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US 2014/0178180 A1Published application
Fundamental gear system architecture
AssigneeUnited Technologies Corporation
InventorWilliam G. Sheridan
Life of this patent
Estimating the term…
Abstract
A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.
Claims20
A fan drive gear system for a gas turbine engine comprising:
- a gear system that provides a speed reduction between a fan drive turbine and a fan;
- and
- a lubrication system configured to provide lubricant to the gear system and to remove thermal energy produced by the gear system,
- wherein the lubrication system includes a capacity for removing thermal energy greater than zero and less than about 2% of power input into the gear system during operation of the engine.
1 more element
A gas turbine engine comprising:
- a fan including a plurality of fan blades rotatable about an axis;
- a fan drive turbine;
- a gear system that provides a speed reduction between the fan drive turbine and the fan, the gear system configured to transfer power input from the fan drive turbine to the fan at an efficiency greater than about 98% and less than 100%;
- and
- a lubrication system configured to provide lubricant to the gear system and to remove thermal energy from the gear system produced by the gear system during operation of the engine.
2 more elements
Dependencies are inferred from the claim text.