GAS TURBINE AIRFOIL WITH COOLING ENHANCEMENT

• Main Authors: SANDEEP MUNSHI SARANGAPANI, POORNA CHANDRA RAO, AJAY GANGADHAR PATIL
• Format: Patent
• Language: English; Japanese
• Published: 20.04.2015
• 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

PROBLEM TO BE SOLVED: To provide a gas turbine airfoil with cooling enhancement.SOLUTION: A turbine vane segment includes one or more vanes extending between a radially inner side wall and a radially outer side wall, each vane having a peripheral edge wall extending between a leading edge and a trailing edge of the vane. In one exemplary embodiment, at least one substantially radially-oriented cooling channel is formed in the peripheral edge wall at the leading edge, with openings at opposite ends of the cooling channel. The location and length of the cooling channels may vary about the peripheral edge wall, and the inner cavity of the vane may be provided with ribs extending along the one or more cooling channels to reinforce the wall and to also increase the cooling surface area in the inner cavity. 【課題】冷却を強化したガスタービン翼を提供する。【解決手段】タービン静翼セグメントは、半径方向内側側壁と半径方向外側側壁との間に延在する１つ以上の静翼を含み、各静翼は、前記静翼の前縁と後縁との間に延在する外周端壁を有する。１つの例示的な実施形態では、略半径方向を向いた少なくとも１つの冷却流路は、前記前縁の前記外周端壁に、開口部を前記冷却流路の両側端部に有するように形成される。前記冷却流路の位置及び長さは、前記外周端壁の周りで変えることができ、前記静翼の内部空洞部には、前記１つ以上の冷却流路に沿って延在するリブを設けて、前記壁を補強し、更に、前記内部空洞部の冷却表面積を増加させることができる。【選択図】図２