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US 2013/0259651 A1Published application
Differential geared architecture for gas turbine engine
OwnerDaniel Bernard Kupratis, Frederick M. Schwarzinventors
Life of this patent
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Abstract
A gas turbine engine includes first and second shafts rotatable about a common axis. A first turbine section is supported on the first shaft. Second compressor and turbine sections are supported on the second shaft. The gas turbine engine includes a fan, a first compressor section, and a differential gear train that couples the fan and the first compressor section to the first shaft.
Claims20
A gas turbine engine comprising:
- first and second shafts rotatable about a common axis;
- a first turbine section supported on the first shaft;
- second compressor and turbine sections supported on the second shaft;
- a fan;
- a first compressor section;
- and
- a differential gear train coupling the fan and the first compressor section to the first shaft.
4 more elements
A gas turbine engine comprising:
- first and second shafts rotatable about a common axis;
- a first turbine section supported on the first shaft;
- second compressor and turbine sections supported on the second shaft;
- a fan;
- a first compressor section;
- a differential gear train coupling the fan and the first compressor section to the first shaft, the differential gear train is an epicyclic gear train including a sun gear, planetary gears arranged about and intermeshing with the sun gear, and a ring gear circumscribing and intermeshing with the planetary gears, the planetary gears are supported by a carrier, the carrier rotationally fixed to the first shaft;
- and
- wherein the first and second shafts respectively provide low and high spools, and the first compressor and turbine sections are low pressure compressor and turbine sections, and the second compressor and turbine sections are high pressure compressor and turbine sections.
5 more elements
Dependencies are inferred from the claim text.