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US 2014/0234078 A1Published application
Method for setting a gear ratio of a fan drive gear system of a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsWilliam G. Sheridan, Karl L. Hasel
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a fan section including a fan rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5. A bypass ratio is greater than about 11.0.
Claims30
A gas turbine engine comprising:
- a fan section including a fan rotatable about an axis;
- and
- a speed reduction device connected to the fan, wherein the speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.5, wherein a bypass ratio is greater than about 11.0.
A method of improving performance of a gas turbine engine comprising:
- determining fan tip speed boundary conditions for at least one fan blade of a fan section;
- determining rotor boundary conditions for a rotor of a low pressure turbine;
- and
- utilizing stress level constraints in the rotor of the low pressure turbine and the at least one fan blade to determine if the rotary speed of the fan section and the low pressure turbine will meet a desired number of operating cycles, wherein a bypass ratio is greater than about 6.0,
- wherein a speed reduction device connects the fan section and the low pressure turbine and includes a planetary gear ratio of at least about 2.5.
2 more elements
A fan drive gear module for a gas turbine engine comprising:
- a planetary fan drive gear system with a speed reduction ratio of at least 2.5, wherein the speed reduction device is configured to drive a fan section with a bypass ratio greater than about 11.0.
A method of designing a gas turbine engine comprising:
- selecting fan tip speed boundary conditions for at least one fan blade of a fan section of a gas turbine engine;
- selecting rotor boundary conditions for a rotor of a fan drive turbine of the gas turbine engine;
- determining stress level constraints in the rotor of the fan drive turbine and the at least one fan blade to determine if the rotary speed of the fan section and the fan drive turbine will meet a desired number of operating cycles, wherein a bypass ratio is greater than about 6.0;
- and
- connecting the fan section and the fan drive turbine through a speed reduction device that includes a planetary gear ratio of at least about 2.5.
2 more elements
Dependencies are inferred from the claim text.