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JP2009063000A - Structure for attaching spindle bolt of compressor - Google Patents

Structure for attaching spindle bolt of compressor Download PDF

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Publication number
JP2009063000A
JP2009063000A JP2008323189A JP2008323189A JP2009063000A JP 2009063000 A JP2009063000 A JP 2009063000A JP 2008323189 A JP2008323189 A JP 2008323189A JP 2008323189 A JP2008323189 A JP 2008323189A JP 2009063000 A JP2009063000 A JP 2009063000A
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bolt
spindle bolt
spindle
shaft end
compressor
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JP4969562B2 (en
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Ryutaro Umagoe
龍太郎 馬越
Taku Ichiyanagi
卓 一柳
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Mitsubishi Heavy Industries Ltd
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Mitsubishi Heavy Industries Ltd
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Abstract

<P>PROBLEM TO BE SOLVED: To prevent a flexural deformation of a rotor disk during operation to improve the fatigue strength of a structure for attaching a spindle bolt of a gas turbine compressor. <P>SOLUTION: A number of disks 82 are arranged between a front shaft-end part 2 and a rear shaft-end part 4 in the axial direction making torque arms come into contact with each other, and are tightened by means of a spindle bolt 1 and a nut 3. The disks 10, 11 corresponding to two stages are integrally formed at a rear side of the front shaft-end part 2 so as to have a recess 13 between two disks. Such a structure enables prevention of a disk-like deformation of the disks 10, 11 and also the improved stiffness of the attachment structure at both ends of the spindle bolt 1. Consequently, a flexural deformation of the bolt 1 during rotation is prevented, and its fatigue strength is enhanced. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

本発明はガスタービン圧縮機のスピンドルボルト取付構造に関し、スピンドルボルト締付時のディスク側のたわみを小さくして回転中にスピンドルボルトにかかる曲げを低減させ、ボルトの疲労強度を向上させるような取付構造としたものである。   BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a spindle bolt mounting structure for a gas turbine compressor. It is structured.

ガスタービンの圧縮機においては、周囲に動翼が取付けられる圧縮機円板をスピンドルボルトで軸方向に多重に結合し、各圧縮機円板からはトルクアームを出し、トルクアームを接触させて、このアームの摩擦と円板同志の接合部に挿入されるラジアルピンによってトルクを伝達する構造となっている。   In a compressor of a gas turbine, a compressor disk on which a moving blade is attached around is connected in multiples by a spindle bolt in the axial direction, a torque arm is taken out from each compressor disk, and the torque arm is contacted, Torque is transmitted by a radial pin inserted into the joint between the arm friction and the disk.

図7は上記の圧縮機が用いられている従来のガスタービンの全体の構成を示す断面図である。図において、50は圧縮機であり、内部には固定側に取付けられた静翼と回転軸54の周囲に取付けられた動翼とが交互に配置され、かつ、多段に配設され、吸気60のように吸気し、空気を圧縮する構成となっている。51は燃焼器であり、圧縮機50から吐出される空気を吸入して燃料を燃焼させ、高温の燃焼ガスをタービン部52へ供給する。タービン部52では高温の燃焼ガスが膨張することによりタービン動翼に回転エネルギーを与えガスタービンロータを回転させ、仕事を終えたガスは排気フード53を通り、排気61として外部へ流出する。圧縮機50は上記したように多数の圧縮機円板を軸方向に接続し、スピンドルボルト55で締め付けてこれらを軸方向に固定し、これら軸方向の円板の外周囲には動翼が取付けられている。このスピンドルボルト55は圧縮機円板の周方向に複数本が等間隔に配置され、軸方向に円板を連結する構成となっている。   FIG. 7 is a cross-sectional view showing the overall configuration of a conventional gas turbine in which the above-described compressor is used. In the figure, reference numeral 50 denotes a compressor, in which stationary blades attached to the fixed side and moving blades attached around the rotary shaft 54 are alternately arranged and arranged in multiple stages, and an intake air 60 In this way, the air is sucked and the air is compressed. Reference numeral 51 denotes a combustor that sucks air discharged from the compressor 50 to burn fuel and supplies high-temperature combustion gas to the turbine unit 52. In the turbine section 52, the high-temperature combustion gas expands to give rotational energy to the turbine rotor blades to rotate the gas turbine rotor, and the finished gas passes through the exhaust hood 53 and flows out as exhaust 61 to the outside. As described above, the compressor 50 has a large number of compressor disks connected in the axial direction, and is fastened with a spindle bolt 55 to fix them in the axial direction. A rotor blade is attached to the outer periphery of the disks in the axial direction. It has been. A plurality of the spindle bolts 55 are arranged at equal intervals in the circumferential direction of the compressor disk, and the disks are connected in the axial direction.

又、ガスタービンプラントの回転軸は、一般的には軸方向に2ヶ所、即ち、No.1軸受56とNo.2軸受57とで2点支持されており、軸方向の流路が増加すると、支持間隔が長くなり、軸の自重により下方へたわみが生じた状態で回転することになり、スピンドルボルト80に引張りや曲げ力が繰り返し加わり、疲労によるボルトの強度低下をまねく結果となる。   In addition, the rotating shaft of the gas turbine plant is generally two places in the axial direction, that is, No. 1 bearing 56 and No. 1 The two bearings 57 are supported at two points. When the axial flow path is increased, the support interval becomes longer, and the shaft is rotated in a state where the shaft is bent downward due to the weight of the shaft. Or bending force is repeatedly applied, resulting in a decrease in bolt strength due to fatigue.

図8は従来のガスタービン圧縮機のスピンドルボルト締結部で、図7のA部詳細を示す断面図である。図において、ロータは多数の円板をスピンドルボルトで締め付けて構成しているが、ロータとして必要な条件は、1本の回転軸として有害な振動が無くて安定して回転すること、翼をその遠心力に耐えて保持すること、及び翼が発生或いは吸収するトルクを確実に伝えることにある。   FIG. 8 is a sectional view showing the details of a portion A of FIG. 7 at a spindle bolt fastening portion of a conventional gas turbine compressor. In the figure, the rotor is configured by tightening a large number of discs with spindle bolts. However, the necessary conditions for the rotor are that it can rotate stably without harmful vibration as a single rotating shaft, It is to withstand and hold the centrifugal force and to reliably transmit the torque generated or absorbed by the blade.

図8において、各段毎に翼を保持する円板82を設け、それを全段軸方向にボルト1で締め付けて1本の軸としている。上記の条件に従って言えば、円板82は翼83を支えて回転する。その時できるだけ遠心応力に対して有利な形状としている。一方、軸として振動が安定であるためには、軸方向に連続した円筒部分81ができるだけ大径であるようにしている。トルクもこの円筒部分で伝えられている。なお、トルク伝達に関しては本発明の対象外であるので、これ以上は言及しない。   In FIG. 8, a disk 82 for holding a blade is provided for each stage, and is tightened with a bolt 1 in the axial direction of all stages to form one axis. If it says according to said conditions, the disc 82 will support the wing | blade 83 and will rotate. At that time, the shape is as advantageous as possible against centrifugal stress. On the other hand, in order for vibration to be stable as an axis, the cylindrical portion 81 continuous in the axial direction is made as large as possible. Torque is also transmitted in this cylindrical part. Since torque transmission is outside the scope of the present invention, no further description will be made.

各円板82を積み重ねて、それらを1本の軸になるように締め付けるボルト1が軸中心からの半径Rの円周上に適当な数配置されている。一般に、このように配置されたボルトとナットには遠心力が働き、この遠心力がナットが締まるオーバハング部分や、段間の支えのない部分に高い曲げ応力が発生する。図では高速回転で、かつ、軸の固有振動数を高くするために円筒部分81をできるだけ外径側に設け、ボルト1の位置は過大遠心力に伴う困難さを避けるために比較的小径となるように位置させている。 An appropriate number of bolts 1 for stacking the respective discs 82 and fastening them so as to become one shaft are arranged on the circumference of the radius R0 from the shaft center. In general, a centrifugal force acts on the bolts and nuts arranged in this manner, and this bending force generates high bending stress in an overhang portion where the nut is tightened or a portion where there is no support between steps. In the figure, a cylindrical portion 81 is provided on the outer diameter side as much as possible in order to increase the natural frequency of the shaft at a high speed, and the position of the bolt 1 has a relatively small diameter in order to avoid difficulties associated with excessive centrifugal force. It is positioned so that.

前述のように、できるだけ有利なロータの形状を追求するとき、端部の円板82に困難性が表れる。端の円板82では、ボルト荷重は半径Rの円上に加えられるのに対して、締付反力は円筒部分81のほぼ平均半径R円上に働く。その結果、円板82は半径差Rをモーメントの腕とするモーメントMを受け、皿形に変形する。ボルトの締結荷重は通常;
(1)各段毎に別々の円筒を積み重ねた時、しかも、それ等が全体として1本の円筒であるかのように振動体として振る舞うために必要な面圧を接合面に与える;
(2)トルクを摩擦で伝えるように設計する場合には、それに必要な面圧を接合面に与える;
(3)その面圧が定常運転時、円板が半径方向に温度分布がある(即ち熱伸差がある)状態など、どのような時にも所要値を維持する;
の条件を満たすように決定されるが、このようにして定めた締付荷重は通常かなり大きな値となる。このために前記円板82の皿形の歪量もかなりの量となる。
As described above, when the rotor shape that is as advantageous as possible is sought, difficulty appears in the circular plate 82 at the end. In the circular plate 82 of the end, the bolt load to the applied on a circle of a radius R 0, the reaction force tightening acts substantially on average radius R 1 yen cylindrical section 81. As a result, the disc 82 is subjected to a moment M to the radius difference R 2 and the moment arm, is deformed into a dish shape. Bolt tightening load is usually;
(1) When separate cylinders are stacked at each stage, the contact surface is given a surface pressure necessary to behave as a vibrating body as if they were a single cylinder as a whole;
(2) When the torque is designed to be transmitted by friction, the necessary surface pressure is applied to the joint surface;
(3) Maintain the required value at any time, such as when the surface pressure is in steady operation and the disk has a temperature distribution in the radial direction (ie, there is a thermal expansion difference);
However, the tightening load determined in this way is usually a considerably large value. For this reason, the amount of distortion in the dish shape of the disk 82 also becomes a considerable amount.

この皿形変形の害はボルトを締め付けるナット座面に現れる。即ちボルトのネジ中心線に対しナットが傾いて噛合いネジの荷重分布で、ネジ噛合いの始点辺りの荷重集中が正しく同芯である場合に比較して大きくなる。ボルト1は軸1回転毎に交番応力が発生し、従って荷重集中(応力集中)が甚だしくなればネジ部の交番応力も大きくなり、疲労破断を招く。   The harm of this dish-shaped deformation appears on the nut seat that tightens the bolt. That is, the nut is inclined with respect to the screw center line of the bolt, and the load distribution of the meshing screw becomes larger than when the load concentration around the starting point of the screw meshing is correct and concentric. The bolt 1 generates an alternating stress every rotation of the shaft. Therefore, if the load concentration (stress concentration) becomes large, the alternating stress of the screw portion also increases, leading to fatigue fracture.

そこで本発明は、スピンドルボルトの両端の圧縮機円板の剛性を増すような構造とし、スピンドルボルトの両端面が回転軸のたわみの影響を受けても、ボルトの軸と直交する平面を保つようにしてスピンドルボルトの曲げ応力を少なくし、疲労強度を向上させ、信頼性を増すことのできる圧縮機のスピンドルボルト取付構造を提供することを課題としてなされたものである。   Therefore, the present invention is structured so as to increase the rigidity of the compressor disk at both ends of the spindle bolt so that even if both end surfaces of the spindle bolt are affected by the deflection of the rotating shaft, a plane perpendicular to the axis of the bolt is maintained. Thus, an object of the present invention is to provide a spindle bolt mounting structure for a compressor that can reduce the bending stress of the spindle bolt, improve the fatigue strength, and increase the reliability.

本発明は前述の課題を解決するために次の(1)〜(5)の手段を提供する。   The present invention provides the following means (1) to (5) in order to solve the above-mentioned problems.

(1)ガスタービン圧縮機の回転体を構成する前方軸端部、軸方向に多重に連接し軸方向に翼を配設するための複数の円板、後方軸端部、及び前記前方軸端部と複数の円板及び後方軸端部を軸方向に貫通し締め付ける複数のスピンドルボルトからなる圧縮機のスピンドルボルト取付構造において、前記前方軸端部には前記複数のスピンドルボルトが円周状に配設されボルト頭が接する取付周面を有し、同取付周面から前記スピンドルボルトが貫通する後方側には少なくとも2段分の円板を一体構造とし、同2段の円板間には外周側に凹部を形成することを特徴とする圧縮機のスピンドルボルト取付構造。   (1) A front shaft end portion constituting a rotating body of a gas turbine compressor, a plurality of disks for connecting a plurality of axially connected blades in the axial direction, a rear shaft end portion, and the front shaft end In the spindle bolt mounting structure of the compressor consisting of a plurality of spindle bolts that penetrate and tighten the end portion, the plurality of disks, and the rear shaft end portion in the axial direction, the plurality of spindle bolts are circumferentially arranged at the front shaft end portion. A mounting peripheral surface that is disposed and is in contact with a bolt head, and at least two stages of discs are integrated on the rear side through which the spindle bolt passes from the mounting peripheral surface. A spindle bolt mounting structure for a compressor, wherein a recess is formed on the outer peripheral side.

(2)前記2段分の円板は一体構造に代えて、それぞれ分離した構造とし接合してなることを特徴とする請求項1記載の圧縮機のスピンドルボルト取付構造。   (2) The spindle bolt mounting structure for a compressor according to claim 1, wherein the two-stage discs are joined as separate structures instead of an integral structure.

(3)前記2段分の円板間の凹部には円周状に段状の延長部を形成し、同延長部の側面には前記スピンドルボルトの頭が当接して取付けられることを特徴とする(1)記載の圧縮機のスピンドルボルト取付構造。   (3) A stepped extension is formed circumferentially in the recess between the two steps of the disks, and the head of the spindle bolt is attached to the side of the extension. The spindle bolt mounting structure for a compressor according to (1).

(4)前記2段分の円板は前記凹部において分離され接合した構造であることを特徴とする(3)記載の圧縮機のスピンドルボルト取付構造。   (4) The spindle bolt mounting structure for a compressor according to (3), wherein the two-stage discs are separated and joined in the recess.

(5)前記後方軸端部は一体の円形状構造体であり、前記スピンドルボルトの貫通穴開口部は軸方向と直交する同一平面を形成することを特徴とする(1)記載の圧縮機のスピンドルボルト。   (5) The compressor according to (1), wherein the rear shaft end is an integral circular structure, and the through hole opening of the spindle bolt forms a same plane perpendicular to the axial direction. Spindle bolt.

本発明の(1)においては、前方軸端部には取付周面から後端側が少なくとも2段分の円板が一体構造に形成され、スピンドルボルトのボルト頭は少なくとも2段分の円板部を介して挿入されるので、ボルト頭が当接する取付周面から後方の部分の構造体が強化され、この部分の剛性が高まる。又、後方軸端部の端面が円形状の同一面を形成し、この部分剛性も高まる。又、凹部が形成されているので、円板の皿形変形は、2段のうち後方の円板側においてのみ起こり、ボルト頭側にはほとんど歪みを起こさない。   In (1) of the present invention, at least a two-stage disk at the rear end side from the mounting peripheral surface is integrally formed on the front shaft end, and the bolt head of the spindle bolt is a disk part of at least two stages. Therefore, the structure of the rear part from the mounting peripheral surface with which the bolt head abuts is strengthened, and the rigidity of this part is increased. Further, the end surface of the rear shaft end portion forms the same circular surface, and this partial rigidity is also increased. Further, since the concave portion is formed, the dish-shaped deformation of the disk occurs only on the rear disk side of the two stages, and hardly causes distortion on the bolt head side.

本発明の(2)では、上記(1)の発明の円板間が分離されており、上記(1)の発明と同様の効果が得られると共に、製作上の面で有利となるものである。又、本発明の(3)においては、円板間には延長部が設けられ、延長部側面にスピンドルボルトが取付けられるので、円板が皿状に変形し倒れるのは延長部ではなく外方の厚さの薄い部分であり、ボルト取付面は変形の影響を受けることがなく、ボルトの疲労強度が向上する。又、本発明の(4)では、上記(3)の発明において円板が分離して構成され、上記(3)の発明と同様の効果が得られると共に、製作上も有利となるものである。   In (2) of the present invention, the discs of the invention of (1) are separated, and the same effects as those of the invention of (1) can be obtained, and it is advantageous in terms of production. . In (3) of the present invention, an extension is provided between the discs, and a spindle bolt is attached to the side of the extension, so that the disc is deformed into a dish shape and falls down, not the extension. The bolt mounting surface is not affected by deformation, and the fatigue strength of the bolt is improved. In the fourth aspect of the present invention, the disc is separated from the third aspect of the invention, and the same effect as the third aspect of the invention can be obtained and the production is advantageous. .

本発明の(5)では、後方軸端部の端面が円形状の同一面を形成し、この部分剛性も高まる。これにより運転中に両端面が圧縮や引張による曲げ変形力を受けても前方軸端部の取付周面と後方軸端部の端面が剛性が高い構造体となっているので、軸方向に対して絶えず垂直な面を保ち、スピンドルボルトの曲げを防止し、このためにボルトの疲労強度が向上する。   In (5) of the present invention, the end surface of the rear shaft end portion forms the same circular surface, and this partial rigidity is also increased. As a result, even if both end surfaces are subjected to bending deformation force due to compression or tension during operation, the mounting peripheral surface of the front shaft end and the end surface of the rear shaft end are highly rigid structures. It keeps the vertical surface constantly and prevents bending of the spindle bolt, which improves the fatigue strength of the bolt.

本発明の圧縮機のスピンドルボルト取付構造は、(1)ガスタービン圧縮機の回転体を構成する前方軸端部、軸方向に多重に連接し軸方向に翼を配設するための複数の円板、後方軸端部、及び前記前方軸端部と複数の円板及び後方軸端部を軸方向に貫通し締付ける複数のスピンドルボルトからなる圧縮機のスピンドルボルト取付構造において、前記前方軸端部には前記複数のスピンドルボルトが円周状に配設されボルト頭が接する取付周面を有し、同取付周面から前記スピンドルボルトが貫通する後方側には少なくとも2段分の円板を一体構造とし、同2段の円板間には外周側に凹部を形成することを特徴としている。このような構造により、ボルト頭が当接する取付周面から後方の部分の構造体が強化され、この部分の剛性が高まる。   The compressor bolt mounting structure of the compressor according to the present invention includes: (1) a front shaft end portion constituting a rotating body of a gas turbine compressor, a plurality of circles for connecting a plurality of shafts in the axial direction and arranging blades in the axial direction; In the spindle bolt mounting structure of a compressor comprising a plate, a rear shaft end portion, and a plurality of spindle bolts that penetrate and tighten the front shaft end portion and the plurality of disks and the rear shaft end portion in the axial direction, the front shaft end portion The plurality of spindle bolts are arranged in a circular shape and have a mounting peripheral surface with which the bolt head contacts, and at least two stages of discs are integrated on the rear side through which the spindle bolt passes from the mounting peripheral surface. The structure is characterized in that a recess is formed on the outer peripheral side between the two-stage discs. With such a structure, the structure of the rear part from the mounting peripheral surface with which the bolt head abuts is reinforced, and the rigidity of this part is increased.

本発明の(2)では、上記(1)の発明の円板間が分離されており、上記(1)の発明と同様の効果が得られると共に、製作上の面で有利となるものである。又、本発明の(3)においては、円板間には延長部が設けられ、延長部側面にスピンドルボルトが取付けられるので、円板が皿状に変形し倒れるのは延長部ではなく外方の厚さの薄い部分であり、ボルト取付面は変形の影響を受けることがなく、ボルトの疲労強度が向上する。又、本発明の(4)では、上記(3)の発明において円板が分離して構成され、上記(3)の発明と同様の効果が得られると共に、製作上も有利となるものである。   In (2) of the present invention, the discs of the invention of (1) are separated, and the same effects as those of the invention of (1) can be obtained, and it is advantageous in terms of production. . In (3) of the present invention, an extension is provided between the discs, and a spindle bolt is attached to the side of the extension, so that the disc is deformed into a dish shape and falls down, not the extension. The bolt mounting surface is not affected by deformation, and the fatigue strength of the bolt is improved. In the fourth aspect of the present invention, the disc is separated from the third aspect of the invention, and the same effect as the third aspect of the invention can be obtained and the production is advantageous. .

本発明の(5)では、後方軸端部の端面が円形状の同一面を形成し、この部分剛性も高まる。これにより運転中に両端面が圧縮や引張による曲げ変形力を受けても前方軸端部の取付周面と後方軸端部の端面が剛性が高い構造体となっているので、軸方向に対して絶えず垂直な面を保ち、スピンドルボルトの曲げを防止し、このためにボルトの疲労強度が向上する。   In (5) of the present invention, the end surface of the rear shaft end portion forms the same circular surface, and this partial rigidity is also increased. As a result, even if both end surfaces are subjected to bending deformation force due to compression or tension during operation, the mounting peripheral surface of the front shaft end and the end surface of the rear shaft end are highly rigid structures. It keeps the vertical surface constantly and prevents bending of the spindle bolt, which improves the fatigue strength of the bolt.

以下、本発明の実施の形態について図面に基づいて具体的に説明する。図1は本発明の実施の第1形態に係るガスタービンにおける圧縮機のスピンドルボルト取付構造を示す。図において、前方軸端部2と後方軸端部4との間には多数の円板82が軸方向に接して配置されている。これら前方軸端部2、後方軸端部4、多数の円板82はスピンドルボルト1とナット5により軸方向に締め付けられ、圧縮機の回転軸を構成している。   Embodiments of the present invention will be specifically described below with reference to the drawings. FIG. 1 shows a spindle bolt mounting structure of a compressor in a gas turbine according to a first embodiment of the present invention. In the figure, a large number of discs 82 are arranged in contact with each other between the front shaft end portion 2 and the rear shaft end portion 4 in the axial direction. The front shaft end 2, the rear shaft end 4, and a large number of disks 82 are tightened in the axial direction by the spindle bolt 1 and the nut 5 to constitute a rotating shaft of the compressor.

スピンドルボルト1のボルト頭の前方軸端部2への取付部は、円板2段分10,11を1つの塊として分離しない構成とし、スピンドルボルト1により、その後方に多数の円板82を締め付ける構成となっている。従って、前方軸端部2は一体成形されると共に、円板10,11との間には外周面に凹部13を設けてボルト取付面14が形成されている。又、この凹部13により円板10,11のトルクアームに相当する接触部を遮断している。又、ボルト穴は一体部分を円板11で貫通させ、ボルト取付面14にナットを設けている。   The mounting portion of the spindle bolt 1 to the front shaft end 2 of the bolt head is configured not to separate the two discs 10 and 11 as one lump, and the spindle bolt 1 allows a number of discs 82 to be placed behind it. It is configured to tighten. Accordingly, the front shaft end portion 2 is integrally formed, and the bolt mounting surface 14 is formed by providing the recess 13 on the outer peripheral surface between the discs 10 and 11. Further, the concave portion 13 blocks a contact portion corresponding to the torque arm of the discs 10 and 11. Further, the bolt hole has an integral part penetrated by the disk 11 and a nut is provided on the bolt mounting surface 14.

又、スピンドルボルト1の後端はナット5が装着され、前方軸端部2と後方軸端部4との間に多数の円板82を挟み込んで締め付けており、各円板82の隣り合う円板部分81同志が接触し、摩擦力により一体化している。   A nut 5 is attached to the rear end of the spindle bolt 1, and a large number of discs 82 are sandwiched between the front shaft end portion 2 and the rear shaft end portion 4 and tightened. The plate portions 81 are in contact with each other and integrated by frictional force.

上記構成の実施の第1形態のスピンドルボルト取付構造によれば、円板10と円板11との間に凹部13を受けることにより、皿形変形60は円板10側においてのみ起こり、円板11の側面はほとんど皿形に歪まない。又、前方軸端部2は一体構造であって、かつスピンドルボルト1の取付面14が2段分の円板10,11で形成されているので、ボルト頭の前方軸端部2の取付部構造の剛性が向上し、ボルト取付面14が軸に対して垂直な面を保つことになる。   According to the spindle bolt mounting structure of the first embodiment of the above configuration, by receiving the recess 13 between the disc 10 and the disc 11, the dish-shaped deformation 60 occurs only on the disc 10 side, and the disc The side of 11 is hardly distorted into a dish shape. Further, since the front shaft end portion 2 has an integral structure, and the mounting surface 14 of the spindle bolt 1 is formed by two stages of discs 10 and 11, the mounting portion of the front shaft end portion 2 of the bolt head. The rigidity of the structure is improved, and the bolt mounting surface 14 is kept perpendicular to the axis.

図2は図1における前方軸端部の拡大図であり、前述のように円板10と11を1つの塊とし、更に円板10と11との間には凹部13を設けた構成としたものであり、上記に説明した通りである。次に、図3に本発明の実施の第2形態に係るガスタービンのスピンドルボルト取付構造の断面図で図4と同様の前方軸端部の拡大図である。本実施の第2形態においては、図1の構成において、円板10と11とを一体物から接合面15で分離し、別体としたものであり、トルク伝達及び軸振動に関して軸の曲げ剛性上から許容されれば分割するものである。このような実施の第2形態においても、実施の第1形態と同様の効果が得られ、これに加えて、製作上有利となるものである。   FIG. 2 is an enlarged view of the front shaft end portion in FIG. 1. As described above, the disks 10 and 11 are formed as one lump, and a recess 13 is provided between the disks 10 and 11 as described above. As described above. Next, FIG. 3 is a sectional view of a spindle bolt mounting structure for a gas turbine according to a second embodiment of the present invention, and is an enlarged view of a front shaft end portion similar to FIG. In the second embodiment, the discs 10 and 11 are separated from the integrated member by the joint surface 15 in the configuration of FIG. 1 and are separated, and the bending rigidity of the shaft with respect to torque transmission and shaft vibration. If allowed from above, it is divided. In the second embodiment, the same effects as those of the first embodiment can be obtained, and in addition to this, it is advantageous in manufacturing.

図4は本発明の実施の第3形態に係る圧縮機スピンドルボルトの取付構造の前方軸端部の拡大断面図であり、図1に対応する図である。本実施の第3形態においては円板10と11との間には延長部20を設け、ボルト取付面20aを形成させ、スピンドルボルト1をボルト取付面20aに当接して取付けるようにし、円板10側面には直接取付けないようにした構造であり、その他は実施の第1形態と同じである。このような構造によれば、実施の第1形態と同様の効果を有し、これに加え、ナット取付面20aは円板10の変形を支える役目をしていないので、円板10が変形して倒れるのは、変形61として図示しているように、ボルト1の外側の厚さの薄い部分で起こり、ボルト取付面20aには変形を及ぼさない。   FIG. 4 is an enlarged cross-sectional view of the front shaft end portion of the compressor spindle bolt mounting structure according to the third embodiment of the present invention, corresponding to FIG. In the third embodiment, an extension 20 is provided between the disks 10 and 11 to form a bolt mounting surface 20a, and the spindle bolt 1 is mounted in contact with the bolt mounting surface 20a. The structure is such that it is not directly attached to the 10 side surfaces, and the others are the same as in the first embodiment. According to such a structure, the same effect as in the first embodiment is obtained, and in addition to this, the nut mounting surface 20a does not play a role of supporting the deformation of the disk 10, so that the disk 10 is deformed. As shown as the deformation 61, the collapse occurs at a thin portion outside the bolt 1, and the bolt mounting surface 20a is not deformed.

図5は本発明の実施の第4形態に係る圧縮機のスピンドルボルト取付構造の前方軸端部の拡大断面図であり、本実施の第4形態では、図4に示す実施の第3形態において、円板10と11とを一体物から接合面16で分離し、別体としたものであり、その他の構成は図4と同じである。このような構成としても、上記実施の第3形態と同様の効果を得ることができ、かつ、製作上有利となるものである。   FIG. 5 is an enlarged sectional view of a front shaft end portion of a spindle bolt mounting structure for a compressor according to a fourth embodiment of the present invention. In the fourth embodiment, the third embodiment shown in FIG. The discs 10 and 11 are separated from the integrated member at the joint surface 16 and separated from each other, and the other configurations are the same as those in FIG. Even with such a configuration, the same effects as those of the third embodiment can be obtained, and this is advantageous in manufacturing.

図6は本発明の実施の第5形態に係る圧縮機のスピンドルボルト取付構造の後方軸端部の拡大断面図であり、上記した実施の第1〜第4形態の前方軸端部の構造のいずれかと組合せて適用されるか、又は本構造のみ適用しても良いものである。図において後方軸端部4は、スピンドルボルト貫通部31aと、その下方の補強部31bとからなり、端部全面がナット接触面31cを形成する一体構造となっており、後方軸端部3としての全体の剛性が従来よりも大きくなるような構造となっている。これによりスピンドルボルト1の曲げが防止され、疲労強度上有利となる。   FIG. 6 is an enlarged sectional view of a rear shaft end portion of a spindle bolt mounting structure for a compressor according to a fifth embodiment of the present invention, and shows the structure of the front shaft end portion of the first to fourth embodiments described above. It may be applied in combination with either, or only this structure may be applied. In the drawing, the rear shaft end portion 4 is composed of a spindle bolt penetrating portion 31a and a reinforcing portion 31b below the spindle bolt penetrating portion 31a, and the entire end portion has an integral structure forming a nut contact surface 31c. It has a structure in which the overall rigidity is greater than in the prior art. This prevents bending of the spindle bolt 1, which is advantageous in terms of fatigue strength.

本発明の実施の第1形態に係る圧縮機のスピンドルボルト取付構造を示す断面図である。It is sectional drawing which shows the spindle bolt attachment structure of the compressor which concerns on 1st Embodiment of this invention. 図における前方軸端部の拡大図である。It is an enlarged view of the front-axis end part in a figure. 本発明の実施の第2形態に係る取付構造の前方軸端部の断面図である。It is sectional drawing of the front-shaft end part of the attachment structure which concerns on 2nd Embodiment of this invention. 本発明の実施の第3形態に係る取付構造の前方軸端部の断面図である。It is sectional drawing of the front-shaft edge part of the attachment structure which concerns on 3rd Embodiment of this invention. 本発明の実施の第4形態に係る取付構造の前方軸端部の断面図である。It is sectional drawing of the front-shaft end part of the attachment structure which concerns on 4th Embodiment of this invention. 本発明の実施の第5形態に係る取付構造の後方軸端部の断面図である。It is sectional drawing of the rear-axis end part of the attachment structure which concerns on 5th Embodiment of this invention. 従来のガスタービンの圧縮機の一般的な断面図である。It is a general sectional view of a compressor of a conventional gas turbine. 図7におけるA部の拡大断面図である。It is an expanded sectional view of the A section in FIG.

符号の説明Explanation of symbols

1 スピンドルボルト
2 前方軸端部
4 後方軸端部
9,13 凹部
10,11 円板
14 ボルト取付面
15,16 接合面
20 延長部
31a スピンドルボルト貫通部
31b 接触面
31c 接触面
60,61 変形
DESCRIPTION OF SYMBOLS 1 Spindle bolt 2 Front shaft end part 4 Back shaft end part 9,13 Recessed part 10,11 Disk 14 Bolt attachment surface 15,16 Joining surface 20 Extension part 31a Spindle bolt penetration part 31b Contact surface 31c Contact surface 60, 61 Deformation

Claims (5)

ガスタービン圧縮機の回転体を構成する前方軸端部、軸方向に多重に連接し軸方向に翼を配設するための複数の円板、後方軸端部、及び前記前方軸端部と複数の円板及び後方軸端部を軸方向に貫通し締付ける複数のスピンドルボルトからなる圧縮機のスピンドルボルト取付構造において、前記前方軸端部には前記複数のスピンドルボルトが円周状に配設されボルト頭が接する取付周面を有し、同取付周面から前記スピンドルボルトが貫通する後方側には少なくとも2段分の円板を一体構造とし、同2段の円板間には外周側に凹部を形成することを特徴とする圧縮機のスピンドルボルト取付構造。   A front shaft end portion constituting a rotating body of a gas turbine compressor, a plurality of disks for connecting in multiple directions in the axial direction and arranging blades in the axial direction, a rear shaft end portion, and a plurality of the front shaft end portions and the plurality In the spindle bolt mounting structure for a compressor comprising a plurality of spindle bolts that penetrate and tighten the disc and the rear shaft end portion in the axial direction, the plurality of spindle bolts are arranged circumferentially at the front shaft end portion. It has a mounting peripheral surface with which the bolt head contacts, and at least a two-stage disk is integrated on the rear side through which the spindle bolt penetrates from the mounting peripheral surface. A structure for attaching a spindle bolt of a compressor, wherein a recess is formed. 前記2段分の円板は一体構造に代えて、それぞれ分離した構造とし接合してなることを特徴とする請求項1記載の圧縮機のスピンドルボルト取付構造。   2. The spindle bolt mounting structure for a compressor according to claim 1, wherein the two-stage discs are joined as separate structures instead of an integrated structure. 前記2段分の円板間の凹部には円周状に段状の延長部を形成し、同延長部の側面には前記スピンドルボルトの頭が当接して取付けられることを特徴とする請求項1記載の圧縮機のスピンドルボルト取付構造。   The concave portion between the two-stage discs is formed with a step-like extension portion in a circumferential shape, and a head of the spindle bolt is abutted and attached to a side surface of the extension portion. The spindle bolt mounting structure of the compressor according to 1. 前記2段分の円板は前記凹部において分離され接合した構造であることを特徴とする請求項3記載の圧縮機のスピンドルボルト取付構造。   4. The spindle bolt mounting structure for a compressor according to claim 3, wherein the two-stage discs are separated and joined in the recess. 前記後方軸端部は一体の円形状構造体であり、前記スピンドルボルトの貫通穴開口部は軸方向と直交する同一平面を形成することを特徴とする請求項1記載の圧縮機のスピンドルボルト。   The spindle bolt of the compressor according to claim 1, wherein the rear shaft end portion is an integral circular structure, and the through-hole opening of the spindle bolt forms a same plane orthogonal to the axial direction.
JP2008323189A 2008-12-19 2008-12-19 Compressor spindle bolt mounting structure Expired - Lifetime JP4969562B2 (en)

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JPS58146001U (en) * 1982-03-26 1983-10-01 株式会社日立製作所 disk coupling rotor
JPS6228001U (en) * 1985-08-05 1987-02-20
JPS62267598A (en) * 1986-05-16 1987-11-20 Hitachi Ltd Rotor blade for gas turbine compressor
JPH0383398U (en) * 1989-12-15 1991-08-23
JPH0988504A (en) * 1995-09-22 1997-03-31 Hitachi Ltd Compressor and gas turbine
JPH108904A (en) * 1996-06-19 1998-01-13 Hitachi Ltd Gas turbine disk, and gas turbine
JP2001003702A (en) * 1999-06-16 2001-01-09 Mitsubishi Heavy Ind Ltd Gas turbine rotor
JP2003113797A (en) * 2001-10-03 2003-04-18 Mitsubishi Heavy Ind Ltd Assembly type rotor

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS57210103A (en) * 1981-06-17 1982-12-23 Hitachi Ltd Stacked rotor
JPS58146001U (en) * 1982-03-26 1983-10-01 株式会社日立製作所 disk coupling rotor
JPS6228001U (en) * 1985-08-05 1987-02-20
JPS62267598A (en) * 1986-05-16 1987-11-20 Hitachi Ltd Rotor blade for gas turbine compressor
JPH0383398U (en) * 1989-12-15 1991-08-23
JPH0988504A (en) * 1995-09-22 1997-03-31 Hitachi Ltd Compressor and gas turbine
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JP2001003702A (en) * 1999-06-16 2001-01-09 Mitsubishi Heavy Ind Ltd Gas turbine rotor
JP2003113797A (en) * 2001-10-03 2003-04-18 Mitsubishi Heavy Ind Ltd Assembly type rotor

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