Assembly including a turbine disk for a gas turbine engine and a bearing-supporting journal, and cooling circuit for the turbine disk of such an assembly
An assembly with a turbine disk for a gas turbine engine and a bearing-supporting journal, the turbine disk having a radial annular fastening flange secured to a radial annular part of the journal by bolts, the bolts passing successively through fastening bores formed in the radial annular fastening flange of the turbine disk and in the radial annular part of the journal, the radial annular part of the journal having air circulation openings, the openings being formed between the fastening bores of the journal.
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.
2. The assembly as claimed in claim 1 , wherein the air circulation openings and the fastening bores are arranged circumferentially on the radial annular part of the journal.
3. The assembly as claimed in claim 1 , wherein the journal comprises a frustoconical part, downstream of its radial annular part, comprising an inner radial portion for mechanical reinforcement.
4. The assembly as claimed in claim 3 , wherein an upstream face of the inner radial portion of the journal directly faces a downstream face of a central bore of the high-pressure turbine disk.
5. The assembly as claimed in claim 1 , wherein a sealing disk, mounted downstream of the journal, is bolted with the journal and the turbine disk, the sealing disk comprising circulation openings which are aligned with the air circulation openings of the journal.
6. The assembly as claimed in claim 5 , wherein the passage cross section of the circulation openings of the sealing disk is adapted in order to calibrate the air circulation flow rate.
7. A cooling circuit for the turbine disk in a gas turbine engine comprising an evacuation passage, downstream of the turbine disk, passing through said openings of the assembly as claimed in claim 1 .
8. The cooling circuit as claimed in claim 7 , further comprising an upstream passage through a central bore of the turbine disk, upstream of the openings of said assembly.
9. A cooling circuit as claimed in claim 1 in a twin-spool engine comprising a high-pressure turbine and a low-pressure turbine, the turbine of said assembly being the high-pressure turbine, which circuit comprises a downstream passage, formed downstream of the openings of said assembly, in order to cool in part the low-pressure turbine.