Patent ID: 6840737
Filing Date: 2005-01-11
Classification: F01D,F05D

Abstract:
1. A gas turbine engine including a stage of turbine guide vanes each of which has a passage therethrough, the radially inner end of said passage with respect to the engine axis, having a respective tubular member in nested, spaced relationship therein, each said tubular member being in airflow communication with a space volume bounded by combustion apparatus and turbine shafts of said engine and suction means connected to draw air from said space volume via said tubular members and force said drawn air through said guide vanes wherein said suction means comprises air feed piping connecting a compressor of said engine to said space separating each said nested tubular member from the wall of its associated passage whereby in operation there is provided a flow of pressurized air over each said tubular member into said associated passage so as to cause a sufficient pressure differential between the opposing ends of each tubular member, as to promote a flow of leakage air therethrough from said space volume into their respective passages.