JPH06229205A - Turbine nozzle - Google Patents
Turbine nozzleInfo
- Publication number
- JPH06229205A JPH06229205A JP1528793A JP1528793A JPH06229205A JP H06229205 A JPH06229205 A JP H06229205A JP 1528793 A JP1528793 A JP 1528793A JP 1528793 A JP1528793 A JP 1528793A JP H06229205 A JPH06229205 A JP H06229205A
- Authority
- JP
- Japan
- Prior art keywords
- outer peripheral
- peripheral wall
- nozzle
- wall portions
- blade
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は発電用ガスタービン等に
適用されるタービンノズルに係り、特にノズル翼をセラ
ミックスで構成した場合に好適なタービンノズルに関す
る。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a turbine nozzle applied to a gas turbine for power generation and the like, and more particularly to a turbine nozzle suitable when the nozzle blade is made of ceramics.
【０００２】[0002]
【従来の技術】近年、ガスタービンの高効率化が推進さ
れ、それに伴うタービン入口温度の高温化の要求に基づ
いて、タービンノズルのノズル翼を耐熱材料であるセラ
ミックスによって構成する研究が行なわれている。2. Description of the Related Art In recent years, the efficiency of gas turbines has been promoted, and in response to the demand for higher turbine inlet temperatures, studies have been conducted to construct nozzle blades of turbine nozzles from ceramics, which is a heat-resistant material. There is.
【０００３】図１４〜図１８は、このようなタービンノ
ズルの従来構造を示したもので、図１４および図１５に
示すように、流体通路１に配置される湾曲板状をなす１
枚の翼部２ａと、流体通路１の内外周に位置して翼部２
ａの端部にフランジ状に連設された内外周壁部２ｂ，２
ｃとからなるノズル翼２が備えられている。このノズル
翼２が図示しないタービン回転軸の周囲に複数、内外周
ホルダ３，４によってそれぞれ圧接状態で固定保持され
ている。ノズル翼２の内外周壁部２ｂ，２ｃは、翼部２
ａの背側または腹側のいずれか一方の側に向って突出
し、これによりノズル翼２は断面略コ字形をなす構造と
なっている。なお、ノズル翼２は、翼部２ａと内外周壁
部２ｂ，２ｃとを滑らかな曲面で接続した構成とされて
いる。また、ノズル翼２にかかる作動ガスからの円周方
向接線力と軸方向力とは、内周側ホルダ３および外周側
ホルダ４を介して内筒５と外筒６とによって受けられ
る。さらに、ノズル翼２と各ホルダ３，４との間には遮
熱部材７，８が介装され、これにより、ノズル翼２をセ
ラミックスで構成した場合でも翼温度の均一化が図ら
れ、過大な熱応力の発生を防ぐことができるようになっ
ている。なお、９，１０は各ホルダ３，４に付設された
ノズル翼圧接用のスプリングであり、１１はシールホル
ダである。FIGS. 14 to 18 show a conventional structure of such a turbine nozzle. As shown in FIGS. 14 and 15, a curved plate-like member 1 arranged in a fluid passage 1 is formed.
The blades 2a of one sheet and the blades 2 located on the inner and outer circumferences of the fluid passage 1
Inner and outer peripheral wall portions 2b, 2 connected to the end portion of a in a flange shape.
A nozzle blade 2 composed of c and c is provided. A plurality of the nozzle blades 2 are fixedly held around the turbine rotation shaft (not shown) in a pressure contact state by the inner and outer circumference holders 3 and 4, respectively. The inner and outer peripheral walls 2b and 2c of the nozzle blade 2 are
The nozzle blade 2 has a structure in which the nozzle vane 2 has a substantially U-shaped cross section by projecting toward either the back side or the ventral side of a. The nozzle blade 2 has a structure in which the blade portion 2a and the inner and outer peripheral wall portions 2b and 2c are connected by a smooth curved surface. Further, the tangential force in the circumferential direction and the axial force from the working gas applied to the nozzle blades 2 are received by the inner cylinder 5 and the outer cylinder 6 via the inner peripheral holder 3 and the outer peripheral holder 4. Further, heat shield members 7 and 8 are interposed between the nozzle blades 2 and the holders 3 and 4, whereby even if the nozzle blades 2 are made of ceramics, the blade temperature is made uniform and excessive. It is possible to prevent the generation of such thermal stress. In addition, 9 and 10 are springs for nozzle blade pressure contact attached to the holders 3 and 4, and 11 is a seal holder.
【０００４】[0004]
【発明が解決しようとする課題】ところで、ノズル翼２
をセラミックスで構成した場合、定常・非定常の熱応力
や熱伸び差およびガス力等によってノズル翼２にかかる
応力をいかに小さく抑えるかが問題となる。By the way, the nozzle blade 2
When the is made of ceramics, how to suppress the stress applied to the nozzle blades 2 due to steady / unsteady thermal stress, thermal expansion difference, gas force, etc. becomes a problem.
【０００５】高温ガス通路内に位置するノズル翼２の翼
部２ａにかかる熱応力や、ノズル翼２の内外周壁部２
ｂ，２ｃにかかる半径方向局所応力、また翼接触支持部
にかかる軸方向または周方向の局所応力の低減について
は、ノズル翼２を板状とし、それをバネ付き支持構造物
であるホルダ３，４によって支持することで解決されて
いる。Thermal stress applied to the blade portion 2a of the nozzle blade 2 located in the hot gas passage, and the inner and outer peripheral wall portion 2 of the nozzle blade 2
In order to reduce the local stress in the radial direction on the blades 2 and 2c and the local stress in the axial direction or the circumferential direction on the blade contact support portion, the nozzle blade 2 is formed into a plate shape, and the nozzle blade 2 is a support structure with a spring. It is solved by supporting by 4.
【０００６】しかしながら、従来のノズル翼２では、翼
部２ａの内外周端部から内外周壁部２ｂ，２ｃが一方向
に突出する片持ち梁構造であるため（図１６参照）、モ
ーメント腕長さＬ1 が大きくなり、翼部２ａと内周壁部
２ｂ、および翼部２ａと外周壁部２ｃの、各連設部分に
かかる応力の集中が避け難いという点に問題が残ってい
る。However, the conventional nozzle blade 2 has a cantilever structure in which the inner and outer peripheral wall portions 2b and 2c project in one direction from the inner and outer peripheral end portions of the blade portion 2a (see FIG. 16). The problem remains that L 1 becomes large, and it is difficult to avoid concentration of stress applied to each continuous portion of the blade portion 2a and the inner peripheral wall portion 2b, and between the blade portion 2a and the outer peripheral wall portion 2c.
【０００７】また、図１６に示すように、上記連設部分
の翼背面に存在する空間部１２に、翼部２ａと各ホルダ
３，４との間隙を通じて高温ガスが流入するため、各ホ
ルダ３，４の部材温度が上昇するという点にも問題が残
っている。Further, as shown in FIG. 16, high temperature gas flows into the space 12 existing on the back surface of the blade of the continuous portion through the gap between the blade 2a and the holders 3 and 4, so that each holder 3 The problem remains that the member temperatures of Nos. 4 and 4 rise.
【０００８】本発明はこのような点に鑑みてなされたも
ので、第１の目的は翼部と内外周壁部との接続部にかか
る応力を低減できるとともに、各ホルダの流体通路側の
空間内に高温ガスが流入することを防止できるタービン
ノズルを提供することにある。The present invention has been made in view of the above circumstances. A first object of the present invention is to reduce the stress applied to the connecting portion between the blade portion and the inner and outer peripheral wall portions, and to reduce the space inside the fluid passage side of each holder. It is an object of the present invention to provide a turbine nozzle capable of preventing high temperature gas from flowing into the turbine nozzle.
【０００９】また、第２の目的は、各ホルダが主流ガス
に曝されることを防止して各ホルダを熱的に保護でき、
同時にノズル翼内の温度分布を均一化してノズル翼に発
生する定常熱応力を低減することができるタービンノズ
ルを提供することにある。A second purpose is to prevent each holder from being exposed to the mainstream gas and to protect each holder thermally.
At the same time, it is an object of the present invention to provide a turbine nozzle that can make the temperature distribution in the nozzle blade uniform and reduce the steady thermal stress generated in the nozzle blade.
【００１０】[0010]
【課題を解決するための手段】請求項１の発明は、流体
通路に配置される湾曲板状をなす１枚の翼部と、前記流
体通路の内外周に位置して前記翼部の端部にフランジ状
に連設された内外周壁部とからなるノズル翼を備え、こ
のノズル翼をタービン回転軸の周囲に複数、内外周ホル
ダによってそれぞれ圧接状態で固定保持したタービンノ
ズルにおいて、前記ノズル翼の内外周壁部を前記翼部の
背側および腹側の両方の側に向って突出する構造とする
とともに、この内外周壁部を前記内外周ホルダに対して
それぞれ両持梁状に支持させたことを特徴とする。According to a first aspect of the present invention, there is provided a single blade having a curved plate shape disposed in a fluid passage, and an end portion of the blade located inside and outside the fluid passage. In a turbine nozzle having a nozzle vane consisting of an inner and outer peripheral wall portion continuously connected in a flange shape to each other, and a plurality of the nozzle vanes around the turbine rotating shaft, which are fixedly held in a pressed state by inner and outer peripheral holders, respectively. The inner and outer peripheral wall portions are configured to project toward both the back side and the ventral side of the wing portion, and the inner and outer peripheral wall portions are supported by the inner and outer peripheral holders in a doubly supported beam shape, respectively. Characterize.
【００１１】請求項２の発明は、流体通路に配置される
湾曲板状をなす１枚の翼部と、前記流体通路の内外周に
位置して前記翼部の端部にフランジ状に連設された内外
周壁部とからなるノズル翼を備え、このノズル翼をター
ビン回転軸の周囲に複数、内外周ホルダによってそれぞ
れ圧接状態で固定保持したタービンノズルにおいて、前
記ノズル翼の内外周壁部を前記翼部の背側および腹側の
両方の側に向って突出する構造とするとともに、この内
外周壁部を前記内外周ホルダに対してそれぞれ両持梁状
に支持させ、かつ前記内外周壁部はこれを圧接支持する
前記各内外周ホルダの流体通路側面の略全体を覆う構造
としたことを特徴とする。According to a second aspect of the present invention, a single blade having a curved plate shape is disposed in the fluid passage, and is connected to the end portion of the blade at the inner and outer circumferences of the fluid passage in a flange shape. In a turbine nozzle having a plurality of nozzle vanes formed of inner and outer peripheral wall portions, and a plurality of the nozzle vanes fixedly held in a pressed state by inner and outer peripheral holders around a turbine rotation shaft, the inner and outer peripheral wall portions of the nozzle vanes are fixed to the blades. The inner and outer peripheral wall portions are supported in a doubly supported beam shape with respect to the inner and outer peripheral holders, and the inner and outer peripheral wall portions support the inner and outer peripheral wall portions. It is characterized in that it is configured to cover substantially the entire side surface of the fluid passage of each of the inner and outer peripheral holders that are pressed and supported.
【００１２】請求項３の発明は、請求項１または２に記
載のタービンノズルにおいて、ノズル翼を翼部および内
外周壁部の全体に亘ってセラミックスによって一体的に
構成するとともに、前記内外周壁部を圧接支持する内外
周ホルダを金属材料によって構成し、かつ前記内外周ホ
ルダの前記内外周壁部に対する接合面側に、表層側に向
ってセラミックスの組成割合が傾斜状に増大するセラミ
ックスおよび金属の傾斜機能材料層を形成したことを特
徴とする。According to a third aspect of the present invention, in the turbine nozzle according to the first or second aspect, the nozzle blade is integrally formed of ceramics over the entire blade portion and the inner and outer peripheral wall portions, and the inner and outer peripheral wall portions are formed. The inner and outer circumference holders that are pressed and supported are made of a metal material, and the function of tilting the ceramics and the metal is such that the composition ratio of the ceramics increases in an inclined shape toward the surface layer on the joint surface side of the inner and outer circumference holders with respect to the inner and outer circumference walls It is characterized in that a material layer is formed.
【００１３】[0013]
【作用】請求項１の発明によれば、ノズル翼の内外周壁
部を前記翼部の背側および腹側の両方の側に向って突出
する構造とするとともに、この内外周壁部を前記内外周
ホルダに対してそれぞれ両持梁状に支持させたので、ノ
ズル翼の内外周壁部の周方向長さが短くなり、翼の高さ
方向にかかる荷重によって翼部と内外周壁部との連設部
に生じるモーメントが軽減でき、曲げ応力の低減が図れ
るようになる。また、翼部と各ホルダとの間に空間部が
存在しないため、高温ガスの流入による各ホルダの部材
温度の上昇が防止できる。According to the invention of claim 1, the inner and outer peripheral wall portions of the nozzle blade are configured to project toward both the back side and the abdominal side of the blade portion, and the inner and outer peripheral wall portions are formed into the inner and outer peripheral walls. Since the holders are supported in a double-supported beam shape, the circumferential length of the inner and outer peripheral wall of the nozzle blade is shortened, and the blade and the inner and outer peripheral wall are continuously connected by the load applied in the height direction of the blade. It is possible to reduce the moment generated at the time and to reduce the bending stress. Further, since there is no space between the blade portion and each holder, it is possible to prevent the member temperature of each holder from rising due to the inflow of high-temperature gas.
【００１４】請求項２の発明によれば、ノズル翼の内外
周壁部を前記翼部の背側および腹側の両方の側に向って
突出する構造とするとともに、この内外周壁部を前記内
外周ホルダに対してそれぞれ両持梁状に支持させ、かつ
前記内外周壁部はこれを圧接支持する前記各内外周ホル
ダの流体通路側面の略全体を覆う構造としたので、ノズ
ル翼支持用の各ホルダの主流ガス側面のをノズル翼の内
外周壁部によって覆うことができ、同面を熱的に保護で
きるようになる。According to the second aspect of the present invention, the inner and outer peripheral wall portions of the nozzle blade project toward both the back side and the ventral side of the blade portion, and the inner and outer peripheral wall portions are formed on the inner and outer peripheral wall portions. Since the holders are supported in a cantilevered manner, and the inner and outer peripheral wall portions cover substantially the entire fluid passage side surfaces of the inner and outer peripheral holders that press and support the holders, the holders for supporting the nozzle blades are provided. The side surface of the mainstream gas can be covered with the inner and outer peripheral wall portions of the nozzle blade, and the same surface can be thermally protected.
【００１５】請求項３の発明によれば、各ホルダの対ノ
ズル翼接合面側に傾斜機能材料層を形成したので、ノズ
ル翼を通して高温主流ガスより流れ込む熱流束が一層低
減され、各ホルダの温度上昇が抑えられる。同時にノズ
ル翼内外周壁部のガス通路側と反ガス通路側との温度差
を減少でき、ノズル翼をセラミックスで構成した場合で
も内部の温度分布を均一化して定常熱応力の発生を抑制
できる。According to the third aspect of the invention, since the functionally graded material layer is formed on the joint surface side of each holder with respect to the nozzle blade, the heat flux flowing from the hot mainstream gas through the nozzle blade is further reduced, and the temperature of each holder is increased. The rise is suppressed. At the same time, the temperature difference between the gas passage side and the anti-gas passage side of the inner and outer peripheral wall of the nozzle blade can be reduced, and even when the nozzle blade is made of ceramics, the internal temperature distribution can be made uniform and the occurrence of steady thermal stress can be suppressed.
【００１６】[0016]
【実施例】以下、本発明の実施例について添付図面を参
照して説明する。Embodiments of the present invention will be described below with reference to the accompanying drawings.
【００１７】実施例１（図１〜図６） 図１はノズル翼の本体を示す斜視図である。 Embodiment 1 (FIGS. 1 to 6) FIG. 1 is a perspective view showing a main body of a nozzle blade.
【００１８】同図に示すように、本実施例ではノズル翼
２１が耐熱性材料、例えばセラミックスによって構成さ
れている。このノズル翼２１の翼部２１ａは、ガス流の
設定および増速に好適な湾曲板状をなしている。翼部２
１ａの内周側および外周側両端には、この翼部２１ａを
含む面に直交して背腹両方向に突出する内周壁部２１ｂ
および外周壁部２１ｃが一体に連設され、これにより１
ピッチ分のノズル翼２１が構成されている。翼部２１ａ
と内周壁部２１ｂおよび外周壁部２１ｃとは、それぞれ
滑らかな曲面で連接されており、それらの境界部も含め
て肉厚は一様となっている。As shown in the figure, in this embodiment, the nozzle blade 21 is made of a heat resistant material such as ceramics. The blade portion 21a of the nozzle blade 21 has a curved plate shape suitable for setting and speeding up the gas flow. Wings 2
An inner peripheral wall portion 21b which is orthogonal to a surface including the blade portion 21a and protrudes in both back and ventral directions at both inner and outer peripheral sides of 1a.
And the outer peripheral wall portion 21c are integrally provided in series so that 1
Nozzle blades 21 for the pitch are configured. Wings 21a
The inner peripheral wall portion 21b and the outer peripheral wall portion 21c are connected to each other by smooth curved surfaces, and the wall thickness is uniform including the boundary portion thereof.
【００１９】図２はノズル翼２１の支持構造を示す斜視
図、図３はタービンノズルの１ピッチ分の部品構成を示
す分解斜視図である。FIG. 2 is a perspective view showing the structure for supporting the nozzle blades 21, and FIG. 3 is an exploded perspective view showing the component structure for one pitch of the turbine nozzle.
【００２０】また、図４は図２のＡ−Ａ線断面図、図５
は環状の翼列を構成する複数のタービンノズルの隣接す
る２ピッチ分のノズル翼をガス流入方向から見た側面
図、図６は図５に示す支持構造部の詳細図である。FIG. 4 is a sectional view taken along the line AA of FIG.
FIG. 6 is a side view of nozzle blades for two pitches adjacent to each other of a plurality of turbine nozzles forming an annular blade row as seen from the gas inflow direction, and FIG. 6 is a detailed view of the support structure portion shown in FIG.
【００２１】これらの図に示すように、ノズル翼２１
は、外筒２２および内筒２３にそれぞれ装着された金属
製の外周側ホルダ２４および内周側ホルダ２５の各窪み
部２６，２７に、外周壁部２１ｃおよび内周壁部２１ｂ
を嵌合した状態で外周側および内周側から挾圧保持され
ている。As shown in these figures, the nozzle blade 21
Is located in the recesses 26 and 27 of the metal outer peripheral side holder 24 and the inner peripheral side holder 25 mounted on the outer cylinder 22 and the inner cylinder 23, respectively, in the outer peripheral wall portion 21c and the inner peripheral wall portion 21b.
In the state of being fitted, the clamping pressure is held from the outer peripheral side and the inner peripheral side.
【００２２】なお、ノズル翼２１の外周側反ガス通路面
２１ｅと外周側ホルダ２４の窪み部２６との間、および
内周側反ガス通路面２１ｄと内周側ホルダ２５の窪み部
２７との間には、それぞれ遮熱部材としての遮熱板２
８，２９が介挿されている。Between the outer peripheral side anti-gas passage surface 21e of the nozzle blade 21 and the recessed portion 26 of the outer peripheral side holder 24, and between the inner peripheral side anti-gas passage surface 21d and the recessed portion 27 of the inner peripheral side holder 25. Between them, a heat shield plate 2 as a heat shield member, respectively.
8, 29 are inserted.
【００２３】また、ノズル翼２１、遮熱板２８，２９お
よび各ホルダ２４，２５は相互に固定されていないが、
外周側ホルダ２４に内蔵した板ばね３０、および内周側
ホルダ２５と内筒２３との間に挿着した板ばね３１によ
り常時、外周側および内周側から弾性的に押圧支持され
ている。Although the nozzle blade 21, the heat shield plates 28 and 29, and the holders 24 and 25 are not fixed to each other,
A leaf spring 30 built in the outer peripheral side holder 24 and a leaf spring 31 inserted between the inner peripheral side holder 25 and the inner cylinder 23 are always elastically pressed and supported from the outer peripheral side and the inner peripheral side.
【００２４】さらに、ノズル翼２１の各周壁部２１ｂ，
２１ｃおよび各遮熱板２８，２９の外形状は各ホルダ２
４，２５の窪み部２６，２７より小さく形成され、これ
によりノズル翼２１の各周壁部２１ｂ，２１ｃおよび遮
熱板２８，２９が各ホルダ２４，２５の窪み部２６，２
７で移動可能となっている。Further, each peripheral wall portion 21b of the nozzle blade 21 is
The outer shapes of 21c and the heat shields 28 and 29 are the holders 2 respectively.
The recesses 26, 27 of the nozzle blades 21 are formed smaller than the recesses 26, 27 of the holder blades 24, 25.
It is possible to move at 7.
【００２５】なお、図５に示すように、互いに隣接する
外周側ホルダ２４，２４間、および内周側ホルダ２５，
２５間の間隙は、それぞれシールプレート３２によって
閉塞されている。As shown in FIG. 5, between the outer peripheral side holders 24, 24 adjacent to each other and the inner peripheral side holders 25,
The gap between the 25 is closed by a seal plate 32.
【００２６】しかして、運転時においては、ノズル翼２
１を通過するガス力によって、図５に示すように、ノズ
ル翼２１の外周側円周方向肉厚端面２１ｆおよび内周側
円周方向肉厚端面２１ｇは各ホルダ２４，２５の窪み内
壁２４ａ，２５ａにそれぞれ接触し、また図４に示すよ
うに、外周側軸方向肉厚端面２１ｈおよび内周側軸方向
肉厚端面２１ｉは各ホルダ２４，２５の窪み内壁２４
ｂ，２５ｂに接触する。However, during operation, the nozzle blade 2
As shown in FIG. 5, due to the gas force passing through 1, the outer circumferential side thick end face 21f and the inner circumferential side thick end face 21g of the nozzle vane 21 are recessed inner walls 24a of the holders 24, 25, respectively. 25a, respectively, and as shown in FIG. 4, the outer peripheral side axially thick end face 21h and the inner peripheral side axially thick end face 21i are recessed inner wall 24 of each holder 24, 25.
Contact b, 25b.
【００２７】一方、ノズル翼２１は板ばね３０，３１に
よって常に圧縮荷重Ｆを受けている。この場合、本実施
例では図６に示すようにモーメント腕長さＬ2 が従来例
におけるモーメント腕長さＬ1 に比べて約半分の長さと
なるため、圧縮荷重Ｆおよびモーメント腕長さＬ2 に基
づいて翼部２１ａと外周壁部２１ｃとの連設部２１ｌに
生じる曲げモーメントは、従来例に比べて略半分に低減
できる。内側支持構造部においても同様である。On the other hand, the nozzle blade 21 is constantly subjected to the compressive load F by the leaf springs 30 and 31. In this case, in this embodiment, as shown in FIG. 6, the moment arm length L 2 is about half the moment arm length L 1 in the conventional example, so the compression load F and the moment arm length L 2 Based on the above, the bending moment generated in the connecting portion 21l of the wing portion 21a and the outer peripheral wall portion 21c can be reduced to about half as compared with the conventional example. The same applies to the inner support structure portion.
【００２８】また、従来例においては、図１６に示した
ように、翼部２ａと各ホルダ２４，２５との間の間隙を
通じて空間部１２に高温ガスが流入し、各ホルダ２４，
２５の温度が上昇していたが、本実施例においてはその
ような空間部が存在しないため、高温ガスの流入という
ことがなく、それだけ温度上昇が防止できるようにな
る。Further, in the conventional example, as shown in FIG. 16, the high temperature gas flows into the space 12 through the gap between the blade portion 2a and the holders 24, 25, and the holders 24, 25
Although the temperature of 25 has risen, in the present embodiment, since there is no such space portion, there is no inflow of high temperature gas, and the temperature rise can be prevented accordingly.
【００２９】実施例２（図７〜図１０） 図７はノズル翼の本体を示す斜視図、図８はノズル翼２
１の支持構造を示す斜視図、図９はタービンノズルの１
ピッチ分の部品構成を示す分解斜視図である。また、図
１０は図８のＢ−Ｂ線断面図である。 Embodiment 2 (FIGS. 7 to 10) FIG. 7 is a perspective view showing a main body of a nozzle blade, and FIG. 8 is a nozzle blade 2
1 is a perspective view showing a supporting structure of FIG. 1, and FIG.
It is an exploded perspective view showing a component composition for a pitch. 10 is a sectional view taken along line BB of FIG.
【００３０】これらの図に示すように、本実施例では、
ノズル翼２１の各周壁部２１ｂ，２１ｃの反ガス通路側
に窪み部４０，４１が形成されている。そして、ノズル
翼２１の各窪み部４０，４１内に、キープレート２８，
２９が挿入されている。As shown in these figures, in this embodiment,
Recesses 40 and 41 are formed on the side of the peripheral walls 21b and 21c of the nozzle blade 21 opposite to the gas passage. The key plate 28,
29 is inserted.
【００３１】また、ノズル翼２１の各周壁部２１ｂ，２
１ｃの端面は、各ホルダ２４，２５のガス通路側面２４
ｃ，２５ｃとそれぞれ同一形状、同一寸法とされ、これ
により各ホルダ２４，２５のガス通路部側面２４ｃ，２
５ｃがノズル翼２１で覆われている。なお、各ホルダ２
４，２５のガス通路部側面２４ｃ，２５ｃはセラミック
コーティング層２４ｄ，２５ｄで覆われている。他の構
成は実施例１と略同様であるから、図７〜図１０に図１
〜図４と同一符号を付して、説明を省略する。Further, each peripheral wall portion 21b, 2 of the nozzle blade 21
The end surface of 1c is the gas passage side surface 24 of each holder 24, 25.
c and 25c have the same shape and the same size, so that the gas passage portion side surfaces 24c and 2 of the holders 24 and 25 are formed.
5 c is covered with the nozzle blade 21. In addition, each holder 2
Side surfaces 24c and 25c of the gas passage portions 4 and 25 are covered with ceramic coating layers 24d and 25d. Since other configurations are substantially the same as those of the first embodiment, the configuration shown in FIG.
~ The same reference numerals as in Fig. 4 are given and the description thereof is omitted.
【００３２】本実施例によれば、ノズル翼２１を通過す
るガス力によって、ノズル翼２１の窪み部４０，４１の
前部内側面４０ａ，４１ａおよび中間部内側面４０ｂ，
４１ｂが各キープレート２８，２９の上流側端面２８
ａ，２９ａに接触し、また各キープレート２８，２９の
下流側端面２８ｂ，２９ｂが各ホルダ２４，２５の窪み
部２６，２７の下流側内側面２６ｃ，２７ｃに接触す
る。また、各ホルダ２４，２５のガス通路部面２４ｃ，
２５ｃが、セラミック製のノズル翼２１の各周壁部２１
ｂ，２１ｃによって覆われるとともに、各キープレート
２８，２９の遮熱効果により、各ホルダ２４，２５に伝
達される熱流束が減少し、金属製の各ホルダ２４，２５
を許容温度内に保つために必要な冷却空気量が低減され
る。According to this embodiment, due to the gas force passing through the nozzle blade 21, the inner front surfaces 40a and 41a of the recesses 40 and 41 of the nozzle blade 21 and the inner side surface 40b of the intermediate portion,
41b is the upstream end surface 28 of each key plate 28, 29.
a, 29a, and the downstream end surfaces 28b, 29b of the key plates 28, 29 contact the downstream inner side surfaces 26c, 27c of the recesses 26, 27 of the holders 24, 25, respectively. Also, the gas passage surface 24c of each holder 24, 25,
25c is each peripheral wall portion 21 of the nozzle blade 21 made of ceramics.
The heat flux transmitted to the holders 24, 25 is reduced by the heat shielding effect of the key plates 28, 29 while being covered with the b, 21c.
The amount of cooling air required to keep the temperature within the allowable temperature is reduced.
【００３３】また、本実施例においてはセラミックコー
ティング層２４ｄ，２５ｄによりノズル翼２１と金属部
材との接触面が存在しなくなり、ノズル翼２１内の温度
分布が均一化されるため、過大な定常熱応力は発生しな
い。Further, in this embodiment, the ceramic coating layers 24d and 25d prevent the contact surface between the nozzle blade 21 and the metal member from existing, and the temperature distribution inside the nozzle blade 21 is made uniform, so that an excessive steady-state heat is generated. No stress is generated.
【００３４】実施例３（図１１〜図１３） 図１１は本実施例によるノズル翼の支持構造を示す斜視
図、図１２はタービンノズルの１ピッチ分の部品構成を
示す分解斜視図、図１３は図１１のＣ−Ｃ線断面図であ
る。 Embodiment 3 (FIGS. 11 to 13) FIG. 11 is a perspective view showing a support structure of a nozzle blade according to this embodiment, FIG. 12 is an exploded perspective view showing a component structure for one pitch of a turbine nozzle, FIG. FIG. 12 is a sectional view taken along line CC of FIG. 11.
【００３５】本実施例では、各ホルダ２４，２５のガス
通路側面に、奥側が金属組成、表面側がセラミックス組
成で、奥側から表面側に向って金属からセラミックスへ
と成分が次第に変化する傾斜機能材料層５０を溶射して
ある。In this embodiment, the gas passage side surface of each holder 24, 25 has a metal composition on the back side and a ceramic composition on the front side, and an inclined function in which the component gradually changes from metal to ceramic from the back side to the surface side. The material layer 50 is sprayed.
【００３６】この傾斜機能材料層５０は、中央部にキー
プレートに代る突部５０ａを有し、この突部５０ａがノ
ズル翼２１の各周壁部２１ｂ，２１ｃの窪み部４０，４
１に嵌合するようになっている。The functionally graded material layer 50 has a protrusion 50a in the center thereof which replaces the key plate, and the protrusion 50a forms recesses 40, 4 in the peripheral wall portions 21b, 21c of the nozzle blade 21.
It is designed to fit into 1.
【００３７】その他は実施例２と略同様であるから、図
１１〜図１３に図８〜図１０とに同一符号を付して説明
を省略する。Since the other points are substantially the same as those of the second embodiment, the same symbols are attached to FIGS. 11 to 13 and FIGS.
【００３８】本実施例によれば、各ホルダ２４，２５の
ガス通路部側面とノズル翼２１とが常に密着し、何らか
の原因でそれらの間に空隙が生じたときも、ホルダ２
４，２５の金属部分は、傾斜機能材料層５０の表面側の
セラミックス部分に保護されて高温ガスに直接曝される
ことはないため、冷却空気減少に貢献できる。According to this embodiment, even if the side surfaces of the gas passages of the holders 24 and 25 are in close contact with the nozzle blades 21 and a gap is generated between them, the holder 2
The metal portions 4 and 25 are protected by the ceramic portion on the surface side of the functionally gradient material layer 50 and are not directly exposed to the high temperature gas, so that they can contribute to the reduction of cooling air.
【００３９】また、従来のノズル翼支持構造に比べて組
立て時の部品点数が減少するという利点も生じる。Further, there is an advantage that the number of parts during assembly is reduced as compared with the conventional nozzle blade supporting structure.
【００４０】[0040]
【発明の効果】請求項１の発明によれば、ノズル翼の内
外周壁部の周方向長さが短くなり、翼の高さ方向にかか
る荷重によって翼部と内外周壁部との連設部に生じるモ
ーメントを軽減させ、曲げ応力の低減が図られる。ま
た、翼部と各ホルダとの間に空間部が存在しないため、
高温ガスの流入による各ホルダの部材温度の上昇が防止
できる。According to the invention of claim 1, the circumferential length of the inner and outer peripheral wall portions of the nozzle blade is shortened, and the load applied in the height direction of the blade imposes a continuous portion between the blade portion and the inner and outer peripheral wall portions. The generated moment is reduced, and the bending stress is reduced. Also, since there is no space between the wing and each holder,
It is possible to prevent the member temperature of each holder from rising due to the inflow of high-temperature gas.
【００４１】請求項２の発明によれば、ノズル翼支持用
の各ホルダの主流ガス側面をノズル翼の内外周壁部によ
って覆うことができ、同面を熱的に保護できる。According to the invention of claim 2, the mainstream gas side surface of each holder for supporting the nozzle blade can be covered with the inner and outer peripheral wall portions of the nozzle blade, and the same surface can be thermally protected.
【００４２】請求項３の発明によれば、各ホルダの対ノ
ズル翼接合面側に傾斜機能材料層を形成したので、ノズ
ル翼を通して高温主流ガスより流れ込む熱流束が一層低
減され、各ホルダの温度上昇が抑えられる。同時にノズ
ル翼内外周壁部のガス通路側と反ガス通路側との温度差
を減少でき、ノズル翼をセラミックスとした場合でも内
部の温度分布を均一化して定常熱応力の発生を抑制でき
る。According to the third aspect of the present invention, since the functionally graded material layer is formed on the joint surface side of each holder with respect to the nozzle blade, the heat flux flowing from the hot mainstream gas through the nozzle blade is further reduced, and the temperature of each holder is increased. The rise is suppressed. At the same time, the temperature difference between the gas passage side and the anti-gas passage side of the inner and outer peripheral wall of the nozzle blade can be reduced, and even when the nozzle blade is made of ceramics, the internal temperature distribution can be made uniform and the occurrence of steady thermal stress can be suppressed.
【図１】本発明の実施例１によるタービンノズルのノズ
ル翼を示す斜視図。FIG. 1 is a perspective view showing a nozzle blade of a turbine nozzle according to a first embodiment of the present invention.
【図２】同実施例の支持構造を示す斜視図。FIG. 2 is a perspective view showing a support structure of the embodiment.
【図３】同実施例の部品構成を示す分解斜視図。FIG. 3 is an exploded perspective view showing a component structure of the embodiment.
【図４】図２のＡ−Ａ線断面図。4 is a cross-sectional view taken along the line AA of FIG.
【図５】同実施例の側面図。FIG. 5 is a side view of the embodiment.
【図６】図５の一部を拡大して示す詳細図。FIG. 6 is a detailed view showing a part of FIG. 5 in an enlarged manner.
【図７】本発明の実施例２によるノズル翼を示す斜視
図。FIG. 7 is a perspective view showing a nozzle blade according to a second embodiment of the present invention.
【図８】同実施例の支持構造を示す斜視図。FIG. 8 is a perspective view showing a support structure of the embodiment.
【図９】同実施例の部品構成を示す分解斜視図。FIG. 9 is an exploded perspective view showing a component structure of the embodiment.
【図１０】図８のＢ−Ｂ線断面図。10 is a sectional view taken along line BB of FIG.
【図１１】本発明の実施例３によるノズル翼を示す斜視
図。FIG. 11 is a perspective view showing a nozzle blade according to a third embodiment of the present invention.
【図１２】同実施例の部品構成を示す分解斜視図。FIG. 12 is an exploded perspective view showing a component structure of the embodiment.
【図１３】図１１のＣ−Ｃ線断面図。13 is a cross-sectional view taken along the line CC of FIG.
【図１４】従来例におけるノズル翼を示す斜視図。FIG. 14 is a perspective view showing a nozzle blade in a conventional example.
【図１５】従来例における支持構造を示す側面図。FIG. 15 is a side view showing a support structure in a conventional example.
【図１６】図１５の一部を拡大して示す詳細図。FIG. 16 is a detailed view showing a part of FIG. 15 in an enlarged manner.
【図１７】図１６に対応する斜視図。FIG. 17 is a perspective view corresponding to FIG. 16.
【図１８】従来例による部品の分解斜視図。FIG. 18 is an exploded perspective view of a conventional component.
２１ ノズル翼 ２１ａ 翼部 ２１ｂ．２１ｃ 周壁部 ２４，２５ ホルダ ５０ 傾斜機能材料層 21 nozzle blade 21a blade portion 21b. 21c Peripheral wall 24, 25 Holder 50 Functionally graded material layer
Claims (3)
枚の翼部と、前記流体通路の内外周に位置して前記翼部
の端部にフランジ状に連設された内外周壁部とからなる
ノズル翼を備え、このノズル翼をタービン回転軸の周囲
に複数、内外周ホルダによってそれぞれ圧接状態で固定
保持したタービンノズルにおいて、前記ノズル翼の内外
周壁部を前記翼部の背側および腹側の両方の側に向って
突出する構造とするとともに、この内外周壁部を前記内
外周ホルダに対してそれぞれ両持梁状に支持させたこと
を特徴とするタービンノズル。1. A curved plate-shaped member 1 arranged in a fluid passage.
Nozzle blades composed of a single blade portion and inner and outer peripheral wall portions located inside and outside the fluid passage and connected to the end portions of the blade portion in a flange shape are provided. In a turbine nozzle fixedly held in a pressed state by a plurality of inner and outer circumference holders, the inner and outer peripheral wall portions of the nozzle blade are configured to project toward both the back side and the ventral side of the blade portion, and A turbine nozzle characterized in that the inner and outer peripheral wall portions are supported by the inner and outer peripheral holders in the shape of a doubly supported beam.
枚の翼部と、前記流体通路の内外周に位置して前記翼部
の端部にフランジ状に連設された内外周壁部とからなる
ノズル翼を備え、このノズル翼をタービン回転軸の周囲
に複数、内外周ホルダによってそれぞれ圧接状態で固定
保持したタービンノズルにおいて、前記ノズル翼の内外
周壁部を前記翼部の背側および腹側の両方の側に向って
突出する構造とするとともに、この内外周壁部を前記内
外周ホルダに対してそれぞれ両持梁状に支持させ、かつ
前記内外周壁部はこれを圧接支持する前記各内外周ホル
ダの流体通路側面の略全体を覆う構造としたことを特徴
とするタービンノズル。2. A curved plate-shaped member 1 arranged in a fluid passage.
Nozzle blades composed of a single blade portion and inner and outer peripheral wall portions located inside and outside the fluid passage and connected to the end portions of the blade portion in a flange shape are provided. In a plurality of turbine nozzles, each of which is fixedly held in a pressed state by an inner / outer peripheral holder, the inner and outer peripheral wall portions of the nozzle blade are configured to project toward both the back side and the ventral side of the blade portion, and The inner and outer peripheral wall portions are supported by the inner and outer peripheral holders in a doubly supported beam shape, and the inner and outer peripheral wall portions cover substantially the entire fluid passage side surface of each of the inner and outer peripheral holders that press and support the inner and outer peripheral wall portions. Characteristic turbine nozzle.
ルにおいて、ノズル翼を翼部および内外周壁部の全体に
亘ってセラミックスによって一体的に構成するととも
に、前記内外周壁部を圧接支持する内外周ホルダを金属
材料によって構成し、かつ前記内外周ホルダの前記内外
周壁部に対する接合面側に、表層側に向ってセラミック
スの組成割合が傾斜状に増大するセラミックスおよび金
属の傾斜機能材料層を形成したことを特徴とするタービ
ンノズル。3. The turbine nozzle according to claim 1 or 2, wherein the nozzle blade is integrally formed of ceramics over the entire blade portion and the inner and outer peripheral wall portions, and the inner and outer peripheral portions press-contact and support the inner and outer peripheral wall portions. The holder is made of a metal material, and a functionally graded material layer of ceramics and metal is formed on the joint surface side of the inner and outer peripheral holders with respect to the inner and outer peripheral wall portions so that the composition ratio of the ceramics increases in a gradient shape toward the surface layer side. A turbine nozzle characterized in that.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1528793A JPH06229205A (en) | 1993-02-02 | 1993-02-02 | Turbine nozzle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1528793A JPH06229205A (en) | 1993-02-02 | 1993-02-02 | Turbine nozzle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH06229205A true JPH06229205A (en) | 1994-08-16 |
Family
ID=11884641
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1528793A Pending JPH06229205A (en) | 1993-02-02 | 1993-02-02 | Turbine nozzle |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH06229205A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6491493B1 (en) * | 1998-06-12 | 2002-12-10 | Ebara Corporation | Turbine nozzle vane |
| JP2005146896A (en) * | 2003-11-11 | 2005-06-09 | Toshiba Corp | Nozzle diaphragm of steam turbine and steam turbine plant |
-
1993
- 1993-02-02 JP JP1528793A patent/JPH06229205A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6491493B1 (en) * | 1998-06-12 | 2002-12-10 | Ebara Corporation | Turbine nozzle vane |
| JP2005146896A (en) * | 2003-11-11 | 2005-06-09 | Toshiba Corp | Nozzle diaphragm of steam turbine and steam turbine plant |
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