Fan drive gear system flexible support features
AssigneeUnited Technologies Corporation
InventorsJohn R. Otto, Sunil Sharma
Life of this patent
Estimating the term…
Abstract
A disclosed gear assembly support for a gas turbine engine includes a first portion configured for attachment to a case of the gas turbine engine and a second portion configured for supporting a gear assembly. The support further includes a snap portion defining a fit within the case. The snap portion includes a tunable feature for adjusting a fit within the case. A torque reacting portion of the support transfers torque from the second portion to the first portion separate from the snap portion and include separately tunable features fore adjusting the snap fit independent of the torque transfer portions.
Claims17
A gear assembly support for a gas turbine engine comprising:
- a first portion configured for attachment to a case of the gas turbine engine;
- a second portion configured for supporting a gear assembly;
- a snap portion defining a fit within the case, the snap portion including a tunable feature for adjusting the fit within the case;
- and
- a torque reacting portion for transferring torque from the second portion to the first portion independent of the snap portion.
A gas turbine engine comprising:
- a fan including a plurality of fan blades rotatable about an axis A;
- a compressor section;
- a combustor in fluid communication with the compressor section;
- a turbine section in fluid communication with the combustor;
- a geared architecture driven by the turbine section for rotating the fan about the axis A;
- and
- a support member that supports the geared architecture, the support member including a first portion configured for attachment to a case, a second portion configured for supporting the geared architecture, a snap portion including a tunable feature for adjusting a fit within the case, and a torque reacting portion for transferring torque from the second portion to the first portion independent of the snap portion.
A method of supporting a gear assembly within a gas turbine engine comprising:
- defining a fit between a support member and a static structure within the gas turbine engine with a snap portion;
- defining a torque transfer path between a first portion configured for attachment to the static structure and a second portion configured for attachment to the gear assembly independent of the snap portion;
- attaching the gear assembly to the second portion;
- and
- attaching the support member to the static structure such that the snap portion positions the support member relative to the static structure.
Dependencies are inferred from the claim text.