FIELD: engines and pumps.
SUBSTANCE: turbine pressure blade for use with the gas turbine engine comprises of a platform, an aerodynamic portion extending from the platform, and cooling circuits passing through the platform and the aerodynamic part of the blade. One of the cooling circuits comprises of a serpentine cooling channel disposed in the platform and comprising of one or more straight sections and one or more bends and several internal connecting passages in the serpentine cooling channel for inspection and access for repair purposes. Internal connecting passages are soldered.
EFFECT: cooling of the platform and other components without unnecessary production and operating costs and without excessive losses of the cooling medium, for efficient operation and extended component life.
18 cl, 5 dwg
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