GAS TURBINE, INTERMEDIATE SHAFT FOR GAS TURBINE, AND METHOD OF COOLING GAS TURBINE COMPRESSOR

摘要

To include a cooling passage leading from a latter stage of a compressor (1), via an external cooler (5), to a hollow part (6) provided in a load coupling (43) that couples a rotor (4) of the compressor (1) and a rotor (4) of a turbine (3) to each other, and also leading from the hollow part (6) to the latter stage of the compressor (1), and a centrifugal compressor (7) that raises air pressure in the hollow part (6) with rotation of the load coupling (43), in the hollow part (6). Therefore, a pressure of the air in the hollow part (6) is raised by the centrifugal compressor (7) by using a centrifugal force resulting from the rotation of the load coupling (43) at the time of operating the gas turbine. As a result, cooled air flows from the hollow part (6) to between compressor rotor blades (141) and compressor vanes (131) at the latter stage, and then flows into the hollow part (6), thereby enabling to efficiently reduce temperature in the hollow part (6).