An objective of the invention to provide an alloy article that exhibits even better mechanical properties and/or even higher corrosion resistance than conventional high entropy articles without sacrificing the attractive properties thereof, a product formed of the alloy article, and a fluid machine having the product. An alloy article according to the invention has a predetermined chemical composition comprising: Co, Cr, Fe, Ni and Ti, each within a range of 5 atomic % or more and 35 atomic % or less; Mo within a range of more than 0 atomic % and less than 8 atomic %; an element with a larger atomic radius than the atomic radiuses of Co, Cr, Fe and Ni within a range of more than 0 atomic % and 4 atomic % or less; and a balance of inevitable impurities.

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a seal body extending circumferentially between opposed mate faces and at least one rail extending outwardly from the seal body. The seal body has a seal face that bounds a gas path. At least one rail aperture is defined at least partially through the at least one rail. At least one wear liner has a liner body. The liner body defines a liner aperture and an outer periphery that mates with the at least one rail aperture. A seal support is mountable to an engine case. The seal support has at least one support hook that mates with the liner aperture to mount the seal to the seal support. A method of assembly for a gas turbine engine is also disclosed.

A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a seal body extending circumferentially between opposed mate faces and at least one rail extending outwardly from the seal body. The seal body has a seal face that bounds a gas path. At least one rail aperture is defined at least partially through the at least one rail. At least one wear liner has a liner body. The liner body defines a liner aperture and an outer periphery that mates with the at least one rail aperture. A seal support is mountable to an engine case. The seal support has at least one support hook that mates with the liner aperture to mount the seal to the seal support. The at least one support hook is made of a first material, and the liner body is made of a second material that differs in construction from the first material. A method of assembly for a gas turbine engine is also disclosed.

A gas turbine engine includes a turbine section having a turbine rotor and at least one blade extending outwardly of the turbine rotor. The turbine rotor rotates about an axis of rotation. A blade outer air seal is positioned radially outward of the at least one blade. The blade outer air seal has an axially forward hook and an axially aft hook supported to static structure. An axial seal is attached to static structure forward of the forward hook, and has a sealing portion extending in an aft direction. A sealing surface member is positioned intermediate an aft end of the axial seal and a forward end of the forward hook to provide a sealing surface for sealing between the seal and the blade outer air seal.

A method for preventing corrosion of an impeller-shaft assembly of a turbomachine comprises the steps of assembling an impeller on a shaft in order to define an impeller-shaft assembly; plating the assembly by inserting the assembly into a plating bath; and coating at least a first predefined surface on the impeller and a second predefined surface on the shaft wherein the coating step is performed by spraying the predefined surfaces.

A gas turbine engine includes a turbine section having a turbine rotor and at least one blade extending outwardly of the turbine rotor. The turbine rotor rotates about an axis of rotation. A blade outer air seal is positioned radially outward of the at least one blade. The blade outer air seal has an axially forward hook and an axially aft hook supported to static structure. An axial seal is attached to static structure forward of the forward hook, and has a sealing portion extending in an aft direction. A sealing surface member is positioned intermediate an aft end of the axial seal and a forward end of the forward hook to provide a sealing surface for sealing between the seal and the blade outer air seal.

A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.

Volumetric resistance blowers are disclosed herein. An example volumetric resistance blower includes a housing, a motor, and a rotor disposed within the housing and rotated by the motor. The rotor is constructed of metal foam.

A compressor rotor for a gas turbine engine has blades circumferentially distributed around and extending a span length from a central hub. The blades include alternating first and second blades having airfoils with corresponding geometric profiles. The airfoil of the first blade has a coating varying in thickness relative to the second blade to provide natural vibration frequencies different between the first and the second blades.