TURBINE STATIONARY BLADE AND GAS TURBINE

• Main Authors: TORII SHUNSUKE, MIYAHISA YASUO, MATSUO SAKI
• Format: Patent
• Language: English; Japanese
• Published: 06.12.2023
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; ENGINE PLANTS IN GENERAL; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; STEAM ENGINES; WEAPONS

To provide a turbine stationary blade which can effectively and efficiently cool a turbine stationary blade while suppressing the complication of a structure, and a gas turbine.SOLUTION: A turbine stationary blade comprises a cooling passage extending along a blade height direction in a blade main body, an outside shroud connected to the blade main body, an inside shroud connected to the blade main body, and an internal flow passage forming part extending along the blade height direction. The internal flow passage forming part forms an outside space at a side opposite to the blade main body with the outside shroud sandwiched therebetween, and forms an inside space at a side opposite to the blade main body with the inside shroud sandwiched therebetween, and the internal flow passage forming part has a first portion and a second portion which is located while being shifted to the outside rather than the first portion in the blade height direction. An area surrounded by an outer edge of the second portion in a second cross section orthogonal to the blade height direction is larger than an area surrounded by an outer edge of the first portion in a first cross section orthogonal to the blade height direction.SELECTED DRAWING: Figure 3 【課題】構造の複雑化を抑制しながら、タービン静翼の効果的かつ効率的な冷却が可能なタービン静翼及びガスタービンを提供する。【解決手段】タービン静翼は、翼本体の内部において翼高さ方向に沿って延在する冷却通路と、前記翼本体に接続される外側シュラウドと、前記翼本体に接続される内側シュラウドと、前記翼高さ方向に沿って延在する内部流路形成部と、を備え、前記内部流路形成部は、前記外側シュラウドを挟んで前記翼本体とは反対側の外側空間、及び、前記内側シュラウドを挟んで前記翼本体とは反対側の内側空間に連通する内部流路を形成し、前記内部流路形成部は、第１部分と、前記翼高さ方向において前記第１部分よりも前記外側端寄りに位置する第２部分と、を有し、前記翼高さ方向に直交する第１断面内にて前記第１部分の外縁に囲まれる面積よりも、前記翼高さ方向に直交する第２断面内にて前記第２部分の外縁に囲まれる面積のほうが大きい。【選択図】図３