Patent ID: 8899913
Filing Date: 2014-12-02
Classification: F01D,Y02T

Abstract:
1. An assembly comprising: a high-pressure turbine disk for a gas turbine engine, and a bearing-supporting journal, the high-pressure turbine disk comprising a radial annular fastening flange secured to a radial annular part of the journal by bolts, with a downstream face of the radial annular fastening flange of the high-pressure turbine disk abutting an upstream face of the radial annular part of the journal, the bolts passing successively through first fastening bores formed in the radial annular fastening flange of the high-pressure turbine disk and through second fastening bores in the radial annular part of the journal, wherein the radial annular fastening flange of the high-pressure turbine disk includes a crenelated radial annular band comprising teeth separated circumferentially by crenels, the first fastening bores being formed in the teeth, wherein the radial annular part of the journal comprises air circulation openings circumferentially disposed between the second fastening bores on the radial annular part of the journal, wherein the crenels of the radial annular fastening flange are circumferentially aligned with the air circulation openings disposed on the radial annular part of the journal, wherein the teeth of the radial annular fastening flange of the high-pressure turbine disk extend radially toward an axis of the engine and present a free inner radial edge below the first fastening bores, and wherein the crenels of the radial annular fastening flange of the turbine disk are open in a radial direction toward the axis of the engine such that each of the crenels are delimited by side surfaces of the teeth and an upper edge.