United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporaation

Ryan K Snyder

Eric J Heims

Kari L Kisselbrack

Kurt J Sobanski

Thomas Bruce Avis

Andre Herman Troughton

Michael Dreher

Steven Michael Danley

William K Ackermann

Francis Parnin

Robert Howard

Bruce D Paradise

Keven G Van Duyn

Marc R Sauerhoefer

Michael R Thomas

Pellegrino J Pisacreta

Judith F Brooks

Mark W Colebrook

James P Chasse

Vito Guardi

Curtis J Ruckey

Jesse Ian Berube

Stephanie Ernst

Alexander P Girgenti

Ahmad Sajad Delawar

Peter C Tiziani

Alexander Trabal

Antonio J Portelinha

Jimmy C Pujols

James D Marshall

Thomas Livingston

James M McPherson

Ping Su

Fernando Quinones

Gabriel Rivera

Michael C O'Brien

Ryan Timothy Matte

Jose A Carrion

Jeffrey Honan

An assembly for mounting an auxiliary component to an engine case of a gas turbine engine includes a support bracket, the support bracket having a first end configured for attachment to a first flange of the engine case, a second end configured for attachment to a second flange of the engine case, and an intermediate portion located intermediate the first end and the second end; a bearing member disposed within the intermediate portion; a locator disposed within the bearing member; and a frangible ring member disposed between the support bracket and the bearing member, wherein the frangible ring member comprises a porous metal material (e.g., frothed aluminum or thin-walled honey combed aluminum or steel). The frangible material thickness can be set to absorb FBO energy while limiting system displacement during and post FBO event, thus reducing the energy transmitted to an auxiliary component (e.g., a gearbox housing).

Frangible gearbox center guide support systems and methods

An assembly for mounting an auxiliary component to an engine case for a gas turbine engine includes a support bracket and a locator. The locator includes a fusible guide pin extending at least partially into a first aperture disposed in the support bracket, and a catcher pin extending at least partially into a second aperture disposed in the support bracket. The fusible guide pin is configured to fracture to absorb energy while the catcher pin limits system displacement during and post an overload event, thus reducing the energy transmitted to the auxiliary component (e.g., a gearbox housing). The locator can further include an anti-rotation pin extending from the plate member and configured to be received by the auxiliary component. The anti-rotation pin prevents rotation of the locator, about a third pin of the locator, with respect to the auxiliary component when the fusible guide pin is broken.

Fusible gearbox center guide support with catcher pin and anti-rotation pin systems and methods

An assembly for mounting an auxiliary component to an engine case for a gas turbine engine includes a support bracket and a locator comprising a guide pin extending at least partially into a first aperture disposed in the support bracket, and a catcher pin extending at least partially into a second aperture disposed in the support bracket. A first frangible ring member is disposed between the support bracket and the catcher pin, wherein the frangible ring member comprises a porous metal material (e.g., frothed aluminum or thin-walled honey combed aluminum or steel). The first frangible ring member is configured to collapse to absorb energy while limiting system displacement during and post an overload event, thus reducing the energy transmitted to the auxiliary component (e.g., a gearbox housing). The guide pin can be fused such that the catcher pin limits movement of the auxiliary component when the guide pin breaks.

Fusible gearbox center guide support with frangible catcher pin systems and methods

A wave guide assembly for a control and diagnostic system for a machine includes a housing defining an exterior surface and an internal cavity extending between distal ends. At least one wave guide within the internal cavity defines a wave propagation passage for at least one wave form signal. At least one conductor within the internal cavity is separate from the wave guide. A control and diagnostic system for a machine and a gas turbine engine are also disclosed.

Wave guide with electric power conduit

A wave guide assembly for a control and diagnostic system for a machine, the wave guide assembly includes a housing defining an exterior surface and an internal cavity extending between distal ends. A wave guide is defined within the internal cavity. At least one open conduit is defined within the internal cavity providing a space for routing conductors through the housing. A fluid passage is defined within the internal cavity separate from the wave guide. A control and diagnostic system for a machine and a gas turbine engine are also disclosed.

Wave guide with fluid passages

A clamp assembly includes a grommet with a non-circular aperture with a multiple of crush apertures defined at least partially around the non-circular aperture. A method of supporting a wiring harness within a clamp assembly for a gas turbine engine includes installing a wiring harness through a non-circular aperture with a multiple of crush apertures defined in an arc at least partially around a major axis of the non-circular aperture; and compressing the grommet to compress the multiple of crush apertures to retain the wiring harness within the non-circular aperture.

Clamp assembly for electrical wiring harnesses

A gas turbine engine comprises a compressor, a combustor and a turbine. A housing for the gas turbine engine includes a mount member to define a vertically upper location. Sides of the engine are defined on opposed sides of the mount, with a fuel filter, a fuel pump and a fuel flow meter being positioned on a first side and an oil pump, an oil filter and an oil tank positioned on a second of the sides.

Gas turbine engine accessory architecture

A distributed electrical system includes a plurality of engine components each in electrical communication with one of a plurality of docking stations. An electronic engine control is positioned remote from the engine components and is configured to communicate wirelessly with each of the plurality of engine components.

Distributed electrical architecture for a gas turbine engine

A gas turbine engine includes a bearing compartment with a bottom disposed opposite a top. An outlet is formed in the bottom of the bearing compartment. A seal is positioned between the bottom of the bearing compartment and the top of the bearing compartment. A scavenge line is connected to the outlet. The scavenge line forms a fluid trap that extends in a first direction from the outlet and the bottom of the bearing compartment and then extends in a second direction to a position disposed vertically between the bottom of the bearing compartment and the seal.

Internal tube oil coke prevention geometry

An adapter for a gas turbine engine has a first portion with a control module mount interface. A second portion with a sensor mount interface defines a sensor mount position relative to a control module. A connecting body connects the first and second portions such that the second portion provides a re-orientated sensor mount position relative to the control module. A lubrication system for a gas turbine engine is also disclosed.

Sensor adapter

A single, unitary fuel/oil manifold for a gas turbine engine is provided which comprises one or more interfaces for mounting various fuel system and lubricating system components directly to the fuel/oil manifold. The fuel/oil manifold also defines fluid passages for transferring fuel or lubricant from one component to another component. Packing numerous fuel system and lubricating system components within the fuel/oil manifold reduces cost and weight and simplifies maintenance.

Fuel/oil manifold

Systems and methods are disclosed herein for an electrical harness. The electrical harness may include a high temperature segment, a low temperature segment, and a transition segment between the high temperature segment and the low temperature segment. The electrical harness may include a conductor disposed within the electrical harness.

Hybrid electrical harness and method of making

An oil control module for a gas turbine engine is provided comprising a housing on which numerous components of a lubricating system are mounted. The components may include a variable oil reduction valve/shuttle valve, a main oil pressure sensor, a main oil temperature sensor, a main oil filter delta pressure sensor, an oil debris monitor, a lube filter, an active oil damper valve, a cool oil orifice, a knock down orifice and a lube trim orifice. By packing numerous lubricating system components onto or within a housing located adjacent to the gas turbine engine, the oil control module reduces cost and weight and simplifies the maintenance of the lubricating system.

Oil control module

Growing community of inventors

Glastonbury, CT, United States of America

Ryan K Snyder