Internal bypass gas turbine engines with blade cooling

Power plants – Reaction motor – Air passage bypasses combustion chamber

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Details

60 3919, 416242, F02K 302

Patent

active

047917849

ABSTRACT:
A gas turbine having internal cooling and method of operating the same includes the bypassing of a portion of the cool air from the compressor section into the turbine section along the suction side of the turbine blades while maintaining stable flow conditions in which there is relatively low intermixing between the cool airflow on the suction side and the hot gases on the pressure side.

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