A mounting bracket for mounting an accessory to a gas turbine engine comprises a space frame structure. The space frame structure comprises a plurality of struts joined to one another at nodes.

A coupon for replacing a cutout in a hot gas path component of a turbomachine is provided. In one embodiment, the coupon includes a body having an outer surface; and a plurality of grinding depth indicators in the outer surface of the body. In another embodiment, the coupon includes a body having an edge periphery configured to mate with an edge periphery of the cutout, and at least a portion of the edge periphery of the body has a wall thickness greater than a wall thickness of an edge periphery of the cutout. The embodiments may be used together or separately.

A method for shaping an aerofoil by: (a) defining an aerofoil having a nominal shape, the nominal shape defined by; a leading edge, a trailing edge, a root and a tip, a span extending from the root to the tip, a pressure surface and a suction surface extending from the leading edge to the trailing edge; a nominal camber line extending from the leading edge to the trailing edge; (b) defining an edge region on one of the pressure and/or suction surface which extends distance of at least 0.1% but no more than 10% of the camber line length from one of the leading edge or the trailing edge of the aerofoil; and (c) adapting the shape of the pressure and/or suction surface within the edge region such that the edge region of the aerofoil achieves an asymmetric profile with respect to the nominal camber line.

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 three-dimensional additive manufactured product includes a body portion and a male screw portion integrally disposed on a surface of the body portion so as to protrude therefrom. The male screw portion includes a following side flank forming a first flank angle with respect to a vertical plane to an axis thereof. The first flank angle is not less than 45 degrees.

Provided is a gas turbine vane and blade assembly in which lattice structures are installed between an impingement plate and an effusion plate. The gas turbine vane and blade assembly is capable of enhancing cooling efficiency in an impingement/effusion cooling technique.

In addition, the gas turbine vane and blade assembly can be manufactured using an additive manufacturing technique, and the lattice structures are capable of replacing supports that are used during an additive manufacturing process, and improving not only structural rigidity and stability but also cooling performance.

A method of a coating by additive manufacturing on a turbomachine casing includes depositing on an internal surface of the turbomachine casing a filament of an abradable material to create a three-dimensional scaffold of filaments. A filamentary material deposition system is positioned from the internal surface of the casing; a first layer of the coating is deposited over 360′; a rotation of the filamentary material deposition system is carried out by a first predetermined angle and the filamentary material deposition system is positioned from the deposited layer; a second layer of coating is deposited on the first coating layer, on a sector of the casing; a displacement is carried out corresponding to the first sector already covered, then for the following sectors until 360° is covered; and after having carried out a rotation of the filamentary material deposition system.

A gas turbine engine guide vane heat exchanger has guide vane heat exchanger including electroformed fluid channels in electroformed heat exchanger tubes or a heat exchanger core disposed within airfoil. Non-flammable heat conducting liquid or non-metallic foam may fill space between tubes or core and airfoil. Fluid circuit may include channels within electroformed heat exchanger tubes or the heat exchanger core and extend from inlet manifold to outlet manifold for directing fluid or oil through channels and include fluid or oil supply inlet connected to inlet manifold for receiving the fluid or oil flowed into inlet manifold and a fluid or oil supply outlet connected to fluid or oil supply outlet for discharging fluid or oil flowed out of fluid or oil outlet manifold. Heat exchanger tubes or heat exchanger core, inlet manifold, outlet manifold, supply inlet and supply outlet may be integrally and monolithically electroformed together.

A method for producing an impact-resistant component, in particular a component of a turbomachine, such as an aircraft engine, and a corresponding component. The component is produced at least partially by an additive manufacturing method from a powder material in such a way that the component is formed at least in a first region from a material with a first toughness and at least in a second region from a material with a second toughness, the second toughness being greater than the first toughness, and wherein the second region is formed, at least in a part of the component, as a continuous or interrupted layer, preferably parallel to the surface of the component, at a distance from the surface of the component.

A method for additively printing extension segments on workpieces using an additive manufacturing machine includes controlling, with a computing system, an operation of a print head of the machine such that a region of interest of a build plate of the machine is scanned with an electromagnetic radiation beam. Additionally, the method includes receiving, with the computing system, data associated with reflections of the beam off of the build plate as the region interest is scanned. Furthermore, the method includes receiving, with the computing system, data associated with a location of the beam relative to the build plate. Moreover, the method includes determining, with the computing system, a location of a workpiece interface based on the received data. In addition, the method includes controlling, with the computing system, the operation of the print head such that an extension segment is additively printed on the determined workpiece interface.