A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.

A gas turbine engine with an accessory gearbox. The accessory gearbox has a gear shaft rotatable about a gear shaft axis. The gear shaft has a first end drivingly engaged to a first accessory and a second end drivingly engaged to a second accessory. The gearbox has a spline made of a polymer material and rotatably coupled to one of the first and second ends of the gear shaft, and to a corresponding one of a first and second accessory shafts of the first and second accessories. The spline is rotatable about the gear shaft axis.

Provided are an exhaust duct, an exhaust duct assembly, and an aircraft using the exhaust duct. The exhaust duct has a structure that enables combustion gas to be diverged and discharged from an inlet end to a first outlet end and a second outlet end at respective sides of the exhaust duct. The exhaust duct includes a first housing including a first body forming an outer wall of the inlet end, and further includes second bodies respectively extending on respective sides from the first body and respectively forming the first outlet end and the second outlet end; a second housing spaced apart from the first body, forming an inner wall of the inlet end, and extending curvedly toward the second bodies; and a connection housing connecting the first housing to the second housing and including at least one recess portion recessed toward the inlet end.

A reverse flow gas turbine engine has a low pressure (LP) spool and a high pressure (HP) spool arranged sequentially in an axial direction. The LP spool comprises an LP compressor disposed forward of an LP turbine and drivingly connected thereto via an LP compressor gear train. The HP spool comprises an HP compressor in flow communication with the LP compressor, and an HP turbine disposed forward of the HP compressor and drivingly connected thereto via an HP shaft.

An aircraft gas turbine engine (10) comprises a main engine shaft (22) arranged to couple a turbine (17) and a compressor (13), the main engine shaft (22) defining an axial direction (9). The gas turbine engine (10) further comprises at least one radially extending offtake shaft (27) coupled to the main engine shaft (22), and a radially extending electric machine (25a, 25b) coupled to the radially extending offtake shaft (22).

An accessory system for a gas turbine engine having a drive shaft with an axis of rotation is provided. Also provided is a bearing housing assembly for coupling the drive shaft of an accessory having a first gear to a gear associated with the accessory system. The bearing housing assembly includes a mount including an interface to be coupled to the accessory and defining a central bore, and a lock cylinder configured to receive the drive shaft. The lock cylinder is movable relative to the central bore and the drive shaft to adjust a contact pattern between the first gear of the drive shaft and the gear of the accessory system.

A heat exchanger is provided. The heat exchanger includes one or more exchanger units that each have a core and manifolds. The core of an exchanger unit is formed by multiple unit cells coupled together in flow communication to create a flow distribution grid. Each unit cell has at a first primary channel, a second primary channel, a first secondary channel in flow communication with the first primary channel, and a second secondary channel in flow communication with the second primary channel. The first secondary channel traverses through the second primary channel and the second secondary channel traverses through the first primary channel. Each manifold includes two chambers for separating fluids flowing through the heat exchanger, with one chamber being in flow communication with one of the primary channels and having one or more tubes traversing therethrough to provide flow communication between the other primary channel and the other chamber.

Blades including integrated damping structures are disclosed herein. An airfoil to be disposed within a flow path of a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis comprising an airfoil body including a first face, a second face and a recessed portion formed in the second face, and an airfoil cap having a first surface, the airfoil cap disposed within the recessed portion, the first surface substantially flush with the second face.

A ferrite core coil device as a sensing element for a sensor device determining a rotational speed of a metallic rotatable object includes a coil having a first sector and a second sector and a ferrite core holding the coil. The ferrite core has a shape of a disk lacking a disk sector and defined by a contour of the disk and a chord of the disk. The chord forms a bending edge of the ferrite core. The first sector of the coil is not arranged on a bed of the ferrite core and the second sector of the coil is arranged on the bed. The first sector is bent around the bending edge at a bending angle with respect to the second sector.

An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, wherein the plurality of circuits of cooling channels are interwoven together; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling each of the plurality of circuits of cooling channels to at least one supply of cooling fluid, wherein, in each of the plurality of circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes into the circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels of the circuit of cooling channels.