Patent ID: 6196791
Filing Date: 2001-03-06
Classification: F01D,F02C

Abstract:
A gas turbine moving blade cooling assembly comprising:a moving blade including a platform, and a shank portion connected to a lower portion of said platform, wherein a sidewall of said shank portion has only a single air inflow hole communicating with an interior of said moving blade;a stationary blade disposed adjacent to and upstream of said moving blade; anda turbine cylinder disposed below said stationary blade;a linear cooling air passage passing through a wall of said turbine cylinder, said linear cooling air passage extending radially outwardly in a direction toward said air inflow hole and away from an axis of rotation of said moving blade such that said linear cooling air passage extends through the wall of said turbine cylinder along a straight line and is inclined by an inclination angle relative to the axis of rotation of said moving blade,wherein said linear cooling air passage establishes fluid communication between an interior of said turbine cylinder and a space defined between said stationary blade and said moving blade so that cooling air from the interior of said turbine cylinder passes through said linear cooling air passage and is jetted into the space between said stationary blade and said moving blade in a direction toward said air inflow hole so as to flow into said air inflow hole.