Patent ID: 6641363
Filing Date: 2003-11-04
Classification: F01D,F05D

Abstract:
A gas turbine engine including a stage of turbine blades and a plurality of arcuate segments, said arcuate segments surrounding said stage of turbine blades, the inner surfaces of said arcuate segments defining a part of a turbine gas annulus of said engine, wherein each said segment includes a plenum chamber at its upstream end connected in cooling air flow series with a cooling air supply via a cooling air distribution member, which member has cooling air inlets from said supply, and cooling air outlets, each cooling air inlet being in flow series with a respective pair of cooling air outlets, and wherein during operation of said engine, one outlet of each said pair of outlets passes cooling air to the radially inner surface of a respective segment via an associated plenum chamber, and the other outlet of said pair passes cooling air to the radially outer surface of the respective segment.