Methods for manufacturing combustor panels of gas turbine engines and combustor panels are described. The methods include defining a particle deposit near-steady state for at least a portion of a combustor panel, the particle deposit near-steady state representative of a build-up of particles on the at least a portion of the combustor panel during use, generating a template based on the defined particle deposit near-steady state, wherein the template includes one or more augmentation elements based on the representative of build-up of particles, and forming a combustor panel based on the template, wherein the formed combustor panel includes one or more augmentation elements defined in the template.

A turbine blade for a gas turbine engine. The turbine blade includes an airfoil having a tip cavity. The tip cavity has a floor bounded by a wall. A pocket opening is formed in the wall proximate a trailing edge of the turbine blade. A passageway communicates cooling medium from an internal cooling circuit to a cooling hole formed in part through the floor and in part through the trailing edge.

A refractory metal core (RMC) finishing method according to an exemplary aspect of the present disclosure includes, among other things, performing a plurality of finishing operations on a plurality of RMC samples, analyzing one or more properties of at least a portion of the plurality of RMC samples and selecting a combination of finishing operations for generating an RMC having desirable properties for manufacturing a part free from defects.

A blade has an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The blade has a compositional variation along the airfoil.

A nozzle guide vane for a gas turbine engine having a combined side wall thickness value which varies within a cavity region so as to provide a point with a maximum value of combined side wall thickness, which is advantageous for capturing debris travelling through the engine core.

A gas turbine engine assembly according to an example of the present disclosure includes, among other things, an endwall having a first material composition, an airfoil extending in a radial direction from the endwall, and a cupped contour of a second material composition that is formed on the endwall to define a cooling chamber, the first material composition different than the second material composition. A method of forming an endwall is also disclosed.

A blower housing assembly structure includes a locking base formed by aluminum die casting and two opposite casing covers disposed on both sides of the locking base respectively. The locking base has two opposite side connecting plates, each having a connection part formed at the top of the side connecting plate, and a side of each casing cover has an intake vent, and the two casing covers have two opposite half-extended pipe sections extending from the edges of the locking base connection part respectively, so that the half-extended pipe sections of the two casing covers are engaged to form an exhaust vent of a housing. This invention has the advantages of simple structure, easy assembling, effective alignment and high stability and the effects of preventing damages by vibration and reducing the noise during operation.

A turbine housing can include a bearing housing end and a treatment unit end; a volute wall that defines a volute; a wall that defines at least a portion of a turbine wheel space that defines a turbine wheel space axis and a turbine wheel space diameter, where the wall extends to an axial peak to define an extended space with an extended space outlet having an extended space outlet dimension; and an outlet wall that defines an outlet space with a treatment unit end outlet having an outlet dimension, where the extended space is disposed at least in part axially between the turbine wheel space and the outlet space to increase axial velocity uniformity at the treatment unit end outlet.

A method of assembling a gas turbine engine is disclosed herein. The method comprises providing a set of standard axial compressor stages. Each axial compressor stage included in the set of standard axial compressor stages includes a rotor having a plurality of blades configured to rotate about an axis and a stator having a plurality of stator vanes.

A cylinder head assembly for an internal combustion engine includes a cast cylinder head, a turbocharger housing including a compressor housing and turbine housing integrally cast with the cylinder head, and a turbocharger cartridge assembly configured to be inserted into the turbocharger housing and including a shaft coupled between a compressor wheel and a turbine wheel. A compressor cover is configured to couple to the compressor housing and define a compressor inlet and at least partially define a compressor diffuser passage. The cartridge assembly includes a housing having a diffuser flange extending outwardly therefrom, the diffuser flange including a front surface and an opposite contoured volute surface. The compressor diffuser passage is at least partially defined by the compressor cover and the diffuser flange front surface. A compressor volute is at least partially defined by the diffuser flange contoured volute surface and a contoured inner surface of the compressor housing.