Rtx Corporation

Raytheon Technologies Corporation

Nicholas J Lawliss

Zhiqiang Wang

Enzo DiBenedetto

Colin J Kling

John P Virtue

Jackson David Johnson

Xuejun Liu

Adam David Vanover

Paul Boules

Kalpendu J Parekh

Liam P Sullivan

Jr John P Virtue

A gas turbine engine has: a compressor; a combustor; a turbine; a generator in a centerbody and coupled to the turbine; a case; a plurality of struts mounting the centerbody to the case; and wiring passing through at least one of the struts to the generator. The centerbody has: a first member having a forward rim and at least one recess extending aft from an opening at the forward rim, the wiring passing through the recess; at least a second member blocking the opening; and a threaded fastener securing the strut to the second member.

Turbine engine centerbody generator

A counter weight for use with a rotor module, including: a root portion; a main body portion that extends away from the root portion; a pair of side portions each extending from opposite sides of the main body portion; and at least one plate secured to one of the opposite sides of the main body portion in order to adjust a weight of the counter weight.

Apparatus and method for partially bladed rotor test

A rotor module, including: a blade cluster of a plurality of blades secured to a rotor disk of the rotor module; and counter weights secured to the rotor disk, wherein the counter weights cause a center of gravity of the plurality of blades to be zeroed out with respect to an axis 'O' of the rotor disk and wherein the counter weights cause a moment of inertia Jx about an X axis of the rotor disk is equal to a moment of inertia Jy about a Y axis of the rotor disk when the rotor module is rotated about the axis “O”.

A rotor assembly is provided that includes a rotor disk, a rotor blade and a rotor spacer. The rotor disk includes a slot. The rotor blade includes a blade root arranged within the slot. The root spacer is arranged within the slot between the rotor disk and the blade root. The root spacer is configured as or otherwise includes a cellular structure with a plurality of internal cells.

Deformable root spacer for a gas turbine engine rotor blade

Fan assemblies for gas turbine engines include a rotor disk having a plurality of lugs with a plurality of slots defined between adjacent lugs. A fan platform is configured to be mounted to a lug of the plurality of lugs, the fan platform having a forward tab and an aft tab. An aft retention ring is configured to be fixedly attached to an aft side of the rotor disk and has a platform retention hook for receiving the aft tab of the fan platform. A forward retention ring is configured to be fixedly attached to a forward side of the rotor disk, the forward retention ring having a tab hook configured to attach the forward retention ring to the lug of the plurality of lugs and retain the forward tab of the fan platform to the lug of the plurality of lugs.

Platform for an airfoil of a gas turbine engine

A split ring seal has: a first circumferential end and a second circumferential end; an inner diameter surface and an outer diameter surface; a first axial end face and a second axial end face. A circumferentially distributed first plurality of open channels are along the first axial end face. A circumferentially distributed second plurality of open channels are along the second axial end face.

Piston seal ring

Rotor systems including an engine shaft, a forward hub, a rear hub, a rotor disk arranged between the forward hub and the rear hub, and a seal tube configured to define a forward hub compartment and a rear hub compartment. The forward hub compartment is defined forward of the rotor disk and the rear hub compartment is defined aft of the rotor disk. The seal tube is connected at a forward end to at least one of the rotor disk and the engine shaft and at a rear end to at least one of the rear hub and the engine shaft and the seal tube includes at least one axial compliance element configured to enable axial extension and compression of the seal tube in an axial direction along the engine shaft.

Growing community of inventors

West Hartford, CT, United States of America

Nicholas J Lawliss