United Technologies Corporation

Raytheon Technologies Corporation

Sunil Sharma

Todd A Davis

John R Otto

Brian P Cigal

James B Coffin

Richard E Domonkos

A gear assembly support for a gas turbine engine includes a first portion engageable to a case of the gas turbine engine and a second portion configured for supporting a gear assembly. The support includes a torque reacting portion for transferring torque from the second portion to the first portion, a forward flange disposed forward of the torque reacting portion, the forward flange defining a first interface to the case and an aft flange disposed aft of the torque reacting portion, the aft flange defining a second interface to the case.

Adjustable flange material and torque path isolation for splined fan drive gear system flexible support

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 for adjusting the snap fit independent of the torque transfer portions.

Fan drive gear system flexible support features

A fan drive gear system for a gas turbine engine includes a carrier that supports circumferentially arranged gears. A torque frame has circumferentially arranged fingers with each finger including a bore having a bore axis. A bushing is arranged in each bore and provides an aperture. At least one bushing has a bushing axis offset from the bore axis. A pin is disposed in the aperture and secures the carrier to the torque frame.

Torque frame bushing arrangement for gas turbine engine fan drive gear system

A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes a first mount feature. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes a second mount feature that cooperates with the first mount feature for transferring torque there between. A method of disassembling a front architecture of a gas turbine engine includes the steps of accessing forward-facing fasteners that secure a central body support to a flex support, wherein the flex support includes a geared architecture supported thereon, removing the fasteners, and decoupling first and second mount features respectively provided on the central body support and the flex support.

Gas turbine engine front center body architecture

A gas turbine engine includes a central body support that provides an inner annular wall for a core flow path. The central body support includes first splines. A geared architecture interconnects a spool and a fan rotatable about an axis. A flex support interconnects the geared architecture to the central body support. The flex support includes second splines that intermesh with the first splines for transferring torque there between.

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Rocky Hill, CT, United States of America

Sunil Sharma