FLEXIBLE SUPPORT STRUCTURE FOR A GEARED ARCHITECTURE GAS TURBINE ENGINE
First Claim
1. A gas turbine engine, comprising:
- a fan shaft driving a fan having fan blades;
a fan shaft support that supports said fan shaft, said fan shaft support defining a fan shaft support transverse stiffness;
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 flexible support supporting said gear system defining a flexible support transverse stiffness, wherein said flexible support transverse stiffness is less than 20% of said fan shaft support transverse stiffness.
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Accused Products
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. The fan shaft support defines a fan shaft support transverse stiffness. A gear system connected to the fan shaft 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. A flexible support supports said gear system and defines a flexible support transverse stiffness. The flexible support transverse stiffness is less than 20% of the fan shaft support 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, said fan shaft support defining a fan shaft support transverse stiffness; 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 flexible support supporting said gear system defining a flexible support transverse stiffness, wherein said flexible support transverse stiffness is less than 20% of said fan shaft support transverse stiffness. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16)
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17. 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, said fan shaft support defining a fan shaft support transverse stiffness; 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 gear mesh lateral 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 flexible support supporting said gear system defining a flexible support transverse stiffness and a flexible support lateral stiffness, wherein said flexible support transverse stiffness is less than 20% of said fan shaft support transverse stiffness, and said flexible support lateral stiffness is less than 8% of said gear mesh lateral stiffness. - View Dependent Claims (18, 19, 20, 21, 22, 23, 24, 25, 26, 27, 28, 29, 30)
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Specification