Cavity on-board injection for leakage flows

摘要

A gas turbine engine (20) having a turbine section cooling system is disclosed which is able to cool the turbine section (26) of the g as turbine engine (20) to an optimal operating temperature range, while at the same time not substantially degrading engine performance. The disclosure provides a number of different structures for doing so including the provision of turning foils (44), turning holes (54), and turning grooves within a secondary air flow cavity which turns or directs cooling and parasitic leakage air into the turbine section (26) in a direction in substantial alignment with a gas flow path through the turbine section (26).