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US 4,302,062 AGranted
Turbine blade support
AssigneeUnited Technologies Corporation
InventorsAlexander D. Hunter, Jr., William T. Dennison
Life of this patent
Estimating the term…
Abstract
A mounting structure for the bearing in a hot part of a gas turbine engine that will permit thermal expansion of the bearing and its supporting ring with relation to the surrounding stationary and supporting part of the engine case without overstressing the several parts and still maintain concentricity of the bearing within this stationary support structure. This is accomplished by radially extending bosses on one part engaging slideably in radial recesses in the cooperating part.
Claims6
A bearing support device for a gas turbine engine including:
- a support structure forming part of the stationary part of the engine and including outer and inner wall elements;
- inwardly extending bosses on the inner wall element;
- and
- a bearing support ring within and spaced from said support structure, said ring having circumferentially spaced recesses to receive the bosses and constructed for radial movement of the bosses in the recesses to permit relative radial expansion, the bases of the recesses being scallop-shaped.
1 more element
A bearing support device including:
- a bearing for a turbine shaft;
- a support ring to which the bearing is secured;
- a support structure for the ring having a plurality of circumferentially spaced inwardly extending bosses on its inner surface, said ring having a plurality of circumferentially spaced recesses to accept the bosses, said bosses and recesses extending radially and having cooperating parallel surfaces on opposite edges to permit relative radial movement therebetween resulting from thermal expansion, the bases of the recesses being scallop-shaped.
Dependencies are inferred from the claim text.