Flexible support structure for a geared architecture gas turbine engine

• US 9,133,729 B1
• Filed: 09/20/2012
• Issued: 09/15/2015
• Est. Priority Date: 06/08/2011
• Status: Expired due to Fees

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: McCune, Michael E., Husband, Jason
• Primary Examiner(s): MCDOWELL, LIAM J
• Application Number:
  US13/623,309
• Time in Patent Office: 1,090 Days
• Field of Search: 415/122.1
• US Class Current: 1/1
• CPC Class Codes: F01D 25/164 Flexible supports; Vibration damping means associated with the bearing
• CPC Class Codes: F02C 7/20 Mounting or supporting of plant; Accommodating heat expansion or creep
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: F05D 2300/501 Elasticity
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine includes a flex mount for a Fan Drive Gear System defined by a lateral and transverse stiffness relatonship.

Claims

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.

2. The gas turbine engine as recited in claim 1, wherein said flexible support lateral stiffness is less than said frame lateral stiffness.

3. The gas turbine engine as recited in claim 1, wherein said flexible support transverse stiffness is less than said frame transverse stiffness.

4. The gas turbine engine recited in claim 1, wherein said flexible support lateral stiffness is less than said frame lateral stiffness, and said flexible support transverse stiffness is less than said frame transverse stiffness.

5. The gas turbine engine as recited in claim 1, wherein said gear system includes a gear mesh that defines a gear mesh lateral stiffness and a gear mesh transverse stiffness.

6. A gas turbine engine comprising:

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.

7. The gas turbine engine as recited in claim 6, wherein said flexible support lateral stiffness is less than said gear mesh lateral stiffness.

8. The gas turbine engine as recited in claim 6, wherein said flexible support transverse stiffness is less than said gear mesh transverse stiffness.

9. The gas turbine engine as recited in claim 6, wherein said flexible support lateral stiffness is less than said gear mesh lateral stiffness, and said flexible support transverse stiffness is less than said gear mesh transverse stiffness.

10. The gas turbine engine as recited in claim 6, wherein said frame defines a frame lateral stiffness and a frame transverse stiffness.

11. A gas turbine engine comprising:

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.