A centrifugal pump component for an oil and gas well pump includes a substrate with an outer surface configured to contact oil and gas well fluid. The component further includes a coating formed on at least a portion of the outer surface. The coating includes a combination of hard particles and a metal matrix.

A blade comprises an airfoil having a root end and a tip. A metallic substrate is along at least a portion of the airfoil. An abrasive tip coating comprises an abrasive and an aluminum-based matrix. An aluminum-based base layer is between the tip coating and the substrate.

A method for repairing a tip portion of a turbine component having a structural defect is provided. The method includes removing a damaged section in turbine component with a structural defect in a tip portion of the turbine component. A pre-sintered preform is provided including a first portion having a first composition and a second portion having a second composition. The pre-sintered preform is configured to mate with an upper surface of a remaining portion of the turbine component. The method also includes applying the pre-sintered preform to the upper surface, wherein the PSP comprises a superalloy material and a braze material. The PSP and the remaining portion of the turbine component are subjected to a brazing process to melt the braze material and fill in the structural defect.

A gear assembly comprises a plurality of planet gear layshafts that have an outer surface having a plurality of gear surfaces and a surface having one or more bearing surfaces. The one or more bearing surfaces of the surfaces of the planet gear layshafts have a first case hardening depth and a first nitriding hardness depth. The gear surfaces of the outer surface of the planet gear layshafts have a second case hardening depth.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal assembly includes an abradable coating adjacent the contact area, and the abradable coating includes magnetic particles.

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor section, a turbine section, and at least one rotatable shaft. The engine further includes a seal assembly including a seal plate mounted for rotation with the rotatable shaft and a face seal in contact with the seal plate at a contact area. The seal assembly includes an abradable coating adjacent the contact area, and the abradable coating includes magnetic particles.

A turbocharger includes a turbine housing that has a bypass passage defined therein. The bypass passage connects a section of an exhaust passage on the upstream side of a turbine wheel to a section of the exhaust passage on the downstream side of the turbine wheel. A wastegate, which selectively opens and closes the bypass passage, is attached to the turbine housing. A valve seat for the wastegate is provided at an open edge of the bypass passage in the inner wall surface of the turbine housing. An abradable portion, which is a deformable portion, is adhered to the valve member of the wastegate. The abradable portion is configured to be deformed in accordance with the shape of the valve seat by contacting the valve seat when the bypass passage is shifted from the open state to the fully closed state.

A piston seal assembly for a gas turbine engine includes a seal composed of a nickel-based superalloy; a component in contact with the seal and defining a seal-counterface; and a coating on the seal at the seal-counterface, wherein the coating is a metal alloy binder phase and a hard particle phase distributed through the binder phase.

A non-metallic engine case inlet compression seal for a gas turbine engine includes a non-metallic longitudinal leg section that extends from the non-metallic arcuate interface section and a non-metallic mount flange section that extends from the longitudinal leg section.

An engine assembly for use with a gas turbine engine includes a first component, a second component, and a retention locking plug. The first component is formed to define a passage that extends into the first component. The second component is received in the passage defined in the first component. The retention locking plug extends into the first component and the second component to couple the second component with the first component.