Patent ID: 6120249
Filing Date: 2000-09-19
Classification: F01D,F05D,Y02T

Abstract:
A gas turbine, comprising:a) a compressor section for producing compressed air;b) a combustion section for heating a first portion of said compressed air, thereby producing a hot compressed gas;c) a turbine section for expanding said hot compressed gas, said turbine section having a rotor disposed therein, said rotor having a plurality of blades attached thereto, each of said blades having an airfoil portion and a root portion, said root portion having a platform from which said airfoil portion extends, said platform having upstream and downstream faces and a first surface exposed to said hot compressed gas and a second surface disposed opposite said first surface; andd) means for cooling said blade root platform including means for directing a cooling fluid to impinge against said second surface of said platform, wherein said blade platform cooling means comprises a member spaced from said second surface and forming a cavity therebetween, the member having a plurality of holes therein, said cooling fluid flowing through said holes into said cavity and a passage extending though a manor portion of said platform having an inlet in flow communication with said cavity and an outlet formed in said downstream face in flow communication with said hot compressed gas, whereby said passage directs said cooling fluid from said cavity to said hot compressed gas.