A 3D printing method providing an improved manufacturing process by providing a plurality of layers forming at least a part of the component, wherein the plurality of layers contains at least one first layer part and at least one second layer part, wherein the at least one first layer part and the at least one second layer part have been manufactured with different manufacturing speeds.

A method of additive manufacturing includes a) providing a component geometry with a hole and, b) selectively irradiating a powder bed with an energy beam according to the geometry in a layerwise manner, wherein in layers of the component including the hole, the respective regions which define the hole are irradiated with the energy beam such that a supporting structure is generated in the hole having a lower rigidity than a structure of the component. The supporting structure is used for counteracting stress or distortion during the additive buildup. A computer program product and apparatus correspond to the method.

The present disclosure discloses a preparation method of a powder metallurgy (PM) superalloy with high strength and plasticity. Under the multi-field coupling action of a thermal field and a force field, the PM superalloy is obtained in a high-temperature graphite mold by using the method of conducting heat preservation and oscillating-pressure sintering in two steps. Under the action of a circulating pressure, rearrangement of powders and discharge of pores are promoted, and therefore, the PM superalloy is sintered and formed. The present disclosure further discloses a PM superalloy prepared by using the method above. The PM superalloy has the characteristics of low grade of prior particle boundary defects, uniform grain refinement and high density. The sintered PM superalloy obtained in the present disclosure has a yield strength of 955 MPa, a tensile strength of 1,437 MPa and an elongation of 31.9%, and has high strength and plasticity.

An additive manufacturing method includes: forming a powder bed by supplying a raw material powder; and irradiating the raw material powder that forms the powder bed with a light beam having an intensity distribution of a second or higher order mode or of a top hat shape.

A gas turbine combustion chamber, having a combustion chamber housing, a burner positioned at least partially in the combustion chamber housing and a flame tube positioned in the combustion chamber housing. An upstream end of the flame tube has a flame tube cover. In the region of the flame tube cover radially inside the flame tube cover a mixing tube of the burner extends, which defines a pre-primary combustion zone. Between the mixing tube of the burner and the flame tube cover an axial air flow passage is formed, via which air can be conducted in the axial direction outside along the mixing tube, and into the flame tube cover radial air flow passages are introduced via which the air following the axial air flow passage can be conducted in the radial direction of the flame tube cover for cooling the flame tube cover.

The invention relates to a method for producing a part by means of a laser beam, with a nozzle (1) that sprays a metal powder towards a substrate (5). Initially, the trajectory of the nozzle is defined in a pre-determined manner, and then, during the production of the part (7): a theoretical reference distance D0 that has been previously recorded and a real distance which is then measured are compared, and
the trajectory of the nozzle is modified on the basis of a deviation threshold between said distances.

A method for manufacturing a metal bladed wheel of a turbomachine reinforced by an insert made of metal matrix composite material, includes winding the ceramic fibers around a mandrel in order to form the insert, the ceramic fibers being surrounded by a material constituting the matrix; and spark plasma sintering the insert with a powder of metal constituting the bladed wheel to be manufactured.

A method of reworking an aerospace component includes removing a casting defect from a component manufactured of a non-fusion weldable base alloy to form a cavity. The cavity is then at least partially filled with a multiple of layers of discrete laser powder deposition spots of a filler alloy. A cast component for a gas turbine engine includes a cast component non-fusion weldable base alloy with a cavity filled with a multiple of layers of laser powder deposition spots of a filler alloy. The filler alloy may be different than the non-fusion weldable base alloy. A layer of non-fusion weldable base alloy is at least partially within the cavity and over the filler alloy.

A combined heat and power system comprises a shaft (4), a compressor (6) coupled to the shaft to compress intake gas to form compressed gas; a recuperator (10) to heat the compressed gas to form heated compressed gas; a combustor (12) to combust a fuel and the heated compressed gas to form combustion gas; a turbine (8) coupled to the shaft to expand the combustion gas to form exhaust gas; a load (24) coupled to the shaft; an exhaust outlet (18) to expel the exhaust gas to a heater for heating a fluid based on heat from the exhaust gas; a recuperator channel (28) providing a path for the exhaust gas to flow from the turbine to the exhaust outlet through the recuperator; and a bypass channel (22) providing a path for the exhaust gas to flow from the turbine to the exhaust outlet bypassing the recuperator.

A turbo machine including a plenum is formed within a double wall structure including an opening configured to provide fluid communication of a first flow of fluid between the plenum through the double wall structure, and an outer wall forming a passage configured to receive a second flow of fluid separate from the first flow of fluid, wherein a flowpath structure is formed at least in part within an inner wall, the flowpath structure configured to receive a third flow of fluid therethrough, the third flow of fluid separate from the first flow of fluid, the flowpath structure comprising an exit opening configured to provide fluid communication from the flowpath structure to the flowpath.