The present invention provides a bladed rotor wheel for a gas turbine engine comprising at least a rotatable forged disc, the rotatable forged disc comprising a front surface and a back surface, at least one rim surface, and a plurality of projections located on at least a portion of at least one of the front or back surface and/or on the rim surface; wherein the projections are 3D printed features protruding outwards from the front, back and/or rim surface; the projections are arranged forming a pattern so that a heat transfer capability is created at the front, back and/or rim surface; and the ratio of the distance between projections to the forged disc external radius is lower than 0.15. Furthermore, the present invention also provides a method for manufacturing a rotatable forged disc for a bladed rotor wheel.

A method for holding a part blank inside a holding assembly. The holding assembly includes a first holding portion. The first holding portion includes an inner cavity containing a fluid. The part blank and the first holding portion are at least partially manufactured by additive manufacturing. The holding method includes a heating of the holding assembly and the part blank to deform the first holding portion by fluid expansion in the inner cavity and to reduce a gap between the part blank and the holding assembly by expansion of the first holding portion in relation to the part blank.

A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.

Methods of forming sintered coatings are provided, along with the resulting coatings on a substrate. The sintered coating may comprise a rare earth compound and a sintering aid, with the rare earth compound has the formula: A.sub.1−bB.sub.bZ.sub.1−dD.sub.dMO.sub.6 where A is Al, Ga, In, Sc, Y, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Fe, Cr, Co, Mn, Bi, or a mixture thereof; b is 0 to about 0.5; Z is Hf, Ti, or a mixture thereof; D is Zr, Ce, Ge, Si, or a mixture thereof; d is 0 to about 0.5; and M is Ta, Nb, or a mixture thereof. The coating may be densified at a sintering temperature, such as 1300° C. to 1600° C.

A method of fabricating an airfoil preform for a turbine engine by selective melting on a bed of powder, the preform including an airfoil and a removable support secured to the airfoil, the airfoil being fabricated layer by layer from a first edge to a second edge of the airfoil, the method including fabricating the removable support and the airfoil, the removable support being for securing to a fabrication platform and to a portion of a face of the airfoil situated near the first edge and facing the fabrication platform. The face of the airfoil facing the fabrication platform includes a flat extending away from the face, the flat being present over a portion of the face that is situated outside the first edge, the support being secured to the flat or both to the flat and to the portion of the face that is situated outside the first edge.

The present disclosure generally relates to methods for additive manufacturing (AM) for fabricating multi-walled structures. A multi-walled structure includes a first wall having a first surface and a second wall having a second surface facing the first surface to define a passage having a width between the first surface and the second surface in a first direction. The multi-walled structure also includes an enlarged powder removal feature connecting the first wall and the second wall. The enlarged powder removal feature has an inner dimension greater than the width in the first direction and at least one open end in a direction transverse to the first width.

An airfoil vane includes an airfoil section which includes an outer wall that defines an internal cavity. A baffle is situated in the internal cavity. The baffle includes a leading edge portion and a trailing edge portion which is bonded to the leading edge portion at a joint. The leading edge portion and the trailing edge portion define an internal cavity therewithin. Both the leading edge portion and the trailing edge portion include a plurality of cooling holes which are configured to provide cooling air to the airfoil outer wall. The trailing edge portion is formed of sheet metal and the leading edge portion is formed of non-sheet-metal. A method of making a baffle for a vane arc segment and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.

A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.

A method for manufacturing a blade in composite material with added metal leading edge for gas turbine aeroengine, the method including producing a batch of plurality of blade bodies in composite material; creating a digital model of a blade body from a blade in the batch of plurality of blade bodies; creating a digital model of a theoretical final blade including a leading edge; generating a digital model of a leading edge from the digital model of a blade body and final blade model; manufacturing at least one leading edge via additive manufacturing from the generated leading edge digital model; bonding each manufactured leading edge onto a blade body from the batch of plurality of blade bodies.

The present invention relates to a turbine injector comprising an annular ring extending around a longitudinal axis and having a radially outer edge and a radially inner edge. The crown has a plurality of channels for fluidly connecting the radially outer edge to the radially inner edge, each channel extending in a radial plane of the ring and having an inlet opening near the outer edge and an outlet opening near the radially inner edge, the orientation of each channel varying progressively according to a tangential component between the inlet section of the inlet opening and the outlet section of the outlet opening.