| 摘要 |
The gas turbine engine includes a compressor section, a combustion section downstream from the compressor section and a turbine section downstream from the combustion section. The turbine section includes a rotor shaft, a plurality of turbine blades, and a plurality of discs coupling corresponding ones of the plurality of turbine blades to the rotor shaft. Each disc has a plurality of disc cooling fluid passages therein associated with cooling the turbine blades, and a respective thermal shape memory sleeve is in at least some of the disc cooling fluid passages. The thermal shape memory sleeve defines a sleeve throat opening that changes based upon a temperature to adjust a flow of cooling fluid therethrough. Part load efficiency may be increased by supplying only the needed cooling fluid to areas of the blades.
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