FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE
First Claim
Patent Images
1. A gas turbine engine, comprising:
- a fan shaft driving a fan having fan blades;
a fan shaft support that supports said fan shaft;
a gear system connected to said fan shaft, said gear system includes a ring gear defining a ring gear transverse stiffness, a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3; and
wherein said ring gear transverse stiffness is less than 20% of said gear mesh transverse stiffness.
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Abstract
A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades, a fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear transverse stiffness, a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. The ring gear transverse stiffness is less than 20% of the gear mesh transverse stiffness.
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Citations
30 Claims
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1. A gas turbine engine, comprising:
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a fan shaft driving a fan having fan blades; a fan shaft support that supports said fan shaft; a gear system connected to said fan shaft, said gear system includes a ring gear defining a ring gear transverse stiffness, a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3; and wherein said ring gear transverse stiffness is less than 20% of said gear mesh transverse stiffness. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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15. A gas turbine engine, comprising:
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a fan shaft driving a fan having fan blades; a fan shaft support that supports said fan shaft; a gear system connected to said fan shaft, said gear system includes a ring gear defining a ring gear transverse stiffness, a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3; wherein said ring gear transverse stiffness is less than 20% of said gear mesh transverse stiffness; and a low fan pressure ratio of less than 1.45 and said low fan pressure ratio is measured across the fan blades alone. - View Dependent Claims (16, 17, 18, 19)
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20. A gas turbine engine, comprising:
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a fan shaft driving a fan having fan blades; a fan shaft support that supports said fan shaft; a gear system connected to said fan shaft, said gear system includes a ring gear defining a ring gear transverse stiffness and a ring gear lateral stiffness, a gear mesh defining a gear mesh transverse stiffness and a gear mesh lateral stiffness, and a reduction ratio greater than 2.3; and wherein said ring gear transverse stiffness is less than 20% of said gear mesh transverse stiffness and said ring gear lateral stiffness is less than 12% of said gear mesh lateral stiffness. - View Dependent Claims (21, 22, 23, 24, 25, 26, 27, 28, 29, 30)
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Specification