GAS TURBINE STATIONARY BLADE ASSEMBLY, STATIONARY MEMBER SEGMENT, AND METHOD FOR MANUFACTURING GAS TURBINE STATIONARY BLADE ASSEMBLY
A stationary blade assembly of a gas turbine comprising: a stationary member formed in an annular shape, and a plurality of stationary blade segments each provided with a shroud and a blade body, the stationary blade segments being arranged along the circumferential direction of the stationary membe...
Saved in:
Main Authors | , , , |
---|---|
Format | Patent |
Language | English French Japanese |
Published |
29.09.2022
|
Subjects | |
Online Access | Get full text |
Cover
Loading…
Summary: | A stationary blade assembly of a gas turbine comprising: a stationary member formed in an annular shape, and a plurality of stationary blade segments each provided with a shroud and a blade body, the stationary blade segments being arranged along the circumferential direction of the stationary member radially inside the stationary member, a cavity being provided between the shrouds and the stationary member, and the shrouds being adjacent to each other in the circumferential direction of the stationary member, wherein the stationary member is provided with holes passing through from the radial outside to the radial inside of the stationary member, and the central axis of each hole is arranged toward the circumferential end of the corresponding shroud.
Ensemble aube fixe d'une turbine à gaz, l'ensemble comprenant : un élément fixe prenant une forme annulaire, et une pluralité de segments d'aube fixe comportant chacun une enveloppe et un corps d'aube, les segments d'aube fixe étant agencés le long de la direction circonférentielle de l'élément fixe radialement à l'intérieur de l'élément fixe, une cavité étant disposée entre les enveloppes et l'élément fixe, et les enveloppes étant adjacentes les unes aux autres dans la direction circonférentielle de l'élément fixe. L'élément fixe est muni de trous traversant de l'extérieur radial à l'intérieur radial, et l'axe central de chaque trou est disposé vers l'extrémité circonférentielle de l'enveloppe correspondante.
ガスタービンの静翼組立体は、環状に形成された静止部材と、シュラウドと翼体とがそれぞれに設けられた複数の静翼セグメントであって、前記静止部材の径方向内側において前記静止部材の周方向に沿って設置され、前記シュラウドと前記静止部材との間にキャビティが設けられ、前記静止部材の周方向において前記シュラウドが互いに隣り合う複数の静翼セグメントと、を備え、前記静止部材は、前記静止部材の径方向外側から径方向内側に貫通する穴が設けられ、前記穴の中心軸線は、前記シュラウドの周方向端部に向けて配置されている。 |
---|---|
Bibliography: | Application Number: WO2022JP11781 |