A combustion chamber suitable in particular for use in a rocket engine comprises a combustion space, a first wall enclosing the combustion space and cooling duct fins, which extend from a surface of the first wall and separate adjacent cooling ducts from one another. At least one of the cooling duct fins has at its end facing away from the surface of the first wall a bent section, which at least partially covers a cooling duct adjacent to the cooling duct fin.

A barrier device is provided for an inlet cowl for an aircraft engine including an inner barrel circumferentially surrounding an opening in the inlet cowl formed along an axis of rotation of the aircraft engine, through which air passes to the aircraft engine, the inner barrel including a face sheet disposed on a radially inward side of the inner barrel relative to the axis. The barrier device includes a containment doubler of the inner barrel, disposed on a radially outward side of the inner barrel, and a blade fragment barrier including one or more strips disposed between the containment doubler and the face sheet, so as to extend circumferentially at least partially around the opening and to occupy a radial distance between the containment doubler and the face sheet.

An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a split case structure. The split case structure includes a first wall, a second wall, a first case segment and a second case segment. The first wall extends axially along and circumferentially about an axial centerline. The second wall extends axially along and circumferentially about the axial centerline. The second wall is radially outboard of and axially overlaps the first wall. The first case segment is configured to form a first portion of the first wall and a first portion of the second wall. The second case segment is configured to form a second portion of the first wall and a second portion of the second wall. The second case segment is circumferentially adjacent and attached to the first case segment at a joint.

A process for manufacturing a turbomachine part coated with a thermal barrier, includes manufacturing the part by additive manufacture; electrophoretic depositing the part of a layer including particles of a ceramic material; consolidating the layer by heat treatment to obtain a ceramic coating.

A method for forming a QCr0.8 alloy tapered cylindrical ring, including: heating a standard QCr0.8 alloy cylindrical part followed by upsetting and stretching at least twice to obtain a primary blank; heating the primary blank followed by upsetting and chamfering to obtain a secondary blank, where a diameter of a top end is greater than that of a bottom end; subjecting the secondary blank to backward extrusion to form a preform; machining the preform to remove a flash and a bottom residue; subjecting a bottom end of the preform to local bulging to enable a shape and a size thereof to match that of a drive roller in a forming tooling, so as to form a profiled ring blank; and rolling the profiled ring blank by a radial-axial ring rolling machine with the forming tooling to form the tapered cylindrical ring.

A method is provided for fabricating a coolant channel closeout jacket on a structure having coolant channels formed in an outer surface thereof. A line of tangency relative to the outer surface is defined for each point on the outer surface. Linear rows of a metal feedstock are directed towards and deposited on the outer surface of the structure as a beam of weld energy is directed to the metal feedstock so-deposited. A first angle between the metal feedstock so-directed and the line of tangency is maintained in a range of 20-90°. The beam is directed towards a portion of the linear rows such that less than 30% of the cross-sectional area of the beam impinges on a currently-deposited one of the linear rows. A second angle between the beam and the line of tangency is maintained in a range of 5-65°.

One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.

A method of fabricating a combustor thermal shield comprising a combustor panel, a cooling feature, and an attachment feature, the combustor thermal shield to be used in a gas turbine engine combustor, includes shaping a sheet of material used to form the combustor panel. The method also includes additively manufacturing the cooling feature onto the sheet of material forming the combustor panel. The method also includes attaching the attachment feature to the sheet of material forming the combustor panel. The method also includes curving the sheet of material forming the combustor panel to achieve a curve profile according to a design of the gas turbine engine combustor.

A center body attachment system may comprise an engine flange, a center body mounting assembly, and a center body. The center body mounting assembly may retain the center body and the engine flange in slidable engagement, whereby the engine flange and the center body may expand and contract at different rates. The center body may comprise a housing. The housing may comprise a floating counter bore, a spring supporting the floating counter bore, and a slider radially inward of the floating counter bore and retained within the housing by a nut.

A weldment member for a gas turbine engine including a forward welding member and an aft welding member. The forward welding member has an annular shape with a forward welding face formed at one end. The forward welding face has a forward radiographic marking hole formed therein. The aft welding member has an annular shape with an aft welding face formed at one end. The aft welding face has an aft radiographic marking hole formed therein. The forward welding face is aligned with the aft welding face and the forward radiographic marking hole is angularly offset from the aft radiographic marking hole.