Turbine engine gearbox
AssigneesUnited Technologies Corporation, The Ohio State University
InventorsMichael E. McCune, Ahmet Kahraman
Life of this patent
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Abstract
An example method of controlling performance of gearbox of a gas turbine engine includes establishing a gear characteristic of a plurality of double helical gears each disposed about a respective axis in a gearbox. Performance of the plurality of double helical gears is controlled by selecting a circumferential offset distance between a first plurality of gear teeth spaced apart from a second plurality of gear teeth on each of the plurality of double helical gears in response to the established gear characteristic.
Claims25
A method of controlling performance of gearbox of a gas turbine engine, comprising:
- establishing a gear characteristic of a plurality of double helical gears each disposed about a respective axis in a gearbox;
- and
- controlling performance of the plurality of double helical gears by selecting a circumferential offset distance between a first plurality of gear teeth spaced apart from a second plurality of gear teeth on each of the plurality of double helical gears in response to the established gear characteristic.
A turbine engine comprising:
- a fan;
- a compressor section;
- a combustor in fluid communication with the compressor section;
- a turbine section in fluid communication with the combustor;
- and
- a gearbox as recited in claim 15 coupled with the fan and the turbine section.
A gearbox for a gas turbine engine comprising:
- a plurality of double helical gears in meshed engagement, each of the plurality of double helical gears disposed about an axis, each of the plurality of double helical gears having a first plurality of gear teeth spaced apart from a second plurality of gear teeth, wherein the first plurality of gear teeth are circumferentially offset from the second plurality of gear teeth by a predetermined amount in response to a gear characteristic.
Dependencies are inferred from the claim text.