JP5725929B2 - gas turbine - Google Patents
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- JP5725929B2 JP5725929B2 JP2011075132A JP2011075132A JP5725929B2 JP 5725929 B2 JP5725929 B2 JP 5725929B2 JP 2011075132 A JP2011075132 A JP 2011075132A JP 2011075132 A JP2011075132 A JP 2011075132A JP 5725929 B2 JP5725929 B2 JP 5725929B2
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本発明は、ガスタービンに関し、特に、燃焼器の尾筒と静翼シュラウドとの接合部に関する。 The present invention relates to a gas turbine, and more particularly, to a joint portion between a combustor tail and a stationary blade shroud.
ガスタービンの燃焼器の尾筒の後端（下流側の端）と、その下流側に設けられるタービンの第１段静翼の静翼シュラウドとの間には、熱膨張を逃がすための間隙が設けられる。しかし、この間隙は、燃焼ガスがガス流路から漏れ出す経路にもなり得る。燃焼ガスがガス流路から漏れ出すとガスタービンの焼損を招くため、燃焼ガスのガス流路からの漏洩は、防止されなくてはならない。 A gap for releasing thermal expansion is provided between the rear end (downstream end) of the combustor of the gas turbine combustor and the stationary blade shroud of the first stage stationary blade of the turbine provided downstream thereof. . However, this gap can also be a path for combustion gas to leak out of the gas flow path. If the combustion gas leaks out of the gas flow path, the gas turbine will be burned out. Therefore, leakage of the combustion gas from the gas flow path must be prevented.
そこで、燃焼ガスのガス流路からの漏洩を防止するために、車室内の圧縮空気の圧力（即ち、ガス流路の外側の圧力）をガス流路の圧力よりも高くすることで、燃焼器および静翼シュラウドの外部から空気（以下、この空気をシール空気と適宜称する）を取り込み、これによって燃焼ガスがガス流路から漏れ出すことを抑制することが行われている。また、尾筒と静翼シュラウドとの間隙に、シール部材を設けることも行われている（例えば、特許文献１参照。）。 Accordingly, in order to prevent the combustion gas from leaking from the gas flow path, the pressure of the compressed air in the vehicle interior (that is, the pressure outside the gas flow path) is made higher than the pressure of the gas flow path, so that the combustor In addition, air is taken in from the outside of the stationary blade shroud (hereinafter, this air is appropriately referred to as sealing air), and thereby, combustion gas is prevented from leaking from the gas flow path. In addition, a seal member is also provided in the gap between the transition piece and the stationary blade shroud (see, for example, Patent Document 1).
しかしながら、従来に提案されている構造は、燃焼器の尾筒と静翼シュラウドとの間隙のシールが完全ではない。これは、ガスタービンの周方向に配列された静翼列における、燃焼ガスの圧力が均一でないことに起因する。
図９に示すように、ガスタービンの周方向に沿って間隔を隔てて配列された複数の静翼１０２、１０２、…に燃焼ガス１０５が静翼１０２に吹き付けられると、各静翼１０２の前縁の近傍には、圧力が高い淀み点１０２ａが現れる。そして、燃焼ガス１０５の圧力は、隣接する静翼１０２の淀み点１０２ａの中間の位置において、淀み点１０２ａの近傍よりも低くなる。
このような圧力分布により、シール空気が、燃焼器の尾筒１０１および静翼シュラウド１０３の周方向において不均一に流れることになる。
However, the structure proposed heretofore does not provide a perfect seal of the gap between the combustor tail and the stationary blade shroud. This is because the pressure of the combustion gas is not uniform in the stationary blade rows arranged in the circumferential direction of the gas turbine.
As shown in FIG. 9, when the combustion gas 105 is blown onto the stationary blades 102 on the plurality of stationary blades 102, 102,... Arranged at intervals along the circumferential direction of the gas turbine, A stagnation point 102a with high pressure appears in the vicinity of the edge. The pressure of the combustion gas 105 is lower than the vicinity of the stagnation point 102a at a position intermediate between the stagnation points 102a of the adjacent stationary blades 102.
Such pressure distribution causes the seal air to flow non-uniformly in the circumferential direction of the combustor tail cylinder 101 and the stationary blade shroud 103.
このため、図１０に示すように、燃焼ガス１０５の圧力が低い部分からは、必要以上のシール空気がガス流路に入り込むこともあり、シール空気量が増大してしまうという問題がある。 For this reason, as shown in FIG. 10, from the part where the pressure of the combustion gas 105 is low, more sealing air than necessary may enter the gas flow path, and there is a problem that the amount of sealing air increases.
また、上記の圧力分布により、図１１に示すように、互いに隣接する静翼１０２、１０２間においては、一方の静翼１０２の腹（正圧面）側１０２ｂから他方の静翼１０２の背（負圧面）側１０２ｃへと流れ（これを２次流れと言う）が生じ、これによって、シール空気が、燃焼器の尾筒１０１および静翼シュラウド１０３の周方向において不均一に流れるという傾向はますます顕著になる。 Further, due to the above pressure distribution, as shown in FIG. 11, between the adjacent stationary blades 102, 102, the back side (negative pressure surface) 102 b of one stationary blade 102 to the back (negative) of the other stationary blade 102. Pressure side) 102c flows (this is referred to as secondary flow), which increases the tendency of the seal air to flow non-uniformly in the circumferential direction of the combustor tail cylinder 101 and stationary blade shroud 103 Become prominent.
本発明は、このような技術的課題に基づいてなされたもので、シール空気の圧力分布を均一化し、シール空気量を低減することのできるガスタービンを提供することを目的とする。 The present invention has been made based on such a technical problem, and an object of the present invention is to provide a gas turbine capable of uniforming the pressure distribution of seal air and reducing the amount of seal air.
かかる目的のもとになされた本発明のガスタービンは、燃焼ガスを尾筒から噴出する燃焼器と、尾筒から燃焼ガスが供給されるタービンと、を備え、タービンは、タービンの周方向に間隔を隔てて複数設けられた静翼と、尾筒の下流側に位置し、且つ、静翼をタービンの内周側と外周側とで支持する静翼シュラウドと、を含む。そして、尾筒の静翼シュラウド側の端部、および、尾筒と静翼シュラウドとの間に設けられるシール部材の静翼シュラウドに近接する部分の少なくともいずれか一方に、それぞれの静翼の上流側において尾筒の内側に向けて突出する凸部と、互いに隣接する静翼どうしの中間部の上流側において尾筒の外側に向けて突出する凹部とが形成されていることを特徴とする。
このように、尾筒またはシール部材に凹部と凸部とを形成すると、凸部により、静翼の上流側における燃焼ガスの流速が高まり圧力が低下し、凹部により、互いに隣接する静翼同士の中間部における燃焼ガスの流速が凸部の部分よりも低くなり、圧力が高くなる。これにより、静翼列の部分において、燃焼ガスの圧力分布を均一化できる。
A gas turbine according to the present invention made for such an object includes a combustor that ejects combustion gas from a tail tube, and a turbine that is supplied with combustion gas from the tail tube, and the turbine is arranged in a circumferential direction of the turbine. A plurality of stationary blades provided at intervals, and a stationary blade shroud that is located on the downstream side of the tail cylinder and supports the stationary blades on the inner peripheral side and the outer peripheral side of the turbine. Further, at least one of the end portion on the stator blade shroud side of the tail tube and the portion of the seal member provided between the tail tube and the stator blade shroud adjacent to the stator blade shroud, the upstream of each stator blade A convex portion that protrudes toward the inside of the transition piece on the side and a concave portion that protrudes toward the outside of the transition piece on the upstream side of the intermediate portion between the adjacent stationary blades are formed.
As described above, when the concave portion and the convex portion are formed in the tail tube or the seal member, the convex portion increases the flow velocity of the combustion gas on the upstream side of the stationary blade, and the pressure is reduced. The flow velocity of the combustion gas in the intermediate portion is lower than that of the convex portion, and the pressure is increased. Thereby, the pressure distribution of the combustion gas can be made uniform in the portion of the stationary blade row.
ここで、静翼シュラウドにおいて、少なくとも尾筒またはシール部材に近接する部分に、それぞれの静翼の上流側において燃焼ガスの流路側に向けて突出する静翼シュラウド側凸部と、互いに隣接する静翼どうしの中間部の上流側において燃焼ガスの流路とは反対側に向けて突出する静翼シュラウド側凹部とを形成することもできる。 Here, in the stationary blade shroud, at least a portion adjacent to the transition piece or the sealing member, a stationary blade shroud side convex portion protruding toward the combustion gas flow path side upstream of each stationary blade, and the adjacent stationary blade shroud. It is also possible to form a stationary blade shroud side recess that protrudes toward the opposite side of the combustion gas flow path on the upstream side of the intermediate portion between the blades.
また、凸部および凹部と、静翼シュラウド側凸部および静翼シュラウド側凹部との間に、外部から燃焼ガスの流路内にシール空気を導入するためのクリアランスを形成してもよい。
そして、本発明のガスタービンは、燃焼ガスを尾筒から噴出する燃焼器と、尾筒から燃焼ガスが供給されるタービンと、を備え、タービンは、タービンの周方向に間隔を隔てて複数設けられた静翼と、尾筒の下流側に位置し、且つ、静翼をタービンの内周側と外周側とで支持する静翼シュラウドと、を含む。そして、尾筒、または尾筒と静翼シュラウドとの間に設けられるシール部材において、少なくとも静翼シュラウドに近接する部分に、それぞれの静翼の上流側において尾筒の内側に向けて突出する凸部と、互いに隣接する静翼どうしの中間部の上流側において尾筒の外側に向けて突出する凹部とが形成され、静翼シュラウドにおいて、少なくとも尾筒またはシール部材に近接する部分に、それぞれの静翼の上流側において燃焼ガスの流路側に向けて突出する静翼シュラウド側凸部と、互いに隣接する静翼どうしの中間部の上流側において燃焼ガスの流路とは反対側に向けて突出する静翼シュラウド側凹部とを形成することを特徴とする。
また、凸部および凹部と、静翼シュラウド側凸部および静翼シュラウド側凹部との間に、外部から燃焼ガスの流路内にシール空気を導入するためのクリアランスを形成してもよい。
Further, a clearance may be formed between the convex portion and the concave portion and the stationary blade shroud side convex portion and the stationary blade shroud side concave portion for introducing the sealing air into the combustion gas flow path from the outside.
And the gas turbine of this invention is provided with the combustor which injects combustion gas from a tail cylinder, and the turbine to which combustion gas is supplied from a tail cylinder, and a plurality of turbines are provided at intervals in the circumferential direction of the turbine. And a stationary blade shroud that is located on the downstream side of the transition piece and supports the stationary blade on the inner peripheral side and the outer peripheral side of the turbine. Further, in the seal member provided between the tail tube or the tail tube and the stationary blade shroud, at least a portion that is close to the stationary blade shroud protrudes toward the inside of the tail tube on the upstream side of each stationary blade. And a concave portion projecting toward the outside of the tail tube at the upstream side of the intermediate portion between the adjacent stationary blades, and at least a portion of the stationary blade shroud adjacent to the tail tube or the seal member, A vane shroud-side convex portion that protrudes toward the combustion gas flow path on the upstream side of the stationary blade, and a protrusion that protrudes toward the opposite side of the combustion gas flow path on the upstream side of the intermediate portion between the adjacent stationary blades Forming a stationary blade shroud side recess.
Further, a clearance may be formed between the convex portion and the concave portion and the stationary blade shroud side convex portion and the stationary blade shroud side concave portion for introducing the sealing air into the combustion gas flow path from the outside.
本発明によれば、尾筒またはシール部材に凹部と凸部とを形成することにより、静翼列の部分において、燃焼ガスの圧力分布を均一化できる。
また、互いに隣接する静翼の間で燃焼ガスの流れが偏るのを防いで温度差が生じるのを抑えることができ、この点からも、燃焼ガスの圧力分布を均一化することができる。
このようにして圧力分布の均一化を図ることで、燃焼器と静翼シュラウドとの隙間において、燃焼ガスの圧力が低い部分からシール空気が必要以上に入り込むのを抑えることができ、シール空気量を抑えることができる。
According to the present invention, the pressure distribution of the combustion gas can be made uniform in the stationary blade row portion by forming the concave portion and the convex portion in the tail cylinder or the seal member.
Further, it is possible to prevent the flow of the combustion gas from being biased between the adjacent stationary blades and suppress the occurrence of a temperature difference, and also from this point, the pressure distribution of the combustion gas can be made uniform.
By making the pressure distribution uniform in this way, it is possible to prevent the sealing air from entering more than necessary from the portion where the pressure of the combustion gas is low in the gap between the combustor and the stationary blade shroud. Can be suppressed.
以下、添付図面に示す実施の形態に基づいてこの発明を詳細に説明する。
［第一の実施形態］
図１は、本実施の形態におけるガスタービン（流体機械）２０の概略構成を説明するための図である。
この図１に示すように、ガスタービン２０には、空気の流れの上流側から下流側に向かって吸込ケーシング２１、圧縮機２２、燃焼器２３、タービン２４が設けられている。
吸込ケーシング２１から取り込まれた空気は圧縮機２２によって圧縮され、高温・高圧の圧縮空気となって燃焼器２３へ送り込まれる。燃焼器２３では、この圧縮空気に天然ガス等のガス、或いは軽油や軽重油等の油を供給して燃料を燃焼させ、高温・高圧の燃焼ガスを生成させる。この高温・高圧の燃焼ガスはタービン２４に噴射され、タービン２４内で膨張してタービン２４を回転させる。タービン２４の回転エネルギーにより、ガスタービン２０の主軸２５に連結された図示しない発電機等が駆動される。
Hereinafter, the present invention will be described in detail based on embodiments shown in the accompanying drawings.
[First embodiment]
FIG. 1 is a diagram for explaining a schematic configuration of a gas turbine (fluid machine) 20 in the present embodiment.
As shown in FIG. 1, the gas turbine 20 is provided with a suction casing 21, a compressor 22, a combustor 23, and a turbine 24 from the upstream side to the downstream side of the air flow.
The air taken in from the suction casing 21 is compressed by the compressor 22 and is fed into the combustor 23 as high-temperature and high-pressure compressed air. In the combustor 23, a gas such as natural gas or oil such as light oil or light heavy oil is supplied to the compressed air to burn the fuel to generate high-temperature and high-pressure combustion gas. The high-temperature and high-pressure combustion gas is injected into the turbine 24 and expands in the turbine 24 to rotate the turbine 24. A generator or the like (not shown) connected to the main shaft 25 of the gas turbine 20 is driven by the rotational energy of the turbine 24.
図２に示すように、ガスタービン２０は、圧縮空気１ａを生成する圧縮機２２（一部のみ図示）と、生成された圧縮空気１ａが供給される車室２とを備えている。車室２の内部には、燃焼ガス３ａを生成する燃焼器２３が設けられている。燃焼器２３は、ガスタービン２０の周方向に複数が設けられている。 As shown in FIG. 2, the gas turbine 20 includes a compressor 22 (only a part of which is shown) that generates compressed air 1a, and a vehicle compartment 2 to which the generated compressed air 1a is supplied. A combustor 23 that generates combustion gas 3 a is provided inside the passenger compartment 2. A plurality of combustors 23 are provided in the circumferential direction of the gas turbine 20.
各燃焼器２３の後端には、上流側の略円筒から下流側の略矩形に遷移する断面形状を有する筒状の尾筒４が設けられている。ガスタービン２０のタービン２４は、その尾筒４の下流側に設けられている。より具体的には、尾筒４の下流側には、第１段の静翼５と、静翼５を支持する内周側および外周側の静翼シュラウド６とが設けられており、これらに囲まれるように燃焼ガス３ａが流れるガス流路３ｂが形成されている。静翼５の下流には、動翼７が設けられている。ガス流路３ｂを流れる燃焼ガス３ａは、尾筒４を介して静翼５に導入され、静翼５によって方向が変えられて動翼７に噴射される。 At the rear end of each combustor 23, a cylindrical tail cylinder 4 having a cross-sectional shape that transitions from an upstream substantially cylindrical shape to a downstream substantially rectangular shape is provided. The turbine 24 of the gas turbine 20 is provided on the downstream side of the tail cylinder 4. More specifically, on the downstream side of the transition piece 4, a first stage stationary blade 5 and inner and outer stationary blade shrouds 6 that support the stationary blade 5 are provided. A gas flow path 3b through which the combustion gas 3a flows is formed so as to be surrounded. A moving blade 7 is provided downstream of the stationary blade 5. The combustion gas 3 a flowing through the gas flow path 3 b is introduced into the stationary blade 5 via the tail cylinder 4, the direction is changed by the stationary blade 5, and the jet is injected onto the moving blade 7.
ここで、図３に示すように、ガスタービン２０の周方向に沿って、複数の燃焼器２３の尾筒４が互いに隣接して配置されることで、全体として環状に配置されている。したがって、各尾筒４は、円環を周方向に分割してなる内周壁４ａおよび外周壁４ｂと、これら内周壁４ａおよび外周壁４ｂを連結する両側の側壁４ｃ、４ｄとを有している。 Here, as shown in FIG. 3, the tail cylinders 4 of the plurality of combustors 23 are arranged adjacent to each other along the circumferential direction of the gas turbine 20, so that they are arranged in an annular shape as a whole. Accordingly, each tail cylinder 4 has an inner peripheral wall 4a and an outer peripheral wall 4b obtained by dividing the annular ring in the circumferential direction, and side walls 4c and 4d on both sides connecting the inner peripheral wall 4a and the outer peripheral wall 4b. .
一方、図４に示すように、静翼シュラウド６は、円環状で、ガスタービン２０の内周側に位置する内周壁６ａと、その外周側に位置する外周壁６ｂとを有し、その間に、第１段の静翼５が両端を支持されて配置されている。第１段の静翼５は、ガスタービン２０の周方向に沿って間隔を隔てて複数が設けられている。本実施形態においては、第１段の静翼５は、尾筒４の数の２倍が設けられている。そして、第１段の静翼５は、側壁４ｃ、４ｄの燃焼ガス流れ方向下流側の位置と、これら側壁４ｃ、４ｄの中間部の位置とに配置されている。 On the other hand, as shown in FIG. 4, the stationary blade shroud 6 has an annular shape, and has an inner peripheral wall 6 a positioned on the inner peripheral side of the gas turbine 20 and an outer peripheral wall 6 b positioned on the outer peripheral side thereof. The first stage stationary blades 5 are arranged with both ends supported. A plurality of first stage stationary blades 5 are provided at intervals along the circumferential direction of the gas turbine 20. In the present embodiment, the first stage stationary blades 5 are provided twice as many as the number of tail cylinders 4. The first stage stationary blade 5 is disposed at a position downstream of the side walls 4c, 4d in the combustion gas flow direction and at a position intermediate between the side walls 4c, 4d.
図５は、燃焼器２３の尾筒４と、静翼シュラウド６との接合部の拡大図である。燃焼器２３の尾筒４には、燃焼ガス３ａが流れるガス流路３ｂと反対の側（外側）にフランジ８が接合されている。同様に、静翼シュラウド６には、燃焼ガス３ａが流れるガス流路３ｂと反対の側にフランジ９が設けられている。フランジ８、９の間に尾筒シール１１が介設され、尾筒シール１１によって尾筒４と静翼シュラウド６とが連結される。
なお、この尾筒シール１１は必須の構成ではない。
FIG. 5 is an enlarged view of a joint portion between the transition piece 4 of the combustor 23 and the stationary blade shroud 6. A flange 8 is joined to the transition piece 4 of the combustor 23 on the side (outside) opposite to the gas flow path 3b through which the combustion gas 3a flows. Similarly, the stationary blade shroud 6 is provided with a flange 9 on the side opposite to the gas flow path 3b through which the combustion gas 3a flows. A transition piece seal 11 is interposed between the flanges 8 and 9, and the transition piece 4 and the stationary blade shroud 6 are connected by the transition piece seal 11.
The tail tube seal 11 is not an essential component.
さて、図４に示したように、本実施形態においては、上記の尾筒４において、静翼シュラウド６に近接する部分に、尾筒４の内周壁４ａ、外周壁４ｂに、周方向に連続する波形の凹凸３０が形成されている。この凹凸３０は、側壁４ｃ、４ｄの位置と、側壁４ｃ、４ｄの中間部の位置とに、尾筒４の内側（ガスタービン２０の径方向に沿ってガス流路３ｂ側）に向けて突出する凸部３０ａが形成され、互いに隣接する凸部３０ａ、３０ａの中間部において尾筒４の外側（ガスタービン２０の径方向に沿ってガス流路３ｂとは反対側）に向けて突出する凹部３０ｂが形成されている。
ガスタービン２０の周方向における、これら凸部３０ａの位置は、後流側の第１段の静翼５、５、５に対応した位置である。これら凸部３０ａ、凹部３０ｂの周方向における位置は、第１段の静翼５、５、５周辺の静圧分布に応じて適宜設定すれば良い。
As shown in FIG. 4, in the present embodiment, in the above-described tail cylinder 4, in the vicinity of the stationary blade shroud 6, the inner peripheral wall 4 a and the outer peripheral wall 4 b of the tail cylinder 4 are continuous in the circumferential direction. Corrugated irregularities 30 are formed. The unevenness 30 protrudes toward the inside of the tail cylinder 4 (on the gas flow path 3b side along the radial direction of the gas turbine 20) at the positions of the side walls 4c and 4d and at the intermediate position of the side walls 4c and 4d. A convex portion 30a that protrudes toward the outside of the tail cylinder 4 (on the opposite side of the gas flow path 3b along the radial direction of the gas turbine 20) at an intermediate portion between the convex portions 30a and 30a adjacent to each other. 30b is formed.
The positions of these convex portions 30 a in the circumferential direction of the gas turbine 20 are positions corresponding to the first-stage stationary blades 5, 5, 5 on the wake side. The positions of the convex portions 30a and the concave portions 30b in the circumferential direction may be appropriately set according to the static pressure distribution around the first stage stationary blades 5, 5, and 5.
なおここで、図６に、凹凸３０の静翼シュラウド６に対する位置関係の複数例を示す。なお、図６においては、静翼シュラウド６の内周壁６ａ側のみを図示しているが、外周壁６ｂ側も、図示したのとはほぼ上下対称な構成を有している。
凸部３０ａと凹部３０ｂは、静翼シュラウド６の内周壁６ａ、外周壁６ｂに対し、図６（ａ−１）、（ａ−２）に示すように、凸部３０ａを内周壁６ａ、外周壁６ｂよりもガス流路３ｂ側に向けて突出させて位置させ、凹部３０ｂを内周壁６ａ、外周壁６ｂよりもガス流路３ｂとは反対側に向けて突出させて位置させることができる。
また、図６（ｂ−１）、（ｂ−２）に示すように、凸部３０ａを内周壁６ａ、外周壁６ｂよりもガス流路３ｂ側に向けて突出させて位置させ、凹部３０ｂを内周壁６ａ、外周壁６ｂの延長線上に位置させることができる。
さらに、図６（ｃ−１）、（ｃ−２）に示すように、凸部３０ａを内周壁６ａ、外周壁６ｂの延長線上に位置させ、凹部３０ｂを内周壁６ａ、外周壁６ｂよりもガス流路３ｂとは反対側に向けて突出させて位置させることができる。
なお、凹凸３０は尾筒４の内周壁４ａのみ、または、外周壁４ｂのみに形成してもよいが、内周壁４ａおよび外周壁４ｂのどちらにも形成することが望ましい。
FIG. 6 shows a plurality of examples of the positional relationship of the unevenness 30 with respect to the stationary blade shroud 6. In FIG. 6, only the inner peripheral wall 6 a side of the stationary blade shroud 6 is illustrated, but the outer peripheral wall 6 b side also has a configuration that is substantially vertically symmetric with respect to the illustrated one.
As shown in FIGS. 6A-1 and 6A-2, the convex portion 30a and the concave portion 30b are formed on the inner peripheral wall 6a and the outer peripheral wall as shown in FIGS. The recessed part 30b can be made to project and protrude toward the opposite side to the gas flow path 3b rather than the inner peripheral wall 6a and the outer peripheral wall 6b from the wall 6b.
Further, as shown in FIGS. 6B-1 and 6B-2, the convex portion 30a is positioned so as to protrude from the inner peripheral wall 6a and the outer peripheral wall 6b toward the gas flow path 3b, and the concave portion 30b is formed. It can be located on the extension line of the inner peripheral wall 6a and the outer peripheral wall 6b.
Further, as shown in FIGS. 6 (c-1) and 6 (c-2), the convex portion 30a is positioned on the extension line of the inner peripheral wall 6a and the outer peripheral wall 6b, and the concave portion 30b is located more than the inner peripheral wall 6a and the outer peripheral wall 6b. It can be made to project toward the opposite side to the gas flow path 3b.
In addition, although the unevenness | corrugation 30 may be formed only in the inner peripheral wall 4a of the tail tube 4, or only in the outer peripheral wall 4b, it is desirable to form in both the inner peripheral wall 4a and the outer peripheral wall 4b.
このように燃焼器２３の尾筒４の内周壁４ａ、外周壁４ｂに、周方向に連続する波形の凹凸３０を形成することによって、尾筒４から静翼シュラウド６に送り込まれる燃焼ガス３ａは、凸部３０ａの部分において流速が高まり凹部３０ｂの部分に比較して圧力が低くなる。一方は、凹部３０ｂの部分においては、凸部３０ａの部分に比較して流速が低く圧力が高い。そして、凸部３０ａを経た圧力が低い燃焼ガス３ａが第１段の静翼５の前縁１５に当たり、凹部３０ｂを経た圧力の高い燃焼ガス３ａが互いに隣接する第１段の静翼５、５の中間部に送り込まれる。これにより、第１段の静翼５、５、…の周辺における燃焼ガス３ａの圧力分布を均一化することができる。
圧力分布の均一化を図ることで、燃焼ガス３ａの圧力が低い部分からシール空気が必要以上に入り込むのを抑えることができ、シール空気量を抑えることができる。
また、圧力分布の均一化を図ることで、第１段の静翼５の背側と、隣接する第１段の静翼の腹側との間でシール空気の流れが偏るのを防ぐことができる。
Thus, by forming the corrugated unevenness 30 continuous in the circumferential direction on the inner peripheral wall 4a and the outer peripheral wall 4b of the tail cylinder 4 of the combustor 23, the combustion gas 3a fed from the tail cylinder 4 to the stationary blade shroud 6 is The flow velocity is increased in the convex portion 30a, and the pressure is lower than that in the concave portion 30b. On the other hand, the flow rate is lower and the pressure is higher in the concave portion 30b than in the convex portion 30a. The combustion gas 3a having a low pressure passing through the convex portion 30a hits the leading edge 15 of the first stage stationary blade 5, and the combustion gas 3a having a high pressure passing through the concave portion 30b is adjacent to each other in the first stage stationary blades 5,5. It is sent to the middle part. Thereby, the pressure distribution of the combustion gas 3a around the first stage stationary blades 5, 5,... Can be made uniform.
By making the pressure distribution uniform, it is possible to suppress the sealing air from entering more than necessary from the portion where the pressure of the combustion gas 3a is low, and the amount of sealing air can be suppressed.
Further, by making the pressure distribution uniform, it is possible to prevent the flow of seal air from being biased between the back side of the first stage stationary blade 5 and the ventral side of the adjacent first stage stationary blade. it can.
（変形例）
なお、上記実施形態では、尾筒４の内周壁４ａ、外周壁４ｂに凹凸３０を形成するようにしたが、尾筒シール（シール部材）１１を備える場合、尾筒シール１１にも尾筒４と同様の凹凸３０を連続して形成してもよいし、尾筒シール１１のみに凹凸３０を形成するようにしてもよい。
(Modification)
In the above embodiment, the irregularities 30 are formed on the inner peripheral wall 4a and the outer peripheral wall 4b of the tail cylinder 4, but when the tail cylinder seal (seal member) 11 is provided, the tail cylinder seal 11 also includes the tail cylinder 4 The same unevenness 30 may be formed continuously, or the unevenness 30 may be formed only on the tail tube seal 11.
また、上記第一の実施形態の構成に加え、図７に示すように、静翼シュラウド６の内周壁６ａ、外周壁６ｂの尾筒４に近接する部分にも、尾筒４の内周壁４ａ、外周壁４ｂの凹凸３０（凸部３０ａおよび凹部３０ｂ）に連続するよう、周方向に連続する波形の凹凸４０（静翼シュラウド側凸部および静翼シュラウド側凹部）を形成することもできる。
３０
Further, in addition to the configuration of the first embodiment, as shown in FIG. 7, the inner peripheral wall 4a of the tail cylinder 4 is also provided on the inner peripheral wall 6a of the stationary blade shroud 6 and the portion of the outer peripheral wall 6b adjacent to the tail cylinder 4. Further, the corrugated irregularities 40 (the stationary blade shroud side convex portion and the stationary blade shroud side concave portion) which are continuous in the circumferential direction can be formed so as to be continuous with the irregularities 30 (the convex portion 30a and the concave portion 30b) of the outer peripheral wall 4b.
30
［第二の実施形態］
次に、本発明に係る第二の実施形態について説明する。なお、以下においては、上記第一の実施形態と異なる構成を中心に説明を行い、上記第一の実施形態と共通する構成については、その説明を省略する。
図８（ａ）、（ｂ）、（ｃ）に示すように、尾筒４、および尾筒シール１１を備える場合は尾筒シール１１に、凹凸３０を形成する。
一方、尾筒４の下流側に位置する静翼シュラウド６の内周壁６ａ、外周壁６ｂの尾筒４に近接する部分に、凹凸３０よりも静翼シュラウド６に対してガス流路３ｂとは反対側に位置して静翼シュラウド側凸部と静翼シュラウド側凹部を有する凹凸５０を形成する。これにより、尾筒４側の凹凸３０と、静翼シュラウド６側の凹凸５０との間に、ガスタービン２０の径方向に沿ったクリアランス６０が形成され、このクリアランスからシール空気１００を取り込みやすくすることができ、また、凹凸３０の後端部と静翼シュラウド６の前縁との段差によって燃焼ガス３ａの流れに２次流れが発生するのを防ぐことができる。
[Second Embodiment]
Next, a second embodiment according to the present invention will be described. In the following, the description will be focused on the configuration different from the first embodiment, and the description of the configuration common to the first embodiment will be omitted.
As shown in FIGS. 8A, 8 </ b> B, and 8 </ b> C, when the transition piece 4 and the transition piece seal 11 are provided, the unevenness 30 is formed on the transition piece seal 11.
On the other hand, what is the gas flow path 3b with respect to the stationary blade shroud 6 rather than the irregularities 30 in the portions of the inner peripheral wall 6a and the outer peripheral wall 6b of the stationary blade shroud 6 located on the downstream side of the tail tube 4 closer to the tail tube 4? An unevenness 50 having a stationary blade shroud side convex portion and a stationary blade shroud side concave portion is formed on the opposite side. As a result, a clearance 60 along the radial direction of the gas turbine 20 is formed between the unevenness 30 on the transition piece 4 side and the unevenness 50 on the stationary blade shroud 6 side, and the sealing air 100 can be easily taken in from this clearance. Further, it is possible to prevent the secondary flow from being generated in the flow of the combustion gas 3a due to the step between the rear end portion of the unevenness 30 and the front edge of the stationary blade shroud 6.
なお、図８（ａ）、（ｂ）においては、凹凸３０の凸部３０ａを内周壁６ａ、外周壁６ｂよりもガス流路３ｂ側に向けて突出させて位置させ、凹部３０ｂを内周壁６ａ、外周壁６ｂよりもガス流路３ｂとは反対側に向けて突出させて位置させ、この凹凸３０に対してクリアランス６０を確保できるような位置に凹凸５０を形成している。これ以外にも、図６（ｂ−１）、（ｂ−２）、（ｃ−１）、（ｃ−２）に示したような位置に凹凸３０を形成した場合にも、凹凸３０との間にクリアランス６０を確保できるように凹凸５０を形成すれば良い。また、図８（ｃ）に示すように、凸部３０ａよりも径方向における突出高さを小さくしてクリアランス６０を確保できるように凹凸５０を形成してもよい。 8A and 8B, the convex portion 30a of the uneven portion 30 is positioned so as to protrude toward the gas flow path 3b side with respect to the inner peripheral wall 6a and the outer peripheral wall 6b, and the concave portion 30b is set to the inner peripheral wall 6a. In addition, the projection 50 is positioned so as to protrude toward the opposite side of the gas flow path 3 b from the outer peripheral wall 6 b, and the projections and depressions 50 are formed at positions where a clearance 60 can be secured with respect to the projections and depressions 30. In addition to this, even when the irregularities 30 are formed at the positions shown in FIGS. 6B-1, B-2, C-1 and C-2, What is necessary is just to form the unevenness | corrugation 50 so that the clearance 60 can be ensured between them. Further, as shown in FIG. 8C, the unevenness 50 may be formed so that the clearance 60 can be ensured by making the protrusion height in the radial direction smaller than the protrusion 30a.
なお、上記実施の形態では、ガスタービン２０の周方向に複数の尾筒４を設けるようにしたが、燃焼器２３の尾筒を、周方向に連続した環状の流路を有するアニュラ型燃焼器とし、その後流側に、周方向に複数が配列された静翼５を設けるようにしてもよい。その場合も、周方向に連続する尾筒（燃焼器）の内周壁部と外周壁部とに、上記と同様に凹凸３０を形成すれば良い。
これ以外にも、本発明の主旨を逸脱しない限り、上記実施の形態で挙げた構成を取捨選択したり、他の構成に適宜変更することが可能である。
In the above embodiment, the plurality of transition tubes 4 are provided in the circumferential direction of the gas turbine 20, but the annular combustion chamber having an annular flow path that is continuous with the transition tube of the combustion chamber 23 is provided. In addition, a plurality of stationary blades 5 arranged in the circumferential direction may be provided on the downstream side. Also in that case, the unevenness | corrugation 30 should just be formed in the inner peripheral wall part and outer peripheral wall part of the transition piece (combustor) which continues in the circumferential direction similarly to the above.
In addition to this, as long as it does not depart from the gist of the present invention, the configuration described in the above embodiment can be selected or changed to another configuration as appropriate.
３ａ 燃焼ガス
３ｂ ガス流路
４ 尾筒
４ａ 内周壁
４ｂ 外周壁
４ｃ 側壁
４ｄ 側壁
５ 静翼
６ 静翼シュラウド
６ａ 内周壁
６ｂ 外周壁
７ 動翼
８ フランジ
９ フランジ
１１ 尾筒シール（シール部材）
２０ ガスタービン
２１ 吸込ケーシング
２２ 圧縮機
２３ 燃焼器
２４ タービン
２５ 主軸
３０ 凹凸
３０ａ 凸部
３０ｂ 凹部
４０ 凹凸
５０ 凹凸
６０ クリアランス
１００ シール空気
3a Combustion gas 3b Gas flow path 4 Cylinder 4a Inner wall 4b Outer wall 4c Side wall 4d Side wall 5 Stator blade 6 Stator blade shroud 6a Inner wall 6b Outer wall 7 Flange 8 Flange 9 Flange 11 Tail cylinder seal (seal member)
20 Gas turbine 21 Suction casing 22 Compressor 23 Combustor 24 Turbine 25 Main shaft 30 Concavity and convexity 30a Convex portion 30b Concavity and convexity 50 Concavity and convexity 60 Clearance 100 Seal air
Claims (5)
前記尾筒から前記燃焼ガスが供給されるタービンと、を備え、
前記タービンは、
前記タービンの周方向に間隔を隔てて複数設けられた静翼と、
前記尾筒の下流側に位置し、且つ、前記静翼を前記タービンの内周側と外周側とで支持する静翼シュラウドと、を含み、
前記尾筒の前記静翼シュラウド側の端部、および、前記尾筒と前記静翼シュラウドとの間に設けられるシール部材の前記静翼シュラウドに近接する部分の少なくともいずれか一方に、それぞれの前記静翼の上流側において前記尾筒の内側に向けて突出する凸部と、互いに隣接する前記静翼どうしの中間部の上流側において前記尾筒の外側に向けて突出する凹部とが形成されていることを特徴とするガスタービン。 A combustor for injecting combustion gas from the tail cylinder;
A turbine to which the combustion gas is supplied from the transition piece,
The turbine is
A plurality of stationary blades provided at intervals in the circumferential direction of the turbine;
A stationary blade shroud that is located on the downstream side of the transition piece and supports the stationary blade on the inner peripheral side and the outer peripheral side of the turbine,
The stationary blade shroud-side end of the transition piece, and said at least either of a portion adjacent to said stationary blade shroud seal member provided between the transition piece and the stationary blade shrouds, each of said A convex portion projecting toward the inside of the tail tube on the upstream side of the stationary blade, and a concave portion projecting toward the outside of the tail tube on the upstream side of the intermediate portion between the stationary blades adjacent to each other are formed. A gas turbine characterized by comprising:
前記尾筒から前記燃焼ガスが供給されるタービンと、を備え、
前記タービンは、
前記タービンの周方向に間隔を隔てて複数設けられた静翼と、
前記尾筒の下流側に位置し、且つ、前記静翼を前記タービンの内周側と外周側とで支持する静翼シュラウドと、を含み、
前記尾筒、または前記尾筒と前記静翼シュラウドとの間に設けられるシール部材において、少なくとも前記静翼シュラウドに近接する部分に、それぞれの前記静翼の上流側において前記尾筒の内側に向けて突出する凸部と、互いに隣接する前記静翼どうしの中間部の上流側において前記尾筒の外側に向けて突出する凹部とが形成され、
前記静翼シュラウドにおいて、少なくとも前記尾筒または前記シール部材に近接する部分に、それぞれの前記静翼の上流側において前記燃焼ガスの流路側に向けて突出する静翼シュラウド側凸部と、互いに隣接する前記静翼どうしの中間部の上流側において前記燃焼ガスの流路とは反対側に向けて突出する静翼シュラウド側凹部とが形成されていることを特徴とするガスタービン。 A combustor for injecting combustion gas from the tail cylinder;
A turbine to which the combustion gas is supplied from the transition piece,
The turbine is
A plurality of stationary blades provided at intervals in the circumferential direction of the turbine;
A stationary blade shroud that is located on the downstream side of the transition piece and supports the stationary blade on the inner peripheral side and the outer peripheral side of the turbine,
In the seal member provided between the tail tube or between the tail tube and the stationary blade shroud, at least a portion close to the stationary blade shroud is directed to the inside of the tail tube on the upstream side of each stationary blade. And a concave portion projecting toward the outside of the tail tube on the upstream side of the intermediate portion between the stationary blades adjacent to each other ,
In the stationary blade shroud, at least a portion close to the transition piece or the seal member, and a stationary blade shroud side convex portion protruding toward the combustion gas flow path side on the upstream side of each stationary blade are adjacent to each other. A gas turbine characterized in that a stationary blade shroud side concave portion protruding toward the opposite side of the combustion gas flow path is formed on the upstream side of the intermediate portion between the stationary blades.
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