Flexible support structure for a geared architecture gas turbine engine
First Claim
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1. A gas turbine engine comprising:
- a fan shaft;
at least one bearing supporting the fan shaft;
a frame which supports said fan shaft, said frame defines a frame lateral stiffness and a frame transverse stiffness;
a gear system which drives said fan shaft;
a flexible support which at least partially supports said gear system, said flexible support defines a flexible support lateral stiffness with respect to said frame lateral stiffness and a flexible support transverse stiffness with respect to said frame transverse stiffness; and
an input coupling to said gear system, said input coupling defines an input coupling lateral stiffness with respect to said frame lateral stiffness and an input coupling transverse stiffness with respect to said frame transverse stiffness.
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Abstract
A gas turbine engine includes a flex mount for a Fan Drive Gear System defined by a lateral and transverse stiffness relatonship.
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Citations
11 Claims
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1. A gas turbine engine comprising:
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a fan shaft; at least one bearing supporting the fan shaft; a frame which supports said fan shaft, said frame defines a frame lateral stiffness and a frame transverse stiffness; a gear system which drives said fan shaft; a flexible support which at least partially supports said gear system, said flexible support defines a flexible support lateral stiffness with respect to said frame lateral stiffness and a flexible support transverse stiffness with respect to said frame transverse stiffness; and an input coupling to said gear system, said input coupling defines an input coupling lateral stiffness with respect to said frame lateral stiffness and an input coupling transverse stiffness with respect to said frame transverse stiffness. - View Dependent Claims (2, 3, 4, 5)
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6. A gas turbine engine comprising:
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a fan shaft; a frame which supports said fan shaft; a gear system which drives said fan shaft, said gear system includes a gear mesh that defines a gear mesh lateral stiffness and a gear mesh transverse stiffness; a flexible support which at least partially supports said gear system, said flexible support defines a flexible support lateral stiffness with respect to said gear mesh lateral stiffness and a flexible support transverse stiffness with respect to said gear mesh transverse stiffness; and an input coupling to said gear system, said input coupling defines an input coupling lateral stiffness with respect to said gear mesh lateral stiffness and an input coupling transverse stiffness with respect to said gear mesh transverse stiffness. - View Dependent Claims (7, 8, 9, 10)
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11. A gas turbine engine comprising:
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a fan shaft; a frame which supports said fan shaft, said frame defines at least one of a frame lateral stiffness and a frame transverse stiffness; a plurality of gears which drive said fan shaft; a flexible support which at least partially supports said plurality of gears, said flexible support defines at least one of a flexible support lateral stiffness with respect to said frame lateral stiffness and a flexible support transverse stiffness with respect to said frame transverse stiffness; and an input coupling to said plurality of gears, said input coupling defines at least one of an input coupling lateral stiffness with respect to said frame lateral stiffness and an input coupling transverse stiffness with respect to said frame transverse stiffness, and said at least one of a frame lateral stiffness and a frame transverse stiffness is greater than said at least one of a flexible support lateral stiffness and a flexible support transverse stiffness, and also greater than said at least one of an input coupling lateral stiffness and an input coupling transverse stiffness.
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Specification