Patent ID: 6637209
Filing Date: 2003-10-28
Classification: F01D,F02C

Abstract:
A gas turbine engine core structure, comprising:an axially extended outer annular shaft body, said outer annular shaft body comprising a front section, a rear section, and a receiving chamber defined in a middle section connected between said front section and said rear section; a turbine rotor body, said turbine rotor body having an outer diameter smaller than an inner diameter of the rear section of said outer annular shaft body; and a plurality of turbine rotor blades respectively radially extended outwardly from turbine rotor body and fixedly connected to the rear section of said outer annular shaft body, wherein said turbine rotor body is coaxially provided in the real section of said outer annular shaft body, and said middle section of the outer annular shaft body includes slots through which compressed intake air passes in a radially inward direction to said receiving chamber and said rotor blades.