Patent ID: 9234432
Filing Date: 2016-01-12
CPC Classification: F01D,F05D

Claim Text:
1. A stator blade supported by a turbine casing of a gas turbine engine, the gas turbine engine having a compressor for compressing air, combustors for combusting a mixture of fuel and compressed air supplied from the compressor, and a turbine to be driven by high-temperature and high-pressure combustion gas from the combustors, the turbine having stator assemblies and rotor assemblies positioned alternately in a direction parallel to a central axis of the gas turbine engine, the stator assemblies each having a number stator blades, wherein the stator blade has a single air passage defined in the stator blade, the single air passage having a portion positioned on an upstream side and extending in a radial direction of the gas turbine engine; a single inlet defined in the stator blade to open radially outwardly in communication with the upstream portion of the single air passage; an adjustment plate covering the single inlet, the adjustment plate having two apertures defined therein for introducing a cooling air radially inwardly into the single inlet, the two apertures being positioned and spaced away from each other on a camber line of the stator blade, the single inlet being elongated along the camber line and having a length along the camber line, one of the two apertures on the upstream side being positioned L/4 to L/3 away from an upstream end of the single inlet and the other on the downstream side being positioned 2L/3 to 3L/4 away from the upstream end of the single inlet; and a radially outward flange defined in the stator blade, the flange having the single inlet formed therewith and a radially outward surface on which the adjustment plate is fixed.