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 variable guide vane (VGV) assembly, has: vanes distributed about a central axis, each of the vanes having an airfoil extending between first and second stems, the vanes rotatable about vane axes extending between the first and second stems; and a bushing ring supporting the first stems of the vanes, the bushing ring defining circumferentially distributed pockets receiving the first stems of the vanes, the bushing ring having a first ring body extending circumferentially around the central axis, a second ring body extending circumferentially around the central axis and removably secured to the first ring body, the second ring body defining at least one tab projecting axially to axially overlap at least a portion of the first ring body and defining a contact plane therebetween, and at least one locking member extending radially through the contact plane to removably secure the first ring body and the second ring body together.

A vane assembly for use with a gas turbine engine includes an outer wall, an inner wall, and a plurality of airfoils. The outer wall and the inner wall extend at least partway about an axis. At least one of the airfoils is coupled with the outer end wall and the inner end wall to transmit force loads through the vane assembly.

A tooling for injecting a polymer resin into a fibrous preform for the manufacture of a revolution part in composite material including a barrel shape with an inside diameter of smaller diameter delimiting the revolution part into an upstream portion and a downstream portion of the inside diameter, the upstream portion including a back-draft intermediate portion, injection tooling wherein, to allow a demolding of the barrel-shaped part once the injection and the polymerization of the polymer resin are carried out, the injection tooling includes on the one hand a frustoconical drum comprising a first drum portion in direct contact with an inner surface of the portion of the revolution part downstream of the inside diameter and a second drum portion and on the other hand a segmented insert whose outer surface matches an inner surface of the portion of the revolution part upstream of the inside diameter.

A gas turbine casing made of composite material from fiber reinforcement densified by a matrix. The casing includes at least one stiffener portion extending at a radius greater than the radius of upstream and downstream portions of the casing that are adjacent to the stiffener portion so as to form an annular recess in the inside surface of the casing.

A service tube assembly comprises a service tube having a threaded end portion and a shoulder. The outer shoulder has a conical surface converging in a direction away from the threaded end portion. The threaded end portion is threadably engaged with a mating part. The mating part has a seat surface which cooperates with the shoulder of the service tube to form a conical seat. The assembly further includes a locking member having an outer conical surface complementary to the conical seat. A mechanical fastener is provided for releasably holding the locking member against the conical seat.

The present invention thus proposes an inlet cone for an aircraft turbine engine, comprising a frustoconical body and a tip made from elastically deformable material fixed to an end of smaller diameter of said body, the tip comprising a top configured to be situated on an axis of rotation of the cone and a fastening base for attachment on said end of said body. Said base extends in a connecting plane P. Said connecting plane P is inclined relative to said axis of rotation. Said base has a generally circular or oval shape. According to the invention, said connecting plane P is inclined relative to a transverse plane T perpendicular to said axis of rotation.

A turbofan engine including an exhaust casing traversed by a primary flow and surrounded by a secondary flow and an outlet cone carried by this exhaust casing, the exhaust casing and the outlet cone together defining an internal space. The exhaust casing includes a hollow radial arm traversing the primary flow in order to convey part of the secondary flow so as to form a cooling flow for supplying the internal space, and the outlet cone is terminated by an opening for discharging the cooling flow.

The invention is related to the gas turbine stators of the gas turbine engines applied in aviation. The gas turbine stator, in the outer housing of which sectors of the split honeycomb ring (made as double-layer one) are installed with support elements on the front and rear axial ends of the sector. In this invention, the layer of the sector facing the outer housing is made U-shaped in the plane, the support elements are made as separate rotary bodies distributed uniformly along the circumference and the front support elements (on the gas flow direction) are larger than rear ones in terms of geometrical dimensions by factor 1.1 . . . 1.5. Therefore, the implementation of the invention proposed with the characteristic features above, in conjunction with the known features of the invention claimed enables reduction of the gas turbine stator weight and improvement its reliability without compromising the turbine efficiency.

A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier. The turbine outer case is arranged circumferentially around an axis. The blade track segment includes an arcuate runner that extends circumferentially partway around the axis to define a gas path boundary of the turbine shroud assembly and an attachment feature that extends radially outward from the runner. The carrier is configured to couple the blade track segment to the turbine outer case.