JP2008223541A - Shrinkage fitting fastening structure for gas turbine - Google Patents

Shrinkage fitting fastening structure for gas turbine Download PDF

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JP2008223541A
JP2008223541A JP2007060471A JP2007060471A JP2008223541A JP 2008223541 A JP2008223541 A JP 2008223541A JP 2007060471 A JP2007060471 A JP 2007060471A JP 2007060471 A JP2007060471 A JP 2007060471A JP 2008223541 A JP2008223541 A JP 2008223541A
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shrink
shaft
fitting fastening
fitting
gas turbine
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JP4835475B2 (en
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Koji Haruguchi
幸治 春口
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Toyota Motor Corp
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<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 support member at a shaft side of the gas turbine and a cylindrical connection part or a cylindrical support member at at least a turbine disk side of a compressor disk and the turbine disk. <P>SOLUTION: In the shrinkage fitting fastening structure, when the compressor disks 4, 5 and the turbine disks 6, 7 are rotated with a shaft 1 at a high speed, a first shrinkage fitting fastening part 11A at a rear shaft 11 side arranged at an inner peripheral side of the shrinkage fitting fastening structure is relatively largely deflected in a centrifugal direction relative to a second shrinkage fitting fastening part 7B2 of a cylindrical arm 7B arranged at an outer peripheral side by addition of each mass. Therefore, an outer peripheral fitting surface 11B of the first shrinkage fitting fastening part 11A at an inner peripheral side is pressed to an inner peripheral fitting surface 7B1 of the second shrinkage fitting fastening part 7B2 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（ラッパ状ないしロート状）または段付き筒状の支持部材の大径部に形成された焼ばめ締結部と、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設けられた筒状アームなどの筒状接続部または筒状支持部材の焼ばめ締結部とを焼ばめ締結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 the support structure, a shrink-fitting fastening portion formed on a large-diameter portion of a tapered cylindrical (trumpet or funnel) or stepped cylindrical support member provided before and after the shaft, and a compressor Generally, a structure in which a cylindrical connecting portion such as a cylindrical arm provided on a side surface of the disk and the turbine disk or a shrink-fitting fastening part of a cylindrical support member is fastened and fastened.
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、シャフト側の支持部材の焼ばめ締結部や、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接続部または筒状支持部材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 shrinkage fastening structure of the support structure as described above, the shrinkage fastening part of the support member on the shaft side, the tubular connection part on the compressor disk and the turbine disk side, or the shrinkage fit of the tubular support member. The shrink-fit force may be insufficient due to variations in the dimensions of the fastening portion. In this case, when each compressor disk and each turbine disk rotate at a high speed together with the shaft, the shrink-fitting fastening part on the outer peripheral side of the shrink-fitting fastening structure may be greatly bent by the centrifugal force, and the shrink-fitting 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支持部材と、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側の筒状接続部または筒状支持部材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。   Accordingly, the present invention provides for the occurrence of loosening of the shrink-fitting fastening structure between the support member on the shaft side of the gas turbine and the cylindrical connection part or the cylindrical support member on at least the turbine disk side of the compressor disk and the turbine disk. It is an object of the present invention to provide a shrink fit fastening structure for a gas turbine that can be reliably prevented.

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支持部材に設けられた第１の焼ばめ締結部と、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側の筒状接続部または筒状接続部材に設けられた第２の焼ばめ締結部とを焼ばめする焼ばめ締結構造であって、第１、第２の焼ばめ締結部のうち、内周側に配置される一方の焼ばめ締結部は、外周側に配置される他方の焼ばめ締結部に較べて遠心方向への撓み量が相対的に大きく設定されていることを特徴とする。   A shrink fit fastening structure for a gas turbine according to the present invention includes a first shrink fit fastening portion provided on a support member on a shaft side of a gas turbine, and a cylindrical connection on at least a turbine disk side of a compressor disk and a turbine disk. Or a second shrink-fitting fastening portion that is fitted to a second shrink-fitting fastening portion provided on the cylindrical connecting member, and is an inner peripheral side of the first and second shrink-fitting fastening portions. One of the shrink-fitting fastening portions arranged in the above is characterized in that the amount of bending in the centrifugal direction is set to be relatively larger than that of the other shrink-fitting fastening portion arranged on the outer peripheral side.

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、内周側に配置される一方の焼ばめ締結部が外周側に配置される他方の焼ばめ締結部に対し相対的に大きく遠心方向へ撓む。このため、内周側の一方の焼ばめ締結部が外周側の他方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 fit fastening structure of the 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 other shrink fit fastening portion disposed on the inner peripheral side is disposed on the outer peripheral side. It bends in the centrifugal direction relatively large with respect to the shrink-fitting fastening portion. For this reason, one shrink fit fastening part on the inner peripheral side is pressed against the other shrink fit fastening part on the outer peripheral side, and the occurrence of loosening of the shrink fit 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、第１の焼ばめ締結部が一方の焼ばめ締結部として内周側に配置されている場合、第１の焼ばめ締結部には、その遠心方向への撓み量を増大させるためのマスが付加されているのが好ましい。この場合、外周側の第２の焼ばめ締結部の遠心方向への撓み量に対する内周側の第１の焼ばめ締結部の遠心方向への撓み量が確実に大きくなる。   In the shrink fit fastening structure of the gas turbine of the present invention, when the first shrink fit fastening portion is arranged on the inner peripheral side as one shrink fit fastening portion, the first shrink fit fastening portion includes It is preferable that a mass for increasing the amount of bending in the centrifugal direction is added. In this case, the amount of bending in the centrifugal direction of the first shrink fitting fastening portion on the inner periphery side with respect to the amount of bending in the centrifugal direction of the second shrink fitting fastening portion on the outer periphery side is reliably increased.

また、第１の焼ばめ締結部にマスが付加されている場合、第１の焼ばめ締結部には、これを遠心方向に撓み易くするための切込みまたはすり割りが形成されているのが好ましい。この場合、内周側の第１の焼ばめ締結部は、切込みまたはすり割りにより遠心方向に容易に撓む。   In addition, when a mass is added to the first shrink-fitting fastening part, the first shrink-fitting fastening part is formed with a cut or slit to make it easier to bend in the centrifugal direction. Is preferred. In this case, the first shrink-fitting fastening portion on the inner peripheral side is easily bent in the centrifugal direction by cutting or slitting.

一方、本発明のガスタービンの焼ばめ締結構造において、第２の焼ばめ締結部が他方の焼ばめ締結部として外周側に配置されている場合、第２の焼ばめ締結部が設けられた筒状接続部または筒状接続部材は、第２の焼ばめ締結部の遠心方向への撓み量が減少するように先端部に向かって漸次薄肉化されているのが好ましい。この場合、外周側の第２の焼ばめ締結部の遠心方向への撓み量に対する内周側の第１の焼ばめ締結部の遠心方向への撓み量が相対的に大きくなる。   On the other hand, in the shrink fit fastening structure of the gas turbine of the present invention, when the second shrink fit fastening portion is arranged on the outer peripheral side as the other shrink fit fastening portion, the second shrink fit fastening portion is It is preferable that the provided cylindrical connecting portion or the cylindrical connecting member is gradually thinned toward the tip so that the amount of bending of the second shrink-fitting fastening portion in the centrifugal direction is reduced. In this case, the amount of bending in the centrifugal direction of the first shrink fitting fastening portion on the inner periphery side relative to the amount of bending in the centrifugal direction of the second shrink fitting fastening portion on the outer periphery side becomes relatively large.

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、内周側の一方の焼ばめ締結部を外周側の他方の焼ばめ締結部に対し相対的に大きく遠心方向へ撓ませて外周側の他方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 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 one shrink-fitting fastening part on the inner peripheral side is connected to the other shrink-fitting fastening on the outer peripheral side. It is possible to bend in the centrifugal direction relatively large with respect to the portion and press the other shrink-fitting fastening portion on the outer peripheral side, thereby reliably preventing the occurrence of loosening of the shrink-fitting fastening structure. 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、その前後の面からシャフト１の軸方向に突出する筒状アーム４Ａ，４Ｂが筒状接続部として形成されている。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-stage compressor disk 4 is formed with cylindrical arms 4A and 4B protruding from the front and rear surfaces in the axial direction of the shaft 1 as cylindrical connection portions. 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が筒状接続部として形成されている。そして、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 protruding from the front and rear surfaces in the axial direction of the shaft 1 as a cylindrical connecting portion. 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が筒状接続部として形成されている。そして、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。   Cylindrical arms 6A and 6B projecting in the axial direction of the shaft 1 from the front and rear surfaces of the front turbine disk 6 are formed as cylindrical connection portions. 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、その前後の面からシャフト１の軸方向に突出する筒状アーム７Ａ，７Ｂが筒状接続部として形成されている。そして、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。   Cylindrical arms 7A and 7B projecting in the axial direction of the shaft 1 from the front and rear surfaces of the turbine disk 7 at the rear stage are formed as cylindrical connecting portions. 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筒状アーム（筒状接続部）４Ａを支持する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筒状アーム（筒状接続部）７Ｂを支持する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 support member that supports a cylindrical arm (cylindrical connecting 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 as a support member that supports a cylindrical arm (cylindrical connecting portion) 7B that protrudes rearward from the rear surface of the rear turbine disk 7 is fixed.

フロントシャフト１０は、大径部に筒状アーム４Ａが焼ばめ締結されるテーパ筒状（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、大径部に筒状アーム７Ｂが焼ばめ締結されるテーパ筒状（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 cylindrical arm 4A is fastened and fastened to the large diameter portion, and is positioned in front of the shaft 1 in the axial direction from the large diameter portion. The small diameter portion is fixed to the front portion of the shaft 1 by, for example, screwing. Similarly, the rear shaft 11 is formed in a tapered tubular shape (trumpet shape or funnel shape) in which the cylindrical arm 7B is fastened and fastened to the large diameter portion, and the shaft 1 is axially rearward from the large diameter portion. The small-diameter portion located at 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の筒状アーム（筒状接続部）７Ｂの内周側にインロー嵌合する第１の焼ばめ締結部１１Ａが形成されており、この第１の焼ばめ締結部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 FIG. 2, the rear shaft 11 formed in a tapered cylindrical shape has a first portion that is inlay-fitted to the inner peripheral side of the cylindrical arm (cylindrical connecting portion) 7B of the turbine disk 7 in the subsequent stage. 11A is formed, and an outer peripheral fitting surface 11B is formed in the first shrink-fitting fastening portion 11A.

一方、筒状アーム（筒状接続部）７Ｂの先端側には、第１の焼ばめ締結部１１Ａの外周嵌合面１１Ｂに焼ばめされる内周嵌合面７Ｂ１が形成されており、この内周嵌合面７Ｂ１を有する筒状アーム（筒状接続部）７Ｂの先端側が第２の焼ばめ締結部７Ｂ２を構成している。   On the other hand, an inner peripheral fitting surface 7B1 that is shrink fitted to the outer peripheral fitting surface 11B of the first shrink fitting fastening portion 11A is formed on the distal end side of the cylindrical arm (cylindrical connecting portion) 7B. The tip end side of the cylindrical arm (cylindrical connecting portion) 7B having the inner peripheral fitting surface 7B1 constitutes the second shrink-fitting fastening portion 7B2.

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）および式（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、ｍｒはリヤシャフト１１の質量、Ｒｒはリヤシャフト１１の重心半径、ωｒはリヤシャフト１１の回転角速度である。
（１）……ｙｒ＝（Ｆｒ）（Ｌｒ）４／８（Ｅｒ）（Ｉｒ）
（２）……Ｆｒ＝（ｍｒ）（Ｒｒ）（ωｒ）２ Here, the amount of bending of the rear shaft 11 in the centrifugal direction can be obtained by the following equations (1) and (2) as the amount of bending of the cantilever beam that receives an evenly distributed load due to the centrifugal force. 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 equation (2), mr is the mass of the rear shaft 11, Rr is the center of gravity radius of the rear shaft 11, and ωr is the rotational angular velocity of the rear shaft 11.
(1) ...... yr = (Fr ) (Lr) 4/8 (Er) (Ir)
(2) ... Fr = (mr) (Rr) (ωr) 2

同様に、筒状アーム（筒状接続部）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）および式（４）により求めることができる。なお、式（３）において、ｙｄは筒状アーム７Ｂの遠心方向への撓み量、Ｆｄは筒状アーム７Ｂが受ける遠心力、Ｌｄは筒状アーム７Ｂの片持ち梁としての長さ、Ｅｄは筒状アーム７Ｂのヤング率、Ｉｄは筒状アーム７Ｂの断面２次モーメントである。また、式（４）において、ｍｄは筒状アーム７Ｂの質量、Ｒｄは筒状アーム７Ｂの重心半径、ωｄは筒状アーム７Ｂの回転角速度である。
（３）……ｙｄ＝（Ｆｄ）（Ｌｄ）４／８（Ｅｄ）（Ｉｄ）
（４）……Ｆｄ＝（ｍｄ）（Ｒｄ）（ωｄ）２ Similarly, the amount of bending in the centrifugal direction of the cylindrical arm (cylindrical connecting portion) 7B is expressed by the following equations (3) and (4) as the amount of bending of the cantilever beam that receives an evenly distributed load due to centrifugal force. Can be sought. In Equation (3), yd is the amount of bending of the cylindrical arm 7B in the centrifugal direction, Fd is the centrifugal force received by the cylindrical arm 7B, Ld is the length of the cylindrical arm 7B as a cantilever, and Ed is The Young's modulus, Id, of the cylindrical arm 7B is the moment of inertia of the cross section of the cylindrical arm 7B. In equation (4), md is the mass of the cylindrical arm 7B, Rd is the center of gravity radius of the cylindrical arm 7B, and ωd is the rotational angular velocity of the cylindrical arm 7B.
(3) ...... yd = (Fd ) (Ld) 4/8 (Ed) (Id)
(4) ... Fd = (md) (Rd) (ωd) 2

ここで、ｙｒ＞ｙｄとすれば、リヤシャフト１１の第１の焼ばめ締結部１１Ａと筒状アーム７Ｂの第２の焼ばめ締結部７Ｂ２との間の焼ばめ締結構造の緩みの発生を防止することができる。そして、ｙｒ＞ｙｄとするには、例えばＦｒ＞Ｆｄとなるようにｍｒ＞ｍｄとすればよい。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、ｍｒ＞ｍｄとすることでｙｒ＞ｙｄとなるようにしている。   Here, if yr> yd, the loose-fitting fastening structure between the first shrink-fitting fastening portion 11A of the rear shaft 11 and the second shrink-fitting fastening portion 7B2 of the cylindrical arm 7B is loosened. Occurrence can be prevented. In order to satisfy yr> yd, for example, mr> md may be set so that Fr> Fd. Therefore, in the shrink-fitting fastening structure of the gas turbine according to the embodiment, by setting mr> md, yr> yd is established.

すなわち、図３に示すように、リヤシャフト１１の第１の焼ばめ締結部１１Ａの内周側には、第１の焼ばめ締結部１１Ａの遠心方向への撓み量を増大させる手段として、ｍｒ＞ｍｄとするための複数のマス１１Ｃ，１１Ｃ…が付加されている。これらのマス１１Ｃ，１１Ｃ…は、第１の焼ばめ締結部１１Ａの内周側に肉盛りされた厚肉部をその内周側から放射方向（遠心方向）に形成された複数の切込み（またはすり割り）１１Ｄ，１１Ｄ…により円周方向に複数に分割することで形成されている。   That is, as shown in FIG. 3, on the inner peripheral side of the first shrink fit fastening portion 11A of the rear shaft 11, as means for increasing the amount of bending of the first shrink fit fastening portion 11A in the centrifugal direction. , Mr> md, a plurality of cells 11C, 11C... Are added. These masses 11C, 11C,... Have a plurality of cuts (in the radial direction (centrifugal direction) formed from the inner peripheral side of the thick portion built up on the inner peripheral side of the first shrink-fitting fastening portion 11A ( (Or slotting) 11D, 11D...

そして、これらのマス１１Ｃ，１１Ｃ…が付加されることにより、リヤシャフト１１側の第１の焼ばめ締結部１１Ａは、筒状アーム７Ｂ側の第２の焼ばめ締結部７Ｂ２に較べて遠心方向への撓み量が相対的に大きく設定されている。なお、図１に示したフロントシャフト１０もリヤシャフト１１と同様に構成されており、フロントシャフト１０側の第１の焼ばめ締結部は、前段のコンプレッサディスク４の筒状アーム４Ａ側の第２の焼ばめ締結部に較べて遠心方向への撓み量が相対的に大きく設定されている。   Then, by adding these masses 11C, 11C..., The first shrink-fitting fastening portion 11A on the rear shaft 11 side is compared with the second shrink-fitting fastening portion 7B2 on the cylindrical arm 7B side. The amount of bending in the centrifugal direction is set relatively large. The front shaft 10 shown in FIG. 1 is also configured in the same manner as the rear shaft 11, and the first shrink-fitting fastening portion on the front shaft 10 side is the first on the cylindrical arm 4A side of the compressor disk 4 in the previous stage. The amount of bending in the centrifugal direction is set to be relatively larger than that of the shrink-fitting fastening portion 2.

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側の第１の焼ばめ締結部１１Ａが筒状アーム７Ｂ側の第２の焼ばめ締結部７Ｂ２に対し相対的に大きく遠心方向へ撓む。   In the shrink-fit fastening structure of the gas turbine of the present embodiment configured as described above, the front compressor disk 4, the rear compressor disk 5, the front turbine disk 6 and the rear turbine together with the shaft 1 shown in FIG. When the disk 7 rotates at a high speed, the first shrink-fitting fastening portion 11A on the rear shaft 11 side bends in the centrifugal direction relatively largely with respect to the second shrink-fitting fastening portion 7B2 on the cylindrical arm 7B side.

このため、リヤシャフト１１側の第１の焼ばめ締結部１１Ａの外周嵌合面１１Ｂが筒状アーム７Ｂ側の第２の焼ばめ締結部７Ｂ２の内周嵌合面７Ｂ１に押圧されるようになり、第１の焼ばめ締結部１１Ａと第２の焼ばめ締結部７Ｂ２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 first shrink-fitting fastening portion 11A on the rear shaft 11 side is pressed against the inner peripheral fitting surface 7B1 of the second shrink-fitting fastening portion 7B2 on the cylindrical arm 7B side. Thus, the occurrence of loosening of the shrink fit fastening structure between the first shrink fit fastening portion 11A and the second shrink fit fastening portion 7B2 is reliably prevented.

同様に、フロントシャフト１０側の第１の焼ばめ締結部(符号省略)が前段のコンプレッサディスク４の筒状アーム４Ａ側の第２の焼ばめ締結部(符号省略)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側の第１の焼ばめ締結部の外周嵌合面(符号省略)が筒状アーム４Ａ側の第２の焼ばめ締結部の内周嵌合面(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, the first shrink-fitting fastening part (reference numeral omitted) on the front shaft 10 side is relatively relative to the second shrink-fitting fastening part (reference numeral omitted) on the cylindrical arm 4A side of the compressor disk 4 in the previous stage. Because of the large bending in the centrifugal direction, the outer periphery fitting surface (reference numeral omitted) of the first shrink fit fastening portion on the front shaft 10 side is the inner circumference fit of the second shrink fit fastening portion on the cylindrical arm 4A side. It is pressed against the surface (reference number omitted), and the occurrence of loosening of the shrink-fitting fastening structure between them 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側の筒状アーム７Ａ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側の筒状アーム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 fit fastening structure of the gas turbine of the present embodiment, the loose fit of the shrink fit fastening structure between the rear shaft 11 on the shaft 1 side and the tubular arm 7A on the turbine turbine 7 side on the rear stage is generated. Similarly, it is possible to reliably prevent the occurrence of loosening of the shrink-fitting fastening structure between the front shaft 10 on the shaft 1 side and the cylindrical arm 4A on the front compressor disk 4 side. 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および図３に示したリヤシャフト１１は、図４および図５に示す形状に変更してもよい。   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 rear shaft 11 shown in FIGS. 2 and 3 may be changed to the shape shown in FIGS. 4 and 5.

図４および図５に示すリヤシャフト１１は、第１の焼ばめ締結部１１Ａの外周側に複数のマス１１Ｅ，１１Ｅ…を付加したものである。これらのマス１１Ｅ，１１Ｅ…は、第１の焼ばめ締結部１１Ａの外周側に肉盛りされた厚肉部をその外周側から放射方向（遠心方向）に形成された複数の切込み（またはすり割り）１１Ｆ，１１Ｆ…により円周方向に複数に分割することで形成されている。   The rear shaft 11 shown in FIGS. 4 and 5 is obtained by adding a plurality of masses 11E, 11E... To the outer peripheral side of the first shrink-fitting fastening portion 11A. These masses 11E, 11E,... Have a plurality of cuts (or rubs) formed in the radial direction (centrifugal direction) from the outer peripheral side of the thick portion that is built up on the outer peripheral side of the first shrink-fitting fastening portion 11A. (Division) 11F, 11F... And divided into a plurality in the circumferential direction.

図４および図５に示したリヤシャフト１１は、前述したｍｒ＞ｍｄの関係を満足すると共に、Ｒｒ＞Ｒｄの関係も満足する。このため、図１に示したシャフト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が高速回転する際、リヤシャフト１１側の第１の焼ばめ締結部１１Ａが筒状アーム７Ｂ側の第２の焼ばめ締結部７Ｂ２に対し相対的に一層大きく遠心方向へ撓む。   The rear shaft 11 shown in FIGS. 4 and 5 satisfies the relationship of mr> md described above and also satisfies the relationship of Rr> Rd. Therefore, when the front compressor disk 4, the rear compressor disk 5, the front turbine disk 6 and the rear turbine disk 7 together with the shaft 1 shown in FIG. The female fastening portion 11A bends in the centrifugal direction relatively larger than the second shrink-fitting fastening portion 7B2 on the cylindrical arm 7B side.

そして、リヤシャフト１１側の第１の焼ばめ締結部１１Ａの外周嵌合面１１Ｂが筒状アーム７Ｂ側の第２の焼ばめ締結部７Ｂ２の内周嵌合面７Ｂ１に強く押圧されるようになり、第１の焼ばめ締結部１１Ａと第２の焼ばめ締結部７Ｂ２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および図５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 first shrink fitting fastening portion 11A on the rear shaft 11 side is strongly pressed against the inner peripheral fitting surface 7B1 of the second shrink fitting fastening portion 7B2 on the cylindrical arm 7B side. As a result, the occurrence of loosening of the shrink fit fastening structure between the first shrink fit fastening portion 11A and the second shrink fit fastening portion 7B2 is more reliably prevented. The front shaft 10 configured in the same manner as the rear shaft 11 shown in FIGS. 4 and 5 also has the same function and effect.

一方、図２に示した後段のタービンディスク７の筒状アーム７Ｂは、図６に示すように変形してもよい。すなわち、筒状アーム７Ｂは、第２の焼ばめ締結部７Ｂ２の遠心方向への撓み量が減少するように、外径を先端部に向かって漸次減少させることで肉厚を先端部に向かって漸次薄肉化してもよい。   On the other hand, the cylindrical arm 7B of the subsequent turbine disk 7 shown in FIG. 2 may be deformed as shown in FIG. That is, the cylindrical arm 7B has a wall thickness toward the tip portion by gradually decreasing the outer diameter toward the tip portion so that the amount of bending of the second shrink-fitting fastening portion 7B2 in the centrifugal direction is reduced. The thickness may be gradually reduced.

この場合、前述したｍｒ＞ｍｄにおけるｍｄが減少し、後段のタービンディスク７の筒状アーム７Ｂ側の第２の焼ばめ締結部７Ｂ２の遠心方向への撓み量に対するリヤシャフト１１側の第１の焼ばめ締結部１１Ａの遠心方向への撓み量が相対的に大きくなる。このため、第１の焼ばめ締結部１１Ａと第２の焼ばめ締結部７Ｂ２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 this case, md at mr> md described above decreases, and the first shaft on the rear shaft 11 side with respect to the amount of bending in the centrifugal direction of the second shrink-fitting fastening portion 7B2 on the cylindrical arm 7B side of the turbine disk 7 in the subsequent stage is reduced. The amount of bending of the shrink-fitting fastening portion 11A in the centrifugal direction becomes relatively large. For this reason, generation | occurrence | production of the loosening of the shrink-fitting fastening structure between 11A of 1st shrink-fitting fastening parts and the 2nd shrink-fitting fastening part 7B2 is prevented more reliably.

なお、後段のタービンディスク７に筒状接続部として一体に形成された筒状アーム７Ｂは、筒状接続部材としてタービンディスク７に適宜の手段で固定される別部材であってもよい。前段のコンプレッサディスク４の筒状アーム４Ａも同様である。   Note that the cylindrical arm 7B integrally formed as a cylindrical connection portion on the subsequent turbine disk 7 may be a separate member fixed to the turbine disk 7 by an appropriate means as a cylindrical connection member. The same applies to the cylindrical arm 4A of the compressor disk 4 at the preceding stage.

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筒状アーム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 cylindrical arm of a subsequent turbine disk shown in FIG. 1 on a 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４に示したリヤシャフトの大径側から見た斜視図である。It is the perspective view seen from the large diameter side of the rear shaft shown in FIG. 図２に示した筒状アームの変形例を示す図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 cylindrical arm 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，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，７Ｂ…筒状アーム、７Ｂ１…内周嵌合面、７Ｂ２…第２の焼ばめ締結部、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…第１の焼ばめ締結部、１１Ｂ…外周嵌合面、１１Ｃ…マス、１１Ｄ…切込み、１２，１３…ベアリング。   DESCRIPTION OF SYMBOLS 1 ... Shaft, 2 ... Compressor, 3 ... Turbine, 4 ... Front stage compressor disk, 4A, 4B ... Cylindrical arm, 4C ... Impeller, 5 ... Rear stage compressor disk, 5A, 5B ... Cylindrical arm, 5C ... Impeller, 6 ... front stage turbine disk, 6A, 6B ... cylindrical arm, 6C ... blade, 7 ... rear stage turbine disk, 7A, 7B ... cylindrical arm, 7B1 ... inner peripheral fitting surface, 7B2 ... second shrink fit Fastening part, 7C ... blade, 8 ... casing, 9 ... combustor, 10 ... front shaft, 11 ... rear shaft, 11A ... first shrink fitting fastening part, 11B ... outer peripheral fitting surface, 11C ... mass, 11D ... Cuts, 12, 13 ... bearings.

Claims (4)

ガスタービンのシャフト側の支持部材に設けられた第１の焼ばめ締結部と、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側の筒状接続部または筒状接続部材に設けられた第２の焼ばめ締結部とを焼ばめする焼ばめ締結構造であって、
前記第１、第２の焼ばめ締結部のうち、内周側に配置される一方の焼ばめ締結部は、外周側に配置される他方の焼ばめ締結部に較べて遠心方向への撓み量が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ばめ締結構造。 A first shrink-fitting fastening portion provided on the support member on the shaft side of the gas turbine; and a second shrink-fitting portion provided on the cylindrical connection portion or the cylindrical connection member on at least the turbine disk side of the compressor disk and the turbine disk. It is a shrink-fitting fastening structure that fits the fitting fastening part.
Of the first and second shrink-fitting fastening portions, one of the shrink-fitting fastening portions arranged on the inner peripheral side is in the centrifugal direction as compared with the other shrink-fitting fastening portion arranged on the outer peripheral side. A shrink-fit fastening structure for a gas turbine, wherein the amount of bending of the gas turbine is set to be relatively large. 前記支持部材の第１の焼ばめ締結部が一方の焼ばめ締結部として内周側に配置されており、この第１の焼ばめ締結部にはマスが付加されていることを特徴とするを請求項１に記載のガスタービンの焼ばめ締結構造。   The first shrink fit fastening portion of the support member is disposed on the inner peripheral side as one shrink fit fastening portion, and a mass is added to the first shrink fit fastening portion. The shrink fit fastening structure for a gas turbine according to claim 1. 前記マスが付加された前記第１の焼ばめ締結部には、切込みまたはすり割りが形成されていることを特徴とする請求項２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 2, wherein a cut or slit is formed in the first shrink fit fastening portion to which the mass is added. 前記第２の焼ばめ締結部が設けられた前記筒状接続部または筒状接続部材は、先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２または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 cylindrical connecting part or the cylindrical connecting member provided with the second shrink-fitting fastening part is gradually thinned toward the tip part. The shrink fit fastening structure of the described gas turbine.
JP2007060471A 2007-03-09 2007-03-09 Shrink fit fastening structure of gas turbine Expired - Fee Related JP4835475B2 (en)

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EP3461584A1 (en) * 2017-09-29 2019-04-03 Safran Aircraft Engines Method for producing a high-pressure compressor rotor of a turbine engine

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