초록 ▼

A turbine blade has a cooling air flow path specifically directed toward cooling the platform portion of the blade root. Two cooling air passages are formed in the blade root platform just below its upper surface. Each passage extends radially outward from an inlet that receives a flow of cooling ai

A turbine blade has a cooling air flow path specifically directed toward cooling the platform portion of the blade root. Two cooling air passages are formed in the blade root platform just below its upper surface. Each passage extends radially outward from an inlet that receives a flow of cooling air and then extend axially along almost the entire length of the platform. Each passage also has an outlet formed in the downstream face of the platform that allows the cooling air to exit the platform and enter the hot gas flow path. The passages are formed in portions of the platform that overhang the shank portion of root.

대표청구항 ▼

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

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 extends and a radially extending shank portion connected to said platform, a portion of said platform extending transversely beyond said shank portion, said platform further having a first approximately axially extending cooling air passage disposed in said transversely extending portion; and d) means for cooling said blade root platform by directing a second portion of said compressed air from said compressor section to flow through said first approximately axially extending cooling air passage of said platform.