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US 2012/0233982 A1Published application
Gas turbine engine compressor arrangement
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 includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages.
Claims20
A gas turbine engine comprising:
- a fan section;
- a low spool that includes a low pressure compressor section, said low pressure compressor section includes between four to eight (4-8) stages;
- a high spool that includes a high pressure compressor section said high pressure compressor section includes between eight to fifteen (8-15) stages, an overall compressor pressure ratio provided by the combination of said low pressure compressor section and said high pressure compressor;
- and
- a gear train defined along an engine centerline axis, said low spool operable to drive said fan section through said gear train.
2 more elements
A gas turbine engine comprising:
- a gear train defined along an engine centerline axis, said gear train defines a gear reduction ratio of greater than or equal to about 2.3;
- and
- a spool along said engine centerline axis which drives said gear train, said spool includes a three-stage low pressure turbine and a four to eight (4-8) stage low pressure compressor.
Dependencies are inferred from the claim text.