JP2014047692A - Axial flow turbo machine - Google Patents
Axial flow turbo machine Download PDFInfo
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本発明は、軸流ターボ機械に関する。 The present invention relates to an axial flow turbomachine.
軸流ターボ機械は、静翼と、静翼の下流側に配置された動翼からなる段落で構成された構造となっている。 The axial-flow turbomachine has a structure composed of a stationary blade and a paragraph composed of a moving blade disposed on the downstream side of the stationary blade.
静翼の上流側から流入した作動流体は、静翼間を通過して、所定の流出角で動翼上流側へと流れる。その際に、静翼後縁より下流の領域では、静翼の翼面で発達した境界層の影響により、作動流体の速度が遅い領域いわゆる静翼後流が形成される。 The working fluid flowing in from the upstream side of the stationary blade passes between the stationary blades and flows to the upstream side of the moving blade at a predetermined outflow angle. At that time, in the region downstream from the trailing edge of the stationary blade, a region where the working fluid is slow, so-called a stationary blade wake, is formed due to the influence of the boundary layer developed on the blade surface of the stationary blade.
静翼後流の数は後流を形成する静翼本数と一致するため、動翼がタービン軸周りを一周する間に、動翼の上流側にある静翼本数分だけ静翼後流を通過することになる。このとき動翼は、回転周波数と静翼本数との積で表される静翼通過周波数の流体励振力によって励振される。 Since the number of stator blade wakes matches the number of stator blades that form the wake, the rotor blades pass through the stator blade wakes by the number of stator blades upstream of the rotor blades as they move around the turbine axis. Will do. At this time, the moving blade is excited by a fluid exciting force having a stationary blade passing frequency represented by the product of the rotational frequency and the number of stationary blades.
静翼通過周波数と動翼固有振動数が一致した場合、共振により動翼に過大な変動応力が発生し、動翼が疲労破壊する可能性がある。従来では、かかる動翼の疲労破壊を防止するため、定格回転速度における静翼通過周波数と動翼固有振動数を離調させる設計を行う場合がある。 When the stationary blade passing frequency and the moving blade natural frequency match, excessive fluctuation stress is generated in the moving blade due to resonance, which may cause fatigue failure of the moving blade. Conventionally, in order to prevent fatigue failure of such a moving blade, there is a case where a design is made to detune the stationary blade passing frequency and the moving blade natural frequency at the rated rotational speed.
離調設計では、静翼本数の調整により静翼通過周波数を変更して、動翼固有振動数と一致しないようにするため、設計時に選択できる静翼本数が限定されるといった問題がある。 In the detuning design, there is a problem that the number of stationary blades that can be selected at the time of design is limited because the stationary blade passing frequency is changed by adjusting the number of stationary blades so as not to coincide with the natural frequency of the moving blade.
また、静翼通過周波数と動翼固有振動数が一致した場合でも、動翼が疲労破壊しないように、充分な耐振強度を有した動翼を採用するため、翼幅の増大による材料費の増大や性能向上の妨げになるといった問題がある。 In addition, even if the stationary blade passage frequency and the natural frequency of the moving blade match, the moving blade has sufficient vibration resistance so that the moving blade will not be damaged by fatigue. And there is a problem that hinders performance improvement.
以上のように、軸流ターボ機械の段落設計において、静翼通過周波数で動翼に作用する励振力が、材料費の増大や性能向上の妨げになるため、励振力の要因となる静翼後流すなわち速度欠損を低減することが望まれている。 As described above, in the stage design of an axial-flow turbomachine, the excitation force acting on the moving blade at the stationary blade passing frequency hinders increase in material cost and performance improvement. It is desirable to reduce flow or velocity deficits.
本技術分野の従来技術として、特開２００７−２７８１８７号公報（特許文献１）がある。この公報には、翼の上流側から下流側に流れる流体の一部が流体流路を介して速度欠損領域に噴出される。このため、後流を弱めることができ騒音及び振動を低減させることが可能となると記載されている。 As a prior art in this technical field, there is JP-A-2007-278187 (Patent Document 1). In this publication, a part of the fluid flowing from the upstream side to the downstream side of the blade is ejected to the velocity deficient region through the fluid flow path. For this reason, it is described that the wake can be weakened and noise and vibration can be reduced.
一般的な蒸気タービンは、静翼と、静翼の下流側に配置された動翼からなる段落が、軸流方向に複数並んだ構造となっており、動翼に流入する流れは、静翼を通過した流れとなるため、静翼を通過する際に生じる速度欠損を含んだ流れが動翼に流入する。 A general steam turbine has a structure in which a plurality of stages including a stationary blade and a moving blade arranged on the downstream side of the stationary blade are arranged in the axial flow direction. Therefore, the flow including velocity deficiency generated when passing through the stationary blade flows into the moving blade.
そのため、速度欠損が大きい場合、動翼に流入する流れの速度変動が大きくなり、動翼に作用する励振力が増大する一因となるため、速度欠損を低減する必要がある。 For this reason, when the speed deficit is large, the speed fluctuation of the flow flowing into the moving blade increases, and the excitation force acting on the moving blade increases, so it is necessary to reduce the speed deficit.
前記特許文献１では、速度欠損領域に流体を噴出するための流体流路が翼の正圧面から負圧面あるいは後縁に導通され形成されていることを特徴とすると記載されている。 In Patent Document 1, it is described that a fluid flow path for ejecting a fluid to a velocity deficient region is formed to be conducted from a pressure surface of a blade to a suction surface or a trailing edge.
しかしながら、速度欠損領域へ噴出する流れを翼の正圧面から吸い込む構造では、翼面上に吸い込み孔を設置しなければならず、吸い込み孔周りの流れ場が乱れて、吸い込み孔が無い構造に比べて効率が低下する可能性がある。 However, in the structure where the flow jetted into the velocity deficit region is sucked from the pressure surface of the blade, the suction hole must be installed on the blade surface, and the flow field around the suction hole is disturbed, compared to the structure without the suction hole. Efficiency may be reduced.
また、一般的な蒸気タービンの高中圧段では、作動流体の圧力が高く、高強度の翼が採用されている。そのため、前記特許文献１に示してあるように、翼面に複数の孔を設置する構造では、クラックなどの問題が生じる可能性があり強度上好ましくないため、より高強度の翼を採用する必要があり、材料費の増大や性能向上の妨げになるといった可能性がある。 Moreover, in the high and medium pressure stage of a general steam turbine, the pressure of the working fluid is high, and high-strength blades are employed. Therefore, as shown in Patent Document 1, the structure in which a plurality of holes are installed on the blade surface may cause problems such as cracks, which is not preferable in terms of strength. Therefore, it is necessary to employ a higher strength blade. There is a possibility that the material cost will increase and the performance will be hindered.
そこで本発明は、翼面に吸い込み孔を設置しない簡単な構造で、静翼後流の速度欠損を回復させ、ある特定の静翼通過周波数で動翼に作用する静翼後流に起因する励振力を低減し、静翼通過周波数と動翼固有振動数が一致した場合でも共振応答を小さくできる軸流ターボ機械の静翼構造を提供する。 Therefore, the present invention has a simple structure in which no suction hole is provided on the blade surface, recovers the speed deficit of the stationary blade wake, and excites due to the stationary blade wake acting on the moving blade at a certain stationary blade passing frequency. Provided is a stationary blade structure for an axial-flow turbomachine capable of reducing the resonance and reducing the resonance response even when the stationary blade passage frequency and the moving blade natural frequency coincide with each other.
上記課題を解決するため、本発明は、ロータと、該ロータの外周側に設けられた円環状構造体と、該円環状構造体の内周側に固定された静翼と、該静翼の作動流体流れ方向下流側でロータに固定された動翼とを備える軸流ターボ機械において、円環状構造体は、作動流体の一部を、静翼をバイパスして円環状構造体の内周側壁面の静翼後縁部下流から作動流体の静翼流出方向に向かって作動流体主流中に吹き出させる流路を備える。 In order to solve the above problems, the present invention provides a rotor, an annular structure provided on the outer peripheral side of the rotor, a stationary blade fixed on the inner peripheral side of the annular structure, In an axial-flow turbomachine comprising a moving blade fixed to a rotor on the downstream side in the working fluid flow direction, the annular structure is configured such that a part of the working fluid bypasses the stationary blade and the inner peripheral side of the annular structure. A flow path is provided for blowing out into the working fluid main flow from the downstream of the trailing edge of the stationary blade on the wall surface toward the stationary blade outflow direction of the working fluid.
本発明によれば、簡単な構造で、静翼下流側に形成される静翼後流の速度欠損を回復できるため、静翼通過周波数で動翼に作用する速度欠損に起因する励振力を低減し、静翼通過周波数と動翼固有振動数が一致した場合でも共振応答を小さくできる軸流ターボ機械の静翼構造を提供することができる。 According to the present invention, since the speed deficit of the stationary blade wake formed on the downstream side of the stationary blade can be recovered with a simple structure, the excitation force due to the velocity deficiency acting on the moving blade at the stationary blade passing frequency is reduced. In addition, it is possible to provide a stationary blade structure of an axial-flow turbomachine that can reduce the resonance response even when the stationary blade passing frequency and the moving blade natural frequency coincide with each other.
上記した以外の課題、構成及び効果は、以下の実施形態の説明により明らかにされる。 Problems, configurations, and effects other than those described above will be clarified by the following description of embodiments.
以下、本発明の実施例について図面を用いて説明する。なお、以下に説明する実施例は、軸流ターボ機械の一例として蒸気タービンに本発明を適用した例であるが、本発明は、蒸気タービンに限らず、ガスタービンや圧縮機の段落構造にも適用可能である。 Embodiments of the present invention will be described below with reference to the drawings. In addition, although the Example described below is an example which applied this invention to the steam turbine as an example of an axial-flow turbomachine, this invention is not limited to a steam turbine but also to the paragraph structure of a gas turbine or a compressor. Applicable.
本発明の第１の実施例について説明する。まず初めに、本発明が適用される蒸気タービンの一例について説明する。 A first embodiment of the present invention will be described. First, an example of a steam turbine to which the present invention is applied will be described.
図１は、軸流ターボ機械の一例である蒸気タービンの段落構造の例である。図１において、１はダイアフラム外輪、２はダイアフラム内輪、３は静翼、４は動翼、５はロータ、６はシュラウドカバー、７はロータ５の中心軸、２０で示した矢印は作動流体である蒸気の主流方向を各々示す。なお、方向の定義として、図面左から右に向かって軸方向、下から上に向かって径方向、紙面手前から奥に向かって周方向となっている。 FIG. 1 is an example of a paragraph structure of a steam turbine that is an example of an axial-flow turbomachine. In FIG. 1, 1 is a diaphragm outer ring, 2 is a diaphragm inner ring, 3 is a stationary blade, 4 is a moving blade, 5 is a rotor, 6 is a shroud cover, 7 is a central axis of the rotor 5, and an arrow indicated by 20 is a working fluid. Each direction of the main flow of a certain steam is shown. The direction is defined as an axial direction from the left to the right in the drawing, a radial direction from the bottom to the top, and a circumferential direction from the front to the back of the page.
一般的な蒸気タービンは、円環状に組み立てられた円環状構造体であるダイアフラム外輪１とダイアフラム内輪２との間に、周方向に複数枚の静翼３を固定して環状流路を形成する静翼列と、静翼列の主流の流れ方向下流側に、回転体であるロータ５のディスク部に周方向に複数枚の動翼４を固定して形成される動翼列とを一列ずつ組み合わせた段落が、軸流方向に複数並んだ構造となっている。なお、動翼４の外周側は、一般的にシュラウドカバー６が設けられ、隣接する翼同士がシュラウドカバー６により連結されている。また、ダイアフラム外輪１は外周側をケーシング（図示せず）に固定されている。蒸気タービンのなかにはダイアフラム外輪１を有しない場合もあるが、その場合においても円環状構造体としてのケーシング等によって静翼３が支持される。 A general steam turbine forms an annular flow path by fixing a plurality of stationary blades 3 in a circumferential direction between a diaphragm outer ring 1 and a diaphragm inner ring 2 which are annular structures assembled in an annular shape. A stationary blade row and a moving blade row formed by fixing a plurality of blades 4 in the circumferential direction to the disk portion of the rotor 5 that is a rotating body, one by one on the downstream side in the mainstream flow direction of the stationary blade row. The combined paragraph has a structure in which a plurality of paragraphs are arranged in the axial direction. In addition, the outer peripheral side of the moving blade 4 is generally provided with a shroud cover 6, and adjacent blades are connected by the shroud cover 6. The outer peripheral side of the diaphragm outer ring 1 is fixed to a casing (not shown). Some steam turbines may not have the diaphragm outer ring 1. In this case, the stationary blade 3 is supported by a casing or the like as an annular structure.
静翼３は、静翼３の流れ方向上流側より流入する蒸気主流を整流し、圧力を速度に変換する役割を果たしており、静翼３を通過した主流のエネルギは、動翼４によって回転エネルギに変換され、ロータ５を回転させる。ロータ５は図示しない発電機に連結されており、発電機を回転させることによって発電する。 The stationary blade 3 rectifies the main steam flow flowing in from the upstream side of the stationary blade 3 in the flow direction, and converts pressure into velocity. The energy of the main flow that has passed through the stationary blade 3 is rotated by the rotating blade 4. And the rotor 5 is rotated. The rotor 5 is connected to a generator (not shown), and generates electricity by rotating the generator.
図２は、蒸気タービンの静翼列を径方向から見た展開図の例である。図２では、軸方向上流側より流入した主流が、前記静翼列より所定の角度で流出するように、静翼３は全周３６０°に渡って周方向に均一に配置されている。つまり、各静翼３の下流側に形成される速度の遅い領域である静翼後流２１も、全周に渡って静翼列の配置間隔で動翼４に流入する。 FIG. 2 is an example of a development view in which the stationary blade row of the steam turbine is viewed from the radial direction. In FIG. 2, the stationary blade 3 is uniformly arranged in the circumferential direction over the entire circumference of 360 ° so that the main flow flowing in from the upstream side in the axial direction flows out from the stationary blade row at a predetermined angle. That is, the stationary blade wake 21, which is a low speed region formed on the downstream side of each stationary blade 3, also flows into the moving blade 4 at intervals of the stationary blade rows over the entire circumference.
ここで、静翼後流２１の速度欠損が小さい場合には速度変動が小さくなるため、動翼に流入する主流の速度変動も小さくなる。つまり、主流の速度変動に起因する動翼に作用する励振力も小さくなる。この速度変動の周波数は、静翼後流２１を通過する周波数つまり静翼通過周波数であるため、速度欠損を小さくすることで静翼通過周波数の励振力を低減できるといえる。 Here, when the speed deficit of the stationary blade wake 21 is small, the speed variation is small, and thus the main flow velocity variation flowing into the moving blade is also small. That is, the excitation force acting on the moving blade due to the mainstream speed fluctuation is also reduced. Since the frequency of this speed fluctuation is the frequency that passes through the stationary blade wake 21, that is, the stationary blade passage frequency, it can be said that the excitation force of the stationary blade passage frequency can be reduced by reducing the velocity deficit.
そこで、静翼通過周波数での励振力を低減できる、本実施例に係る蒸気タービンの段落構造について以下に説明する。 Therefore, the paragraph structure of the steam turbine according to the present embodiment that can reduce the excitation force at the stationary blade passing frequency will be described below.
図３は、本実施例の段落構造を示す例である。図３に示すように、本実施例はダイアフラム外輪１に、内周側壁面８の静翼後縁部下流から、作動流体である蒸気の一部を蒸気主流の静翼流出方向に向かって蒸気主流中に吹き出させる流路を備える。この流路は、ダイアフラム外輪１の作動流体流れ方向上流側を向いた上流側壁面９に設けた吸い込み孔１１と、ダイアフラム外輪１の内周側壁面８の静翼後縁部下流に設置した吹き出し孔１３と、吸い込み孔１１より取り込んだ主流の一部である吸い込み流れ２２を、静翼３をバイパスして吹き出し流れ２３として吹き出し孔へ導くバイパス流路１０とからなる。 FIG. 3 is an example showing the paragraph structure of this embodiment. As shown in FIG. 3, in this embodiment, a part of the steam, which is a working fluid, is applied to the diaphragm outer ring 1 from the downstream of the rear edge of the stationary blade on the inner peripheral side wall 8 toward the stationary blade flow direction of the main steam. A flow path is provided for blowing into the main stream. This flow path includes a suction hole 11 provided in the upstream side wall surface 9 facing the upstream side in the working fluid flow direction of the diaphragm outer ring 1, and a blowout installed downstream of the stationary blade trailing edge of the inner peripheral side wall surface 8 of the diaphragm outer ring 1. It consists of a bypass passage 10 that guides the suction flow 22, which is a part of the main flow taken in from the suction hole 11, to the blow-out hole as a blow-off flow 23 by bypassing the stationary blade 3.
ここで、ダイアフラム外輪１に吸い込み孔１１を設置して流れを吸い込む構造の方が、静翼３の翼面上から流れを吸い込む構造に比べて、静翼３周りの流れ場を乱さないため、効率が低下しないといった利点がある。 Here, the structure in which the suction hole 11 is installed in the diaphragm outer ring 1 and the flow is sucked does not disturb the flow field around the stationary blade 3 compared to the structure in which the flow is sucked from the blade surface of the stationary blade 3. There is an advantage that efficiency does not decrease.
吹き出し孔１３より吹き出す流れ２３は、速度欠損を効率良く回復させるため、前記静翼列より下流側へ流出する主流、または前記静翼列に起因する下流側の速度欠損領域の方向と同方向に吹き出す方が望ましい。しかしながら、必ずしも同方向とせずとも、静翼３の流出角±５°以内の角度で吹き出せば良い。 The flow 23 blown out from the blowout holes 13 is in the same direction as the direction of the main flow flowing out downstream from the stationary blade row or the downstream velocity missing region caused by the stationary blade row in order to efficiently recover the velocity loss. It is better to blow out. However, it does not necessarily have to be in the same direction, but it may be blown out at an angle within ± 5 ° of the stationary blade 3.
また、図３に示すように吹き出し孔１３の設置位置は、ダイアフラム外輪１の内周側の流路に接した内周側壁面８で、且つ静翼３の後縁より下流側に設置することが望ましい。これは、静翼３の後縁より上流側に設置すると、速度欠損領域でない主流に流れを吹き出すことになり、主流が乱れて効率低下の要因となる可能性があるためである。 Further, as shown in FIG. 3, the blowing hole 13 is installed on the inner peripheral side wall surface 8 in contact with the flow path on the inner peripheral side of the diaphragm outer ring 1 and on the downstream side from the rear edge of the stationary blade 3. Is desirable. This is because if installed upstream from the trailing edge of the stationary blade 3, the flow is blown out into the main flow that is not in the velocity deficit region, which may disturb the main flow and cause a reduction in efficiency.
さらに、吹き出し孔１３の設置位置は、静翼３の後縁に近い位置であることが望ましい。これは、静翼３の後縁より下流側に向かうにつれ、速度欠損領域の幅が広がるため、速度欠損領域の幅が小さい静翼３の後縁に近い領域で流れを吹き出した方が、効率よく速度欠損を回復できるためである。 Furthermore, the installation position of the blowout hole 13 is desirably a position close to the rear edge of the stationary blade 3. This is because the speed deficit region increases in width toward the downstream side from the trailing edge of the stationary blade 3, so that it is more efficient to blow out the flow in a region near the rear edge of the stationary blade 3 where the width of the velocity deficient region is small. This is because the speed deficit can be recovered well.
バイパス流路１０は、製造上できるだけ直線であることが望ましいため、吸い込み孔１１より吹き出し部１２までをダイアフラム外輪１内で貫通させ、吹き出し部１２はダイアフラム外輪１とは別構造としている。 Since it is desirable that the bypass flow path 10 be as straight as possible in manufacturing, the portion from the suction hole 11 to the blowing portion 12 is penetrated in the diaphragm outer ring 1, and the blowing portion 12 has a different structure from the diaphragm outer ring 1.
図４に示すように吹き出し部１２は、ダイアフラム外輪１とは別体で構成され、ダイアフラム外輪１の内周側壁面８の各静翼後縁部の下流に取り付けられる。吹き出し部１２は、バイパス流路１０に接続するバイパス接続孔１６と、バイパス接続孔１６よりも半径方向内周側に位置し、主流に面する壁面に設けられた吹き出し孔１３と、バイパス接続孔１６と吹き出し孔１３とを結び、バイパス接続孔１６を通過した蒸気を下方の吹き出し孔１３に向かってに噴出させる流路を内部に有する。なお、図４に示すように、別構造である吹き出し部１２とバイパス流路１０の接続を容易にするため、吹き出し部１２のバイパス流路接続部１６は、バイパス流路１０よりも大きい取り込み口となることが望ましい。 As shown in FIG. 4, the blowing portion 12 is configured separately from the diaphragm outer ring 1 and is attached downstream of each stationary blade rear edge portion of the inner peripheral side wall surface 8 of the diaphragm outer ring 1. The blowout portion 12 is connected to the bypass flow path 10, the blowout hole 13 provided on the wall surface facing the mainstream, and the bypass connection hole, located on the radially inner peripheral side of the bypass connection hole 16. 16 and the blowing hole 13 are connected to each other, and a flow path is provided inside to allow the vapor that has passed through the bypass connection hole 16 to be blown out toward the lower blowing hole 13. As shown in FIG. 4, in order to facilitate the connection between the blowing section 12 and the bypass flow path 10 which are different structures, the bypass flow path connecting section 16 of the blowing section 12 has a larger intake port than the bypass flow path 10. It is desirable that
吸い込み孔１１、バイパス流路１０、および吹き出し部１２内の流路は、吹き出し部１２をダイアフラム外輪１に取り付けた際、半径方向からみて吸い込み孔１１からバイパス流路１０、吹き出し孔１３まで、静翼流出角に沿って傾斜した直線状流路を構成するように形成する。またバイパス流路１０はタービン軸に平行に沿って形成し、吹き出し部12内の流路で下方に傾斜させる。 The suction holes 11, the bypass flow paths 10, and the flow paths in the blow-off section 12 are static when the blow-off section 12 is attached to the diaphragm outer ring 1, from the suction holes 11 to the bypass flow paths 10 and the blow-out holes 13 when viewed from the radial direction. It forms so that the linear flow path inclined along the blade outflow angle may be comprised. The bypass channel 10 is formed parallel to the turbine axis, and is inclined downward in the channel in the blowing portion 12.
このように吹き出し部１２を別構造とすることで、バイパス流路１０から吹き出し孔１３への流路の接続を容易にしている。 Thus, by making the blowing part 12 into another structure, the connection of the flow path from the bypass flow path 10 to the blowing hole 13 is facilitated.
以上のように、本実施例では、吹き出し部１２をダイアフラム外輪１とは別構造としているが、バイパス流路１０と吹き出し孔１３を容易に貫通できる場合には、吹き出し部１２をダイアフラム外輪１と別構造にする必要はなく、一体構造で製造しても良い。 As described above, in the present embodiment, the blowing portion 12 has a different structure from the diaphragm outer ring 1, but when the bypass passage 10 and the blowing hole 13 can be easily penetrated, the blowing portion 12 is connected to the diaphragm outer ring 1. It is not necessary to have a separate structure, and it may be manufactured as an integral structure.
図５は、本実施例の作用について説明した図である。本実施例の静翼構造では、ダイアフラム外輪１に固定した静翼３の下流側に設置した吹き出し孔１３より流れが吹き出す構造であるため、図５に示すように、静翼３の下流側に形成される静翼後流２１の先端側で、静翼後流２１と吹き出し流れ２３が混合するため、静翼後流２１の速度欠損が回復する。 FIG. 5 is a diagram for explaining the operation of this embodiment. In the stationary blade structure of the present embodiment, since the flow blows out from the blowing hole 13 installed on the downstream side of the stationary blade 3 fixed to the diaphragm outer ring 1, as shown in FIG. Since the stationary blade wake 21 and the blowout flow 23 are mixed on the leading end side of the formed stationary blade wake 21, the velocity defect of the stationary blade wake 21 is recovered.
つまり、本実施例では、静翼３の下流側に設置される動翼４へ流入する静翼後流２１において、静翼後流２１の速度欠損が小さくなるため速度変動が抑制され、速度変動に起因する励振力も小さくなる。 That is, in the present embodiment, in the stationary blade wake 21 flowing into the moving blade 4 installed on the downstream side of the stationary blade 3, the speed fluctuation of the stationary blade wake 21 is reduced, so that the speed variation is suppressed and the speed variation. The excitation force due to the is also reduced.
よって、本実施例により、静翼通過周波数で動翼４に作用する速度変動に起因する励振力が小さくなり、共振応答も低減できるといった効果がある。 Therefore, according to the present embodiment, there is an effect that the excitation force due to the speed fluctuation acting on the moving blade 4 at the stationary blade passing frequency is reduced, and the resonance response can be reduced.
また、動翼は根元で固定されているため、翼に作用する力のモーメントは、根元側と先端側に同じ大きさの励振力が作用した場合は、先端側の方が大きくなり振動応力に大きく影響する。本実施例のダイアフラム外輪１の内周側壁面８から吹き出す構造では、主に翼先端部の速度欠損を低減でき、翼先端側における速度欠損の低減効果が得られれば、振動低減効果は充分に期待できる。 In addition, since the rotor blade is fixed at the root, the moment of force acting on the blade is larger on the tip side when vibration forces of the same magnitude are applied to the root side and the tip side. A big influence. In the structure that blows out from the inner peripheral side wall surface 8 of the diaphragm outer ring 1 of this embodiment, the speed deficiency at the blade tip can be reduced mainly, and if the speed deficit reduction effect at the blade tip side can be obtained, the vibration reducing effect is sufficient. I can expect.
また従来技術のように、翼内部から吹き出す構造では、翼構造が複雑になるだけでなく、翼内部に空洞が多くなるので翼強度が低下する可能性があり、結局、頑丈な翼を採用しなければならず、励振力も大きくなるおそれがある。一方、本実施例によれば、翼内部を通す構造ではないので、従来の翼を使用することができ、簡単な構造で容易に製造することができる。 In addition, the structure that blows out from the inside of the blade as in the prior art not only complicates the blade structure but also increases the number of cavities inside the blade, which may reduce the blade strength. There is a risk that the excitation force will also increase. On the other hand, according to the present embodiment, since the structure does not pass through the inside of the blade, a conventional blade can be used, and it can be easily manufactured with a simple structure.
次に本発明の第２の実施例について説明する。図６は、吸い込み孔１１と吹き出し孔１３をバイパス流路１０で貫通させた構造の例を示す図である。ここで、先に第１の実施例で説明した構成と同等の構成については同一の符号を付して説明を省略し、先に説明した実施例と異なる箇所について説明をする。 Next, a second embodiment of the present invention will be described. FIG. 6 is a diagram illustrating an example of a structure in which the suction hole 11 and the blowout hole 13 are penetrated by the bypass channel 10. Here, the same components as those described in the first embodiment are denoted by the same reference numerals, description thereof is omitted, and portions different from those in the first embodiment are described.
図６では、静翼下流側の静翼ダイアフラム外輪１に設置した吹き出し孔１３より吹き出し流れ２３を主流部へ吹き出す構造となっているため、先に説明した実施例と同様の効果が得られる。 In FIG. 6, since the blowout flow 23 is blown out to the main flow portion from the blowout hole 13 installed in the stationary blade diaphragm outer ring 1 on the downstream side of the stationary blade, the same effect as the embodiment described above can be obtained.
しかし、実施例１と異なる点は、バイパス流路１０を吸い込み孔１１から吹き出し孔１３に向かって、半径方向外周側から内周側に向かって貫通させた構造となっている点である。 However, the difference from the first embodiment is that the bypass flow path 10 is structured to penetrate from the suction hole 11 toward the blowout hole 13 toward the inner peripheral side from the radially outer side.
実施例１では、バイパス流路１０と吹き出し部１２を別構造とすることで、バイパス流路から主流部への接続を容易に製造できる構造としたが、本実施例では、吸い込み孔１１から吹き出し孔１３までバイパス流路１０を貫通させているため、前記吹き出し部１２を別構造にする必要はなく、実施例１に比較して、さらに容易に製造できるといった利点がある。 In the first embodiment, the bypass flow path 10 and the blowout portion 12 have different structures, so that the connection from the bypass flow path to the main flow portion can be easily manufactured. However, in this embodiment, the blowout flow from the suction hole 11 Since the bypass passage 10 is penetrated to the hole 13, there is no need to make the blowing portion 12 a separate structure, and there is an advantage that it can be manufactured more easily than the first embodiment.
次に本発明の第３の実施例について説明する。図７は、吸い込み部１４を多孔板１５とした構造の例を示す図である。ここで、先に実施例で説明した構成と同等の構成については同一の符号を付して説明を省略し、先に説明した実施例と異なる箇所について説明をする。 Next, a third embodiment of the present invention will be described. FIG. 7 is a diagram illustrating an example of a structure in which the suction portion 14 is a perforated plate 15. Here, the same components as those described in the previous embodiment are denoted by the same reference numerals, the description thereof will be omitted, and different points from the above-described embodiment will be described.
図７では、静翼下流側のダイアフラム外輪１に設置した吹き出し孔１３より流れを主流部へ吹き出す構造となっているため、先に説明した実施例と同様の効果が得られる。 In FIG. 7, since the flow is blown out to the main flow portion from the blow-out hole 13 installed in the diaphragm outer ring 1 on the downstream side of the stationary blade, the same effect as the embodiment described above can be obtained.
しかし、先の実施例と異なる点は、吸い込み流れ２２を取り込む位置が、ダイアフラム外輪１の上流側を向いた面ではなく、ダイアフラム外輪１の内周側の静翼３より上流の流路に接した面に設置した構造となっている点である。 However, the difference from the previous embodiment is that the position where the suction flow 22 is taken in is not on the surface facing the upstream side of the diaphragm outer ring 1 but on the flow path upstream of the stationary blade 3 on the inner peripheral side of the diaphragm outer ring 1. It is the point where it has a structure installed on the surface.
ここで、吸い込み孔１１と吹き出し孔１３をバイパス流路１０で容易に接続できるようにするため、本実施例ではバイパス流路１０と吸込み部１４および吹き出し部１２を別構造としている。吹き出し部１２は実施例１と同様の構造を採用すれば良いが、実施例１で前述したが、バイパス流路１０と吹き出し孔１３を容易に貫通できる場合には、吹き出し部１２を静翼ダイアフラムと別構造にする必要はなく、一体構造で製造しても良い。なお、図７に図示した例では、吹き出し構造１２をダイアフラム外輪１と一体構造とした例を示している。 Here, in order to make it easy to connect the suction hole 11 and the blowout hole 13 by the bypass flow path 10, in this embodiment, the bypass flow path 10, the suction part 14 and the blowout part 12 have different structures. The blowing part 12 may have the same structure as that of the first embodiment, but as described above in the first embodiment, when the bypass channel 10 and the blowing hole 13 can be easily penetrated, the blowing part 12 is provided with a stationary blade diaphragm. It is not necessary to have a separate structure. In the example illustrated in FIG. 7, an example in which the blowing structure 12 is integrated with the diaphragm outer ring 1 is illustrated.
吸い込み部１４の構造は、図８に示したように実施例１のダイアフラム外輪１の上流側を向いた面に吸い込み孔１１を設置した構造と違い、ダイアフラム外輪１の内周側壁面８に凹部を形成して吸い込み部１４を設けている。吸い込み部１４に主流に接するように多孔板１５を設置し、吸い込み部１４に主流の一部が取り込まれる空洞部が形成される構造となっている。吸い込み部１４の設置位置は、静翼３の前縁部の上流側近傍付近にする。 Unlike the structure in which the suction hole 11 is provided on the surface facing the upstream side of the diaphragm outer ring 1 according to the first embodiment, the structure of the suction portion 14 is recessed on the inner peripheral side wall surface 8 of the diaphragm outer ring 1. The suction part 14 is provided. A perforated plate 15 is installed in the suction part 14 so as to be in contact with the main stream, and a cavity part in which a part of the main stream is taken into the suction part 14 is formed. The installation position of the suction portion 14 is in the vicinity of the upstream side of the front edge portion of the stationary blade 3.
多孔板１５には複数の吸い込み孔１１を設置し、吸い込み孔１１より吸い込み部１４内に流れを取り込み、バイパス流路接続部１７より、バイパス流路１０を介して、吹き出し孔１３に導き、流れを静翼３をバイパスして主流に吹き出す構造となる。 A plurality of suction holes 11 are provided in the perforated plate 15, a flow is taken into the suction part 14 from the suction hole 11, and the flow is guided from the bypass flow path connection part 17 to the blowout hole 13 via the bypass flow path 10. This is a structure that bypasses the stationary blade 3 and blows out the mainstream.
本実施例では、先の実施例に比較して、吸い込み部１４に多孔板１５を用いて、吸込み孔１１の位置をダイアフラム外輪１の上流側から主流部側にすることで、静翼３上流側のダイアフラム外輪１の壁面で発達した境界層を吸い込むことができ、静翼３へと流入する圧力損失が低減されるため、効率が向上するといった利点がある。 In this embodiment, compared with the previous embodiment, the perforated plate 15 is used for the suction portion 14 and the suction hole 11 is positioned upstream from the diaphragm outer ring 1 to the main flow portion side, so that the upstream of the stationary blade 3 Since the boundary layer developed on the wall surface of the diaphragm outer ring 1 on the side can be sucked and the pressure loss flowing into the stationary blade 3 is reduced, the efficiency is improved.
図９は、図８に示した吸い込み部１４を応用した一例を示す図である。図９では、吹き出し孔１３の設置位置が、静翼下流側のダイアフラム外輪１の内周側の流路に接した面に設置した先の実施例とは異なり、静翼３の後縁に設置した構造となっている。 FIG. 9 is a diagram illustrating an example in which the suction unit 14 illustrated in FIG. 8 is applied. In FIG. 9, the blowing hole 13 is installed at the rear edge of the stationary blade 3, unlike the previous embodiment in which the blowing hole 13 is installed on the surface in contact with the flow path on the inner peripheral side of the diaphragm outer ring 1 on the downstream side of the stationary blade. It has a structure.
図１０は、吸い込み部１４の設置位置をダイアフラム内輪２とした静翼構造の例を示す図である。先の実施例とは異なり、吸い込み部１４の設置位置をダイアフラム内輪２としているため、静翼３上流側のダイアフラム内輪２の壁面で発達した境界層を吸い込むことができ、静翼３の根元側の圧力損失を低減できるといった利点がある。 FIG. 10 is a diagram illustrating an example of a stationary blade structure in which the installation position of the suction portion 14 is the diaphragm inner ring 2. Unlike the previous embodiment, since the installation position of the suction portion 14 is the diaphragm inner ring 2, the boundary layer developed on the wall surface of the diaphragm inner ring 2 upstream of the stationary blade 3 can be sucked, and the root side of the stationary blade 3 There is an advantage that the pressure loss can be reduced.
以上、本発明の実施例を説明したが、本発明は上記した実施例に限定されるものではなく、様々な変形例が含まれる。例えば、実施例１の図３では、吸い込み孔１１がダイアフラム外輪１の上流側を向いた面に設置されているが、必ずしもダイアフラム外輪１に設置する必要はなく、ダイアフラム内輪２の上流側を向いた面に設置しても構わない。要は静翼３の下流側に形成される静翼後流２１に流れを吹き出す構造であれば効果がある。 As mentioned above, although the Example of this invention was described, this invention is not limited to an above-described Example, Various modifications are included. For example, in FIG. 3 of the first embodiment, the suction hole 11 is installed on the surface facing the upstream side of the diaphragm outer ring 1, but it is not always necessary to install the suction hole 11 on the diaphragm outer ring 1 and faces the upstream side of the diaphragm inner ring 2. You may install it on the surface. In short, any structure that blows the flow to the stationary blade wake 21 formed downstream of the stationary blade 3 is effective.
また、本発明の実施例では、ダイアフラム構造の蒸気タービンを例として説明したが、本発明はダイアフラム構造の蒸気タービンに限定されるものではなく、例えば組み立て式静翼の構造でも同様の効果が得られる。 In the embodiments of the present invention, the diaphragm-structured steam turbine has been described as an example. However, the present invention is not limited to the diaphragm-structured steam turbine. It is done.
１ ダイアフラム外輪
２ ダイアフラム内輪
３ 静翼
４ 動翼
５ ロータ
６ シュラウドカバー
７ ロータ中心軸
８ 内周側壁面
１０ バイパス流路
１１ 吸い込み孔
１２ 吹き出し部
１３ 吹き出し孔
１４ 吸い込み部
１５ 多孔板
１６ バイパス接続部
２１ 静翼後流
２２ 吸い込み流れ
２３ 吹き出し流れ
DESCRIPTION OF SYMBOLS 1 Diaphragm outer ring | wheel 2 Diaphragm inner ring | wheel 3 Stator blade 4 Rotor blade 5 Rotor 6 Shroud cover 7 Rotor center axis | shaft 8 Inner peripheral side wall surface 10 Bypass flow path 11 Suction hole 12 Outlet part 13 Outlet part 14 Inlet part 15 Perforated plate 16 Bypass connection part 21 Stator wing wake 22 Suction flow 23 Blowout flow
Claims (5)
前記円環状構造体は、作動流体の一部を、前記静翼をバイパスして円環状構造体の内周側壁面の静翼後縁部下流から作動流体の静翼流出方向に向かって作動流体主流中に吹き出させる流路を備えることを特徴とする軸流ターボ機械。 A rotor, an annular structure provided on the outer peripheral side of the rotor, a stationary blade fixed to the inner peripheral side of the annular structure, and a stationary blade fixed to the rotor on the downstream side in the working fluid flow direction of the stationary blade. An axial flow turbomachine comprising
In the annular structure, a part of the working fluid is bypassed from the stationary blade, and the working fluid flows from the downstream of the trailing edge of the stationary blade on the inner peripheral side wall surface of the annular structure toward the stationary blade outflow direction. An axial-flow turbomachine comprising a flow path for blowing out into a main stream.
前記流路は、前記静翼上流側に設けられ、作動流体主流の一部を吸込む吸込部と、
前記静翼の下流側に設けられ、吸込部で吸込んだ作動流体を作動流体主流に吹き出す
吹出部と、
前記吸込部で導入した作動流体を前記静翼をバイパスして前記吹出部に導くバイパス流路とを有し、
前記吸込部は、前記円環状構造体の上流側壁面に開口する吸込孔を有することを特徴とする軸流ターボ機械。 The axial-flow turbomachine according to claim 1,
The flow path is provided on the upstream side of the stationary blade, and a suction portion that sucks a part of the main working fluid,
A blow-off portion that is provided on the downstream side of the stationary blade, and blows out the working fluid sucked in the suction portion into the working fluid mainstream;
A bypass flow path for guiding the working fluid introduced in the suction section to the blowout section by bypassing the stationary blade,
The axial flow turbomachine according to claim 1, wherein the suction part has a suction hole that opens to an upstream side wall surface of the annular structure.
前記流路は、前記静翼上流側に設けられ、作動流体主流の一部を吸込む吸込部と、
前記静翼の下流側に設けられ、吸込部で吸込んだ作動流体を作動流体主流に吹き出す
吹出部と、
前記吸込部で導入した作動流体を前記静翼をバイパスして前記吹出部に導くバイパス流路とを有し、
前記吸込部は、前記円環状構造体の内周壁面の静翼前縁部上流側に開口する複数の吸込孔を有することを特徴とする軸流ターボ機械。 The axial-flow turbomachine according to claim 1,
The flow path is provided on the upstream side of the stationary blade, and a suction portion that sucks a part of the main working fluid,
A blow-off portion that is provided on the downstream side of the stationary blade, and blows out the working fluid sucked in the suction portion into the working fluid mainstream;
A bypass flow path for guiding the working fluid introduced in the suction section to the blowout section by bypassing the stationary blade,
The axial-flow turbomachine characterized in that the suction portion has a plurality of suction holes that open to the upstream side of the stationary blade front edge portion of the inner peripheral wall surface of the annular structure.
前記吹出部は、前記円環状構造体と別体として設けられていることを特徴とする軸流ターボ機械。 An axial-flow turbomachine according to any one of claims 1 to 3,
The blowout unit is provided as a separate body from the annular structure, and is an axial-flow turbomachine.
前記流路は、前記円環状構造体の上流側壁面に設けられ、作動流体主流の一部を吸込む吸込孔と、
前記円環状構造体の内周壁面の前記静翼後縁部下流に設けられ、吸込部で吸込んだ作動流体を作動流体主流に吹き出す吹出孔と、
前記吸込孔で導入した作動流体を前記静翼をバイパスして前記吹出孔に導くバイパス流路とを有し、
前記吸込孔、前記吹出孔、およびバイパス流路は、前記円環状構造体を貫通させた貫通孔で構成されていることを特徴とする軸流ターボ機械。 The axial-flow turbomachine according to claim 1,
The flow path is provided on the upstream side wall surface of the annular structure, and a suction hole for sucking a part of the main working fluid flow;
A blowout hole that is provided downstream of the stationary blade trailing edge of the inner peripheral wall surface of the annular structure and blows out the working fluid sucked in the suction portion into the working fluid mainstream,
A bypass flow path that bypasses the stationary blade and introduces the working fluid introduced through the suction hole to the outlet hole;
The axial-flow turbomachine characterized in that the suction hole, the blowout hole, and the bypass flow path are configured by through-holes that penetrate the annular structure.
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| JP2020505555A (en) * | 2017-02-02 | 2020-02-20 | ゼネラル・エレクトリック・カンパニイ | Turbine tip balance slit |
| WO2021020518A1 (en) * | 2019-07-31 | 2021-02-04 | 三菱パワー株式会社 | Axial flow turbine |
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