Fundamental gear system architecture
First Claim
Patent Images
1. A fan drive gear system for a gas turbine engine comprising:
- a gear system configured to provide a speed reduction between a fan drive turbine and a fan;
a mount flexibly supporting portions of the gear system radially extending from a static structure of the gas turbine engine with respect to a central axis to accommodate radial movement between the gear system and the static structure; and
a lubrication system configured to provide lubricant to the gear system and remove thermal energy produced by the gear system, wherein the lubrication system includes a maximum capacity for removing thermal energy from the gear system greater than zero and less than about 2% of power input into the gear system during operation of the engine.
1 Assignment
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Accused Products
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.
60 Citations
20 Claims
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1. A fan drive gear system for a gas turbine engine comprising:
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a gear system configured to provide a speed reduction between a fan drive turbine and a fan; a mount flexibly supporting portions of the gear system radially extending from a static structure of the gas turbine engine with respect to a central axis to accommodate radial movement between the gear system and the static structure; and a lubrication system configured to provide lubricant to the gear system and remove thermal energy produced by the gear system, wherein the lubrication system includes a maximum capacity for removing thermal energy from the gear system greater than zero and less than about 2% of power input into the gear system during operation of the engine. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A gas turbine engine comprising:
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a fan including a plurality of fan blades rotatable about an axis; a compressor section; a combustor in fluid communication with the compressor section; a fan drive turbine in communication with the combustor; a gear system is configured to;
(a) provide a speed reduction between the fan drive turbine and the fan; and
(b), transfer power input from the fan drive turbine to the fan at an efficiency greater than about 98% to less 100%;a mount flexibly supporting the gear system radially extending from a static structure of the engine with respect to a central axis to accommodate radial movement between the gear system and the static structure; and a lubrication system configured to provide lubricant to the gear system and remove removing thermal energy from the gear system produced by the gear system. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17, 18, 19, 20)
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Specification