitting fastening structure for a gas turbine according to the present invention will be described with reference to the drawings. In this description, the same or similar components are denoted by the same reference numerals, and redundant description may be omitted. Here, in the drawings to be referred to, FIG. 1 is a longitudinal sectional view schematically showing a schematic structure of a gas turbine to which a shrink-fitting fastening structure of a gas turbine according to an embodiment is applied.

一実施形態に係るガスタービンの焼ばめ締結構造は、図１に示すようなガスタービンに適用されている。このガスタービンは、出力軸となる１本のシャフト１がコンプレッサ２のシャフトとタービン３のシャフトとを兼用した１軸の軸流式ガスタービンである。   The shrink fitting fastening structure of the gas turbine which concerns on one Embodiment is applied to the gas turbine as shown in FIG. This gas turbine is a single-shaft axial-flow gas turbine in which a single shaft 1 serving as an output shaft serves as a shaft of a compressor 2 and a shaft of a turbine 3.

シャフト１の前部には、コンプレッサ２を構成する前段のコンプレッサディスク４および後段のコンプレッサディスク５が遊嵌されている。また、シャフト１の後部には、タービン３を構成する前段のタービンディスク６および後段のタービンディスク７が遊嵌されている。   A front-stage compressor disk 4 and a rear-stage compressor disk 5 constituting the compressor 2 are loosely fitted to the front portion of the shaft 1. In addition, a front-stage turbine disk 6 and a rear-stage turbine disk 7 constituting the turbine 3 are loosely fitted to the rear portion of the shaft 1.

前段のコンプレッサディスク４には、その前面からシャフト１の軸方向に突出する筒状アームからなる筒状の焼ばめ締結部４Ａと、その後面からシャフト１の軸方向に突出する筒状アーム４Ｂとが形成されている。そして、コンプレッサディスク４の外周には、ケーシング８の内壁面に沿って回転する複数のインペラ４Ｃが配列されている。   The front compressor disk 4 includes a cylindrical shrink-fitting fastening portion 4A composed of a cylindrical arm protruding from the front surface in the axial direction of the shaft 1 and a cylindrical arm 4B protruding from the rear surface in the axial direction of the shaft 1. And are formed. A plurality of impellers 4 </ b> C that rotate along the inner wall surface of the casing 8 are arranged on the outer periphery of the compressor disk 4.

後段のコンプレッサディスク５には、その前後の面からシャフト１の軸方向に突出する筒状アーム５Ａ，５Ｂが形成されている。そして、このコンプレッサディスク５の外周には、ケーシング８の内壁面に沿って回転する複数のインペラ５Ｃが配列されている。   The rear compressor disk 5 is formed with cylindrical arms 5A and 5B that protrude in the axial direction of the shaft 1 from the front and rear surfaces thereof. A plurality of impellers 5 </ b> C that rotate along the inner wall surface of the casing 8 are arranged on the outer periphery of the compressor disk 5.

前段のタービンディスク６には、その前後の面からシャフト１の軸方向に突出する筒状アーム６Ａ，６Ｂが形成されている。そして、このタービンディスク６の外周には、ケーシング８の内壁面に沿って回転する複数のブレード６Ｃが配列されている。   The front-stage turbine disk 6 is formed with cylindrical arms 6A and 6B that protrude in the axial direction of the shaft 1 from the front and rear surfaces thereof. A plurality of blades 6 </ b> C that rotate along the inner wall surface of the casing 8 are arranged on the outer periphery of the turbine disk 6.

後段のタービンディスク７には、その前面からシャフト１の軸方向に突出する筒状アーム７Ａと、その後面からシャフト１の軸方向に突出する筒状アームからなる筒状の焼ばめ締結部７Ｂとが形成されている。そして、このタービンディスク７の外周には、ケーシング８の内壁面に沿って回転する複数のブレード７Ｃが配列されている。   The turbine turbine 7 at the rear stage has a cylindrical shrink-fitting fastening portion 7B composed of a cylindrical arm 7A protruding from the front surface in the axial direction of the shaft 1 and a cylindrical arm protruding from the rear surface in the axial direction of the shaft 1. And are formed. A plurality of blades 7 </ b> C that rotate along the inner wall surface of the casing 8 are arranged on the outer periphery of the turbine disk 7.

そして、ケーシング８には、燃焼器９の燃料噴射ノズル９Ａが貫通して装着されている。この燃料噴射ノズル９Ａは、前段のコンプレッサディスク４のインペラ４Ｃおよび後段のコンプレッサディスク５のインペラ５Ｃの回転により吸入されて加圧された圧縮空気に燃料を噴射し、これを着火させて燃焼させる。   The casing 8 is fitted with a fuel injection nozzle 9A of the combustor 9 penetrating therethrough. The fuel injection nozzle 9A injects fuel into the compressed air sucked and pressurized by the rotation of the impeller 4C of the front-stage compressor disk 4 and the impeller 5C of the rear-stage compressor disk 5, and ignites and burns it.

ここで、前段のコンプレッサディスク４、後段のコンプレッサディスク５、前段のタービンディスク６および後段のタービンディスク７は、相対回転することなく一体に回転するように、相互に同心状に連結されている。   Here, the front-stage compressor disk 4, the rear-stage compressor disk 5, the front-stage turbine disk 6 and the rear-stage turbine disk 7 are concentrically connected to each other so as to rotate integrally without relative rotation.

すなわち、前段のコンプレッサディスク４の筒状アーム４Ｂの先端面と後段のコンプレッサディスク５の筒状アーム５Ａの先端面との間、後段のコンプレッサディスク５の筒状アーム５Ｂの先端面と前段のタービンディスク６の筒状アーム６Ａの先端面との間、前段のタービンディスク６の筒状アーム６Ｂの先端面と後段のタービンディスク７の筒状アーム７Ａの先端面との間がそれぞれ凹凸係合により同心状に連結されている。   That is, between the front end surface of the cylindrical arm 4B of the front compressor disk 4 and the front end surface of the cylindrical arm 5A of the rear compressor disk 5, the front end surface of the cylindrical arm 5B of the rear compressor disk 5 and the front turbine. Due to the concavo-convex engagement between the front end surface of the cylindrical arm 6A of the disc 6 and the front end surface of the cylindrical arm 6B of the front turbine disc 6 and the front end surface of the cylindrical arm 7A of the rear turbine disc 7 respectively. Concentrically connected.

一方、シャフト１の前部には、前段のコンプレッサディスク４の前面から前方に突出する焼ばめ締結部４Ａを支持する筒状支持部材としてのフロントシャフト１０が固定され、シャフト１の後部には、後段のタービンディスク７の後面から後方に突出する焼ばめ締結部７Ｂを支持する筒状支持部材としてのリヤシャフト１１が固定されている。   On the other hand, a front shaft 10 as a cylindrical support member that supports a shrink-fitting fastening portion 4A that protrudes forward from the front surface of the front compressor disk 4 is fixed to the front portion of the shaft 1. A rear shaft 11 is fixed as a cylindrical support member that supports a shrink-fitting fastening portion 7B that protrudes rearward from the rear surface of the turbine disk 7 at the rear stage.

フロントシャフト１０は、大径部に焼ばめ締結部４Ａが焼ばめされるテーパ筒状（ラッパ状ないしロート状）に形成されており、その大径部よりシャフト１の軸方向前方に位置する小径部がシャフト１の前部に例えば螺合して固定されている。同様に、リヤシャフト１１は、大径部に焼ばめ締結部７Ｂが焼ばめされるテーパ筒状（ラッパ状ないしロート状）に形成されており、その大径部よりシャフト１の軸方向後方に位置する小径部がシャフト１の後部に例えば螺合して固定されている。   The front shaft 10 is formed in a tapered cylindrical shape (a trumpet shape or a funnel shape) in which the shrink-fitting fastening portion 4A is shrink-fitted to the large-diameter portion, and is positioned forward of the large-diameter portion in the axial direction of the shaft 1 The small-diameter portion to be fixed is, for example, screwed into the front portion of the shaft 1. Similarly, the rear shaft 11 is formed in a tapered cylindrical shape (trumpet shape or funnel shape) in which the shrink fit fastening portion 7B is shrink fitted to the large diameter portion, and the axial direction of the shaft 1 from the large diameter portion. A small-diameter portion located rearward is fixed to the rear portion of the shaft 1 by, for example, screwing.

そして、フロントシャフト１０の小径部およびリヤシャフト１１の小径部がそれぞれベアリング１２、１３を介してケーシング８側の図示しない不動部材に回転自在に支持されることで、シャフト１と共に前段のコンプレッサディスク４、後段のコンプレッサディスク５、前段のタービンディスク６および後段のタービンディスク７が同心状に一体に回転できるようになっている。   The small-diameter portion of the front shaft 10 and the small-diameter portion of the rear shaft 11 are rotatably supported by a non-illustrated non-illustrated member on the casing 8 side via bearings 12 and 13, respectively. The rear-stage compressor disk 5, the front-stage turbine disk 6, and the rear-stage turbine disk 7 can be rotated concentrically and integrally.

ここで、フロントシャフト１０およびリヤシャフト１１は、略同様の形状を有するため、両者を代表してリヤシャフト１１の形状を説明する。図２および図３に示すようにテーパ筒状に形成されたリヤシャフト１１の大径部には、後段のタービンディスク７の焼ばめ締結部７Ｂの内周側にインロー嵌合する嵌合締結部１１Ａが形成されており、この嵌合締結部１１Ａには外周嵌合面１１Ｂが形成されている。   Here, since the front shaft 10 and the rear shaft 11 have substantially the same shape, the shape of the rear shaft 11 will be described as a representative of both. As shown in FIGS. 2 and 3, the large-diameter portion of the rear shaft 11 formed in a tapered cylindrical shape is fitted and fastened with an inlay on the inner peripheral side of the shrink-fitting fastening portion 7 </ b> B of the subsequent turbine disk 7. A portion 11A is formed, and an outer peripheral fitting surface 11B is formed in the fitting fastening portion 11A.

一方、後段のタービンディスク７の焼ばめ締結部７Ｂには、リヤシャフト１１の大径部の嵌合締結部１１Ａに形成された外周嵌合面１１Ｂに焼ばめされる内周嵌合面７Ｂ１が形成されている。   On the other hand, the inner periphery fitting surface which is shrink-fitted to the outer periphery fitting surface 11B formed in the fitting fastening portion 11A of the large-diameter portion of the rear shaft 11 is attached to the shrink-fitting fastening portion 7B of the turbine disk 7 at the rear stage. 7B1 is formed.

ここで、リヤシャフト１１の遠心方向への撓み量は、遠心力による等分布荷重を受ける片持ち梁の撓み量として、次の式（１）により求めることができ、また、リヤシャフト１１の遠心方向への剛性は、次の式（２）により求めることができる。なお、式（１）において、ｙｒはリヤシャフト１１の遠心方向への撓み量、Ｆｒはリヤシャフト１１が受ける遠心力、Ｌｒはリヤシャフト１１の片持ち梁としての長さ、Ｅｒはリヤシャフト１１のヤング率、Ｉｒはリヤシャフト１１の断面２次モーメントである。また、式（２）において、Ｋｒはリヤシャフト１１の遠心方向への剛性である。
（１）……ｙｒ＝（ＦｒＬｒ４）／（８ＥｒＩｒ）
（２）……Ｋｒ＝Ｆｒ／ｙｒ＝８Ｅｒ／Ｌｒ４ Here, the amount of bending of the rear shaft 11 in the centrifugal direction can be obtained by the following equation (1) as the amount of bending of the cantilever beam that receives the equally distributed load due to the centrifugal force. The rigidity in the direction can be obtained by the following equation (2). In equation (1), yr is the amount of bending of the rear shaft 11 in the centrifugal direction, Fr is the centrifugal force received by the rear shaft 11, Lr is the length of the rear shaft 11 as a cantilever, and Er is the rear shaft 11. The Young's modulus, Ir, is the cross-sectional second moment of the rear shaft 11. In the formula (2), Kr is the rigidity of the rear shaft 11 in the centrifugal direction.
(1) ... yr = (FrLr 4 ) / (8ErIr)
(2) ... Kr = Fr / yr = 8Er / Lr 4

同様に、後段のタービンディスク７の焼ばめ締結部７Ｂの遠心方向への撓み量は、遠心力による等分布荷重を受ける片持ち梁の撓み量として、次の式（３）により求めることができ、また、焼ばめ締結部７Ｂの遠心方向への剛性は、次の式（４）により求めることができる。なお、式（３）において、ｙｄは焼ばめ締結部７Ｂの遠心方向への撓み量、Ｆｄは焼ばめ締結部７Ｂが受ける遠心力、Ｌｄは焼ばめ締結部７Ｂの片持ち梁としての長さ、Ｅｄは焼ばめ締結部７Ｂのヤング率、Ｉｄは焼ばめ締結部７Ｂの断面２次モーメントである。また、式（４）において、Ｋｄは焼ばめ締結部７Ｂの遠心方向への剛性である。
（３）……ｙｄ＝（ＦｄＬｄ４）／（８ＥｄＩｄ）
（４）……Ｋｄ＝Ｆｄ／ｙｄ＝８Ｅｄ／Ｌｄ４ Similarly, the amount of bending in the centrifugal direction of the shrink-fitting fastening portion 7B of the turbine disk 7 in the subsequent stage can be obtained by the following equation (3) as the amount of bending of the cantilever beam that receives an evenly distributed load due to centrifugal force. In addition, the rigidity in the centrifugal direction of the shrink-fitting fastening portion 7B can be obtained by the following equation (4). In equation (3), yd is the amount of bending of the shrink fit fastening portion 7B in the centrifugal direction, Fd is the centrifugal force received by the shrink fit fastening portion 7B, and Ld is the cantilever of the shrink fit fastening portion 7B. , Ed is the Young's modulus of the shrink-fitting fastening portion 7B, and Id is the moment of inertia of the cross section of the shrink-fitting fastening portion 7B. Moreover, in Formula (4), Kd is the rigidity to the centrifugal direction of the shrink fitting fastening part 7B.
(3) ... yd = (FdLd 4 ) / (8EdId)
(4) ... Kd = Fd / yd = 8 Ed / Ld 4

ここで、リヤシャフト１１に形成された嵌合締結部１１Ａの外周嵌合面１１Ｂと、後段のタービンディスク７に形成された焼ばめ締結部７Ｂの内周嵌合面７Ｂ１との間の焼ばめ締結構造の緩みの発生を防止するには、ｙｄ＜ｙｒとなるようにＫｄ＞Ｋｒとすればよい。そして、Ｋｄ＞Ｋｒとするには、Ｅｄ＞ＥｒおよびＬｄ＜Ｌｒの一方または両方の構成を採用するればよい。   Here, the shrinkage between the outer peripheral fitting surface 11B of the fitting fastening portion 11A formed on the rear shaft 11 and the inner peripheral fitting surface 7B1 of the shrink fitting fastening portion 7B formed on the subsequent turbine disk 7 is achieved. In order to prevent the loosening of the fitting fastening structure, Kd> Kr may be set so that yd <yr. In order to satisfy Kd> Kr, one or both of Ed> Er and Ld <Lr may be employed.

そこで、一実施形態のガスタービンの焼ばめ締結構造においては、Ｌｄ＜ＬｒおよびＥｄ＞Ｅｒの両方の構成が採用されている。すなわち、焼ばめ締結部７Ｂの片持ち梁としての長さＬｄは、リヤシャフト１１の片持ち梁としての長さＬｒの例えば１／４程度に短く設定されている（図２参照）。   Therefore, in the gas turbine fastening structure of one embodiment, both configurations of Ld <Lr and Ed> Er are employed. That is, the length Ld as the cantilever of the shrink-fitting fastening portion 7B is set to be, for example, about 1/4 of the length Lr as the cantilever of the rear shaft 11 (see FIG. 2).

そして、特に、焼ばめ締結部７Ｂの材料は、リヤシャフト１１の材料よりもヤング率の大きい材料で構成されている。すなわち、焼ばめ締結部７Ｂを含む後段のタービンディスク７は、例えばヤング率Ｅｄが２００〜２２０（ＧＰａ）程度のニッケル合金で構成され、リヤシャフト１１は、例えばヤング率Ｅｒが７０（ＧＰａ）程度のアルミニウム合金で構成されている。   In particular, the material of the shrink-fitting fastening portion 7 </ b> B is made of a material having a Young's modulus greater than that of the rear shaft 11. That is, the latter stage turbine disk 7 including the shrink-fitting fastening portion 7B is made of a nickel alloy having a Young's modulus Ed of about 200 to 220 (GPa), for example, and the rear shaft 11 has a Young's modulus Er of 70 (GPa), for example. Consists of about an aluminum alloy.

なお、図１に示したフロントシャフト１０および焼ばめ締結部４Ａを含む前段のコンプレッサディスク４も前述したリヤシャフト１１および焼ばめ締結部７Ｂと同様に構成されている。   The front compressor disk 4 including the front shaft 10 and the shrink-fitting fastening portion 4A shown in FIG. 1 is also configured in the same manner as the rear shaft 11 and the shrink-fitting fastening portion 7B.

以上のように構成された本実施形態のガスタービンの焼ばめ締結構造では、図１に示したシャフト１側のフロントシャフト１０およびリヤシャフト１１と共に、前段のコンプレッサディスク４、後段のコンプレッサディスク５、前段のタービンディスク６および後段のタービンディスク７が高速回転する際、リヤシャフト１１の大径部の嵌合締結部１１Ａが後段のタービンディスク７の焼ばめ締結部７Ｂに対し相対的に大きく遠心方向へ撓む。   In the gas turbine fastening structure of the present embodiment configured as described above, the front-stage compressor disk 4 and the rear-stage compressor disk 5 together with the front shaft 10 and the rear shaft 11 on the shaft 1 side shown in FIG. When the front-stage turbine disk 6 and the rear-stage turbine disk 7 rotate at a high speed, the large-diameter fitting engagement portion 11A of the rear shaft 11 is relatively larger than the shrink-fitting fastening portion 7B of the rear-stage turbine disk 7. Deflection in the centrifugal direction.

このため、リヤシャフト１１の嵌合締結部１１Ａの外周嵌合面１１Ｂがタービンディスク７の焼ばめ締結部７Ｂの内周嵌合面７Ｂ１に押圧されるようになり、嵌合締結部１１Ａの外周嵌合面１１Ｂと焼ばめ締結部７Ｂの内周嵌合面７Ｂ１との間の焼ばめ締結構造の緩みの発生が確実に防止される。   For this reason, the outer peripheral fitting surface 11B of the fitting fastening portion 11A of the rear shaft 11 is pressed against the inner peripheral fitting surface 7B1 of the shrink-fitting fastening portion 7B of the turbine disk 7, and the fitting fastening portion 11A Generation | occurrence | production of the loosening of the shrink fitting fastening structure between the outer periphery fitting surface 11B and the inner periphery fitting surface 7B1 of the shrink fitting fastening part 7B is reliably prevented.

同様に、フロントシャフト１０の大径部の嵌合締結部(符号省略)が前段のコンプレッサディスク４の焼ばめ締結部４Ａに対し相対的に大きく遠心方向へ撓むため、フロントシャフト１０の嵌合締結部の外周嵌合面(符号省略)が前段のコンプレッサディスク４の焼ばめ締結部４Ａの内周嵌合面(符号省略)に押圧されるようになり、両者の間の焼ばめ締結構造の緩みの発生が確実に防止される。   Similarly, since the fitting fastening portion (reference numeral omitted) of the large-diameter portion of the front shaft 10 bends in the centrifugal direction relatively greatly with respect to the shrink-fitting fastening portion 4A of the compressor disk 4 in the previous stage, the fitting of the front shaft 10 The outer peripheral fitting surface (reference numeral omitted) of the joint fastening portion is pressed against the inner peripheral fitting surface (reference numeral omitted) of the shrink fitting fastening portion 4A of the compressor disk 4 in the previous stage, and the shrink fit between the two. Occurrence of loosening of the fastening structure is reliably prevented.

すなわち、本実施形態のガスタービンの焼ばめ締結構造によれば、シャフト１側のリヤシャフト１１と後段のタービンディスク７の焼ばめ締結部７Ｂとの間の焼ばめ締結構造の緩みの発生を確実に防止することができ、同様に、シャフト１側のフロントシャフト１０と前段のコンプレッサディスク４の焼ばめ締結部４Ａとの間の焼ばめ締結構造の緩みの発生を確実に防止することができる。その結果、シャフト１の回転バランスが崩れてシャフト１が大きく振動する事態を未然に防止することができる。   That is, according to the shrink-fitting fastening structure of the gas turbine of this embodiment, the loose-fitting fastening structure between the rear shaft 11 on the shaft 1 side and the shrink-fitting fastening part 7B of the turbine disk 7 at the rear stage is reduced. Similarly, the occurrence of loosening of the shrink-fitting fastening structure between the front shaft 10 on the side of the shaft 1 and the shrink-fitting fastening part 4A of the compressor disk 4 on the front stage can be reliably prevented. can do. As a result, it is possible to prevent a situation in which the rotation balance of the shaft 1 is lost and the shaft 1 vibrates greatly.

本発明に係るガスタービンの焼ばめ締結構造は、前述した一実施形態に限定されるものではない。例えば、図２に示した焼ばめ締結部７Ｂを含む後段のタービンディスク７は、ヤング率Ｅｄが２０６（ＧＰａ）の鋼鉄などで構成し、リヤシャフト１１は、ヤング率Ｅｒが１００〜１３０（ＧＰａ）程度の銅合金などで構成してもよい。図１に示したフロントシャフト１０および前段のコンプレッサディスク４も同様である。   The shrink fit fastening structure of the gas turbine according to the present invention is not limited to the above-described embodiment. For example, the subsequent turbine disk 7 including the shrink-fitting fastening portion 7B shown in FIG. 2 is made of steel having a Young's modulus Ed of 206 (GPa), and the rear shaft 11 has a Young's modulus Er of 100 to 130 ( GPa) grade copper alloy or the like. The same applies to the front shaft 10 and the front compressor disk 4 shown in FIG.

また、図２に示したリヤシャフト１１は、図４に示すように、嵌合締結部１１Ａ側の大径部からシャフト１に嵌合固定される基端部の小径部に向かって肉厚が漸次薄肉化された形状に変更してもよい。   Further, as shown in FIG. 4, the rear shaft 11 shown in FIG. 2 has a wall thickness from the large diameter portion on the fitting fastening portion 11A side toward the small diameter portion of the base end portion that is fitted and fixed to the shaft 1. You may change into the shape thinned gradually.

図４に示したリヤシャフト１１は、前述した式（１）において、断面２次モーメントＩｒが小さくなるため、その分、遠心方向への撓み量ｙｒが増大する。このため、図１に示したシャフト１と共にリヤシャフト１１および後段のタービンディスク７が高速回転する際、リヤシャフト１１の嵌合締結部１１Ａがタービンディスク７の焼ばめ締結部７Ｂに対し相対的に一層大きく遠心方向へ撓む。   In the rear shaft 11 shown in FIG. 4, since the second moment of inertia Ir is reduced in the above-described equation (1), the amount of deflection yr in the centrifugal direction is increased accordingly. Therefore, when the rear shaft 11 and the subsequent turbine disk 7 rotate at a high speed together with the shaft 1 shown in FIG. 1, the fitting fastening portion 11 </ b> A of the rear shaft 11 is relative to the shrink-fitting fastening portion 7 </ b> B of the turbine disk 7. More flexibly in the centrifugal direction.

そして、リヤシャフト１１の嵌合締結部１１Ａの外周嵌合面１１Ｂがタービンディスク７の焼ばめ締結部７Ｂの内周嵌合面７Ｂ１に強く押圧されるようになり、嵌合締結部１１Ａの外周嵌合面１１Ｂと焼ばめ締結部７Ｂの内周嵌合面７Ｂ１との間の焼ばめ締結構造の緩みの発生が一層確実に防止される。なお、図４に示したリヤシャフト１１と同様に構成されたフロントシャフト１０も、同様の作用効果を奏する。   Then, the outer peripheral fitting surface 11B of the fitting fastening portion 11A of the rear shaft 11 is strongly pressed against the inner peripheral fitting surface 7B1 of the shrink-fitting fastening portion 7B of the turbine disk 7, and the fitting fastening portion 11A Occurrence of loosening of the shrink-fitting fastening structure between the outer fitting surface 11B and the inner fitting surface 7B1 of the shrink-fitting fastening portion 7B is more reliably prevented. The front shaft 10 configured in the same manner as the rear shaft 11 shown in FIG. 4 also has the same function and effect.

一方、図２に示したタービンディスク７の焼ばめ締結部７Ｂの片持ち梁としての長さは、図５に示すように短縮してもよい。この場合、前述した式（４）のＬｄが小さくなることで焼ばめ締結部７Ｂの剛性Ｋｄが大幅に増大し、焼ばめ締結部７Ｂの遠心方向への撓み量ｙｄが大幅に減少する。このため、嵌合締結部１１Ａの外周嵌合面１１Ｂと焼ばめ締結部７Ｂの内周嵌合面７Ｂ１との間の焼ばめ締結構造の緩みの発生が一層確実に防止される。   On the other hand, the length as a cantilever of the shrink-fitting fastening portion 7B of the turbine disk 7 shown in FIG. 2 may be shortened as shown in FIG. In this case, the rigidity Kd of the shrink-fitting fastening portion 7B is greatly increased by decreasing Ld in the above-described formula (4), and the amount of bending yd in the centrifugal direction of the shrink-fitting fastening portion 7B is greatly reduced. . For this reason, generation | occurrence | production of the loosening of the shrink fitting fastening structure between the outer periphery fitting surface 11B of the fitting fastening part 11A and the inner periphery fitting surface 7B1 of the shrink fitting fastening part 7B is prevented more reliably.

なお、図示省略するが、タービンディスク７の焼ばめ締結部７Ｂの基端部の内周側に肉盛りしてもよい。この場合、焼ばめ締結部７Ｂの剛性Ｋｄが増大して遠心方向への撓み量ｙｄが減少するため、嵌合締結部１１Ａの外周嵌合面１１Ｂと焼ばめ締結部７Ｂの内周嵌合面７Ｂ１との間の焼ばめ締結構造の緩みの発生が一層確実に防止される。   In addition, although illustration is omitted, you may build up on the inner peripheral side of the base end part of the shrink-fitting fastening part 7B of the turbine disk 7. In this case, since the rigidity Kd of the shrink-fitting fastening portion 7B is increased and the amount of bending yd in the centrifugal direction is reduced, the outer fitting surface 11B of the fitting fastening portion 11A and the inner fitting of the shrink-fitting fastening portion 7B. Generation | occurrence | production of the looseness of the shrink-fitting fastening structure between the mating surfaces 7B1 is prevented more reliably.

また、図示省略するが、リヤシャフト１１の嵌合締結部１１Ａの突出長を増大してもよい。この場合、嵌合締結部１１Ａの剛性が低下して遠心方向への撓み量が増大するため、嵌合締結部１１Ａの外周嵌合面１１Ｂと焼ばめ締結部７Ｂの内周嵌合面７Ｂ１との間の焼ばめ締結構造の緩みの発生が一層確実に防止される。   Although not shown, the protrusion length of the fitting fastening portion 11A of the rear shaft 11 may be increased. In this case, since the rigidity of the fitting fastening portion 11A decreases and the amount of bending in the centrifugal direction increases, the outer circumferential fitting surface 11B of the fitting fastening portion 11A and the inner circumferential fitting surface 7B1 of the shrink fitting fastening portion 7B. Occurrence of loosening of the shrink fit fastening structure between the two is more reliably prevented.

本発明の一実施形態に係るガスタービンの焼ばめ締結構造が適用されたガスタービンの概略構造を模式的に示す縦断面図である。BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a longitudinal sectional view schematically showing a schematic structure of a gas turbine to which a gas turbine fastening structure according to an embodiment of the present invention is applied. 図１に示した後段のタービンディスクの焼ばめ締結部をシャフトに支持するリヤシャフトの拡大断面図である。FIG. 2 is an enlarged cross-sectional view of a rear shaft that supports a shrink-fitting fastening portion of the subsequent turbine disk shown in FIG. 1 on the shaft. 図２に示したリヤシャフトの大径側から見た斜視図である。FIG. 3 is a perspective view of the rear shaft shown in FIG. 2 as viewed from the large diameter side. 図２に示したリヤシャフトの変形例を示す図２に対応した拡大断面図である。FIG. 3 is an enlarged cross-sectional view corresponding to FIG. 2 showing a modification of the rear shaft shown in FIG. 2. 図２に示した焼ばめ締結部の変形例を示す図２に対応した拡大断面図である。It is an expanded sectional view corresponding to FIG. 2 which shows the modification of the shrink-fitting fastening part shown in FIG.

符号の説明Explanation of symbols

１…シャフト、２…コンプレッサ、３…タービン、４…前段のコンプレッサディスク、４Ａ…焼ばめ締結部、４Ｂ…筒状アーム、４Ｃ…インペラ、５…後段のコンプレッサディスク、５Ａ，５Ｂ…筒状アーム、５Ｃ…インペラ、６…前段のタービンディスク、６Ａ，６Ｂ…筒状アーム、６Ｃ…ブレード、７…後段のタービンディスク、７Ａ…筒状アーム、７Ｂ…焼ばめ締結部、７Ｂ１…内周嵌合面、７Ｃ…ブレード、８…ケーシング、９…燃焼器、１０…フロントシャフト、１１…リヤシャフト、１１Ａ…嵌合締結部、１１Ｂ…外周嵌合面、１２，１３…ベアリング。   DESCRIPTION OF SYMBOLS 1 ... Shaft, 2 ... Compressor, 3 ... Turbine, 4 ... Front stage compressor disk, 4A ... Shrink fitting fastening part, 4B ... Cylindrical arm, 4C ... Impeller, 5 ... Rear stage compressor disk, 5A, 5B ... Cylindrical shape Arm, 5C ... Impeller, 6 ... Front stage turbine disk, 6A, 6B ... Cylindrical arm, 6C ... Blade, 7 ... Rear stage turbine disk, 7A ... Cylindrical arm, 7B ... Shrink fit fastening part, 7B1 ... Inner circumference Fitting surface, 7C ... blade, 8 ... casing, 9 ... combustor, 10 ... front shaft, 11 ... rear shaft, 11A ... fitting fastening part, 11B ... outer peripheral fitting surface, 12, 13 ... bearing.

Claims (4)

ガスタービンのシャフト側の筒状支持部材に形成された筒状の嵌合締結部を内周側とし、ガスタービンのコンプレッサディスクおよびタービンディスクの少なくともタービンディスクに形成された筒状の焼ばめ締結部を外周側として、前記嵌合締結部に前記焼ばめ締結部を焼ばめする焼ばめ締結構造であって、
前記焼ばめ締結部の遠心方向への剛性が前記筒状支持部材の遠心方向への剛性よりも相対的に大きく設定されていることを特徴とするガスタービンの焼きばめ締結構造。 A cylindrical fitting fastening portion formed on the cylindrical support member on the shaft side of the gas turbine is used as an inner peripheral side, and a cylindrical shrink-fitting fastening is formed on at least the turbine disk of the compressor disk and the turbine disk of the gas turbine. A shrink-fitting fastening structure in which the shrink-fitting fastening part is shrink-fitted to the fitting fastening part, with the part as the outer peripheral side,
A shrink fit fastening structure for a gas turbine, wherein the rigidity of the shrink fit fastening portion in the centrifugal direction is set to be relatively larger than the stiffness of the cylindrical support member in the centrifugal direction. 前記焼ばめ締結部は、前記筒状支持部材の材料よりもヤング率の大きい材料で構成されていることを特徴とする請求項１に記載のガスタービンの焼ばめ締結構造。   The shrink fit fastening structure for a gas turbine according to claim 1, wherein the shrink fit fastening portion is made of a material having a Young's modulus greater than that of the cylindrical support member. 前記筒状支持部材は、前記シャフト側の基端部に向かって漸次薄肉化されていることを特徴とする請求項１または２に記載のガスタービンの焼ばめ締結構造。   3. The shrink fit fastening structure for a gas turbine according to claim 1, wherein the cylindrical support member is gradually thinned toward a base end portion on the shaft side. 4. 前記焼ばめ締結部は、突出長が前記筒状支持部材の嵌合締結部の突出長よりも短く設定されていることを特徴とする請求項１〜３の何れかに記載のガスタービンの焼ばめ締結構造。   4. The gas turbine according to claim 1, wherein the shrink-fitting fastening portion is set to have a projection length shorter than a projection length of the fitting fastening portion of the cylindrical support member. Shrink fit fastening structure.
JP2007060467A 2007-03-09 2007-03-09 Shrink fit fastening structure of gas turbine Expired - Fee Related JP4935435B2 (en)

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