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US 2015/0176493 A1Published application
Gas turbine engine forward bearing compartment architecture
AssigneeUnited Technologies Corporation
InventorsPeter M. Munsell, Philip S. Stripinis
Life of this patent
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Abstract
A gas turbine engine includes a bearing structure mounted to the front center body case structure to rotationally support a shaft driven by a geared architecture. A bearing compartment passage structure is in communication with the bearing structure through a front center body case structure.
Claims18
A gas turbine engine comprising:
- a front center body case structure;
- a geared architecture at least partially supported by said front center body case structure;
- a bearing structure mounted to said front center body case structure to rotationally support a shaft driven by said geared architecture;
- a bearing compartment passage structure in communication with said bearing structure through said front center body case structure, wherein said bearing compartment passage structure includes a hollow front center body strut;
- and
- a conditioning device in fluid communication with said bearing compartment passage structure.
3 more elements
A gas turbine engine comprising:
- a front center body case structure;
- a geared architecture at least partially supported by said front center body case structure;
- a bearing structure mounted to said front center body case structure to rotationally support a shaft driven by said geared architecture;
- a fan rotor bearing support structure at least partially supporting said bearing structure;
- and
- a bearing compartment passage structure in communication with said bearing structure through said front center body case structure, wherein said bearing compartment passage structure includes a hollow front center body strut in fluid communication with a passage in said fan rotor bearing support structure, and wherein, downstream of said passage in said fan rotor bearing support structure, passageways are arranged to direct fluid to at least one of (1) a spinner, and (2) an annular core flow path of said gas turbine engine.
3 more elements
Dependencies are inferred from the claim text.