A thermal barrier coating (TBC) with depth-varying material properties is formed on a turbine component. Exemplary depth-varying material properties include physical ductility, strength and thermal resistivity that vary from the TBC layer inner to outer surface. Exemplary ways to modify physical properties include application of plural separate overlying layers of different material composition or by varying the applied material composition during the application of the TBC layer. Various embodiment described herein also apply a calcium-magnesium-aluminum-silicon (CMAS)-retardant material over the TBC layer to retard reaction with or adhesion of CMAS containing combustion particulates to the TBC layer. In other embodiments the CMAS retardant material is also applied within engineered groove features (EGFs) that are formed in the TBC surface.

A sealing strip element for sealing a gap between two components of a gas-turbine installation, and extends along a longitudinal direction and has a contoured cross section in a ribbed central region. The sealing strip element extends along the longitudinal direction, wherein at least one of the first main surface and the second main surface includes a riffle structure, wherein the riffle structure has multiple teeth extending substantially from the first strip end to the second strip end along a substantially straight line while establishing chutes between them, wherein at least one dam is provided at at least one strip end of the sealing strip element.

A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.

A centrifugal multiblade blower includes: an electric motor; and an impeller blowing off air outward in a radial direction by being rotated by the electric motor. A main plate of the impeller has an uneven part on one surface adjacent to the electric motor in a thickness direction of the main plate. The one surface is in contact with air passing through inside of the electric motor. A surface shape of the uneven part is formed in manner that, among a whole surface of the uneven part, a total surface area of a surface facing inward in a radial direction of the motor is larger than an imaginary smooth surface on which the surface shape of the uneven part is defined to be a smooth surface without the uneven part.

A turbomachine sealing component has: a substrate having circumferential surface; and a coating on the circumferential surface. The coating or a layer thereof is patterned to form circumferential sealing ridges.

A blower including a housing at least partially defining a chamber, a motor including a drive shaft defining a rotational axis, an impeller driven by the motor to generate an air flow in the chamber, and a coupler operably connected between the drive shaft and the impeller. The chamber may have an axial height which increases from a position proximate a back plate to a position spaced from the back plate. The chamber may have a non-circular cross-section proximate a chamber outlet, and a tube assembly in fluid communication with the chamber may have a tube inlet with a non-circular cross-section. The impeller may define two separate airflow paths each having an inlet and an outlet.

Disclosed is a compressor including: a rotatably-mounted rotor disk including a slot in an outer circumference thereof; and a blade including a root member connected to fix to the slot of the rotor disk, an airfoil with a leading edge facing introduced air and a trailing edge, and a platform formed in between the root member and the airfoil to stably support the airfoil over the rotor disk, the blade further including first and second bumps being respectively formed on each end side of the platform to face the introduced air.

A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls. At least one pedestal is positioned within the at least one cooling channel and has a body extending from a first end connected to the first side wall to a second end connected to the second side wall. The body includes at least one protrusion.

An impeller (10) of a centrifugal compressor (4) is provided with a hub (14) and a plurality of blades (16) provided at intervals in a circumferential direction of the impeller (10) on an outer peripheral surface of the hub (14). In a meridian plane shape of the blades (16), as the coordinate axes with the origin at a tip end (30s) of a trailing edge (30) of the blades (16), an X-axis connecting the tip end (30s) and a base end (30h) of the trailing edge (30) and a Y-axis orthogonal to the X-axis are defined. When a direction from the tip end (30s) toward the base end (30h) along the X-axis is defined as a positive direction of the X-axis and a direction toward the outside in a radial direction of the impeller (10) along the Y-axis is defined as a positive direction of the Y-axis, the trailing edge (30) in the meridian plane shape of the blades (16) includes a first decrease section (30a) extending so that the Y-coordinate decreases as the X-coordinate increases, and a first increase section (30b) positioned between the first decrease section (30a) and the base end (30h) and extending so that the Y-coordinate increases as the X-coordinate increases.

An airfoil assembly has a platform and an airfoil. The platform has an upstream edge, a downstream edge, and a surface extending between the upstream edge and the downstream edge. At least a portion of the surface extends circumferentially along a surface baseline defined by a constant radial distance from the rotational axis. The airfoil has an outer wall. The outer wall extends between a root and a tip, and between a leading edge and a trialing edge. The airfoil assembly includes a fence provided along the outer wall.