Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A fitting according to an exemplary aspect of the present disclosure includes, among other things, a main body portion having a first axial end and a second axial end opposite the first axial end, an inlet provided at the first axial end, and an outlet adjacent the second axial end. The outlet includes a plurality of circumferentially spaced-apart slots formed through the main body portion, and each slot has an area within a range of 0.52 and 0.59 square inches.

Abstract: An oil lubrication system is provided. The oil lubrication system may comprise an oil pump, a conduit fluidly coupled to the oil pump, and a damper fluidly coupled to the conduit. The damper may further comprise a volume configured to receive oil in response to a pulse event. A heat exchanger may also be fluidly coupled to the conduit. In various embodiments, the damper may comprise a spherical volume. The damper may be fluidly coupled to the conduit between the oil pump and the heat exchanger. An adapter may be mechanically coupled between the conduit and the damper. The adapter may comprise a passage in fluid communication with the conduit and the damper. The damper may further comprise a membrane. A gas or compressible fluid may be disposed in the damper on a first side of the membrane. The membrane may be configured to separate the gas from the oil.

Abstract: A gas turbine bypass flow arrangement comprises an outer housing and an inner housing, an outer bypass duct defined between the outer housing and the inner housing and an inner bypass duct defined inwardly of the inner housing. A first heat exchanger is positioned at an upstream location within the outer bypass duct and a second heat exchanger is positioned within the inner bypass duct at an upstream location. A downstream heat exchanger is positioned to be in the path of air downstream of the second heat exchanger in the inner bypass duct. Air flowing across the downstream heat exchanger passes from the inner bypass duct into the outer bypass duct. A gas turbine engine is also disclosed.

Abstract: Aspects of the disclosure are directed to a screen configured for use in association with a cooler of an aircraft, the screen comprising: a first portion arranged as a grid and located in a line-of-sight of the cooler with respect to a fluid inlet, and a second portion located out of the line-of-sight of the cooler with respect to the fluid inlet, wherein the second portion is grid-free.