Gas turbine engine with low stage count low pressure turbine
AssigneeUnited Technologies Corporation
InventorsGabriel L. Suciu, Brian D. Merry, Christopher M. Dye, Steven B. Johnson, Frederick M. Schwarz
Life of this patent
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Abstract
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section, and a low spool including a low pressure compressor section and a low pressure turbine. A high spool includes a high pressure compressor section. A gear arrangement is defined along an engine axis. The low spool is operable to drive the fan section through the gear arrangement. A mount system includes an aft mount configured to react at least a portion of a thrust load at an engine case generally parallel to an engine axis.
Claims20
A gas turbine engine comprising:
- a fan section;
- a low spool including a low pressure compressor section and a low pressure turbine, said low pressure compressor section including three (3) or more stages, and said low pressure turbine including three to six (3-6) stages;
- a high spool including a high pressure compressor section, said high pressure compressor section including eight to thirteen (8-13) stages;
- a gear arrangement defined along an engine axis, said low spool operable to drive said fan section through said gear arrangement;
- and
- a mount system including an aft mount configured to react at least a portion of a thrust load at an engine case generally parallel to an engine axis, said engine case defined about said engine axis.
A method of designing a gas turbine engine comprising:
- providing a fan section including a fan;
- providing a low spool including a low pressure compressor section and a low pressure turbine, said low pressure compressor section including three (3) or more stages, and said low pressure turbine including three to six (3-6) stages;
- providing a high spool including a high pressure compressor section and a high pressure turbine, said high pressure compressor section including thirteen (13) or fewer stages;
- providing a gear arrangement defined along an engine axis, said low spool operable to drive said fan section through said gear arrangement;
- and
- providing a mount system including an aft mount located aft of said high pressure turbine relative to said engine axis, said aft mount configured to react at least a portion of a thrust load at an engine case generally parallel to said engine axis.
Dependencies are inferred from the claim text.