Disclosed is a cooled airfoil having a hub end and tip, an airfoil height being defined between the hub end and the tip. The airfoil has a leading edge, trailing edge, suction side and pressure side. The airfoil has a first airfoil height section adjacent the hub end and extending towards the tip, wherein, in a meridional view, the leading edge and trailing edge are straight along the first airfoil height section. The airfoil has a second airfoil height section adjacent the tip and extending towards the hub end, wherein, in a meridional view, the airfoil is concavely shaped at the leading edge and is convexly shaped at the trailing edge along the second airfoil height section. At least one cooling channel has a length principally extending along the airfoil height, extends straight in a first cooling channel length section, and is bent in a second cooling channel length section.

A turbine blade includes an airfoil portion having a pressure surface and a suction surface each of which extends between a leading edge and a trailing edge, and a platform including an end wall to which a base-end portion of the airfoil portion is connected. The end wall includes a concave portion on suction surface disposed at least in a region of suction surface of the end wall, and a convex portion on pressure surface disposed at least in a region of pressure surface of the end wall. The concave portion on suction surface has a bottom point located on an axially upstream side of a tangent point on the suction surface, the suction surface having a tangential line extending in an axial direction through the tangent point.

A compressor aerofoil rotor blade for a turbine engine includes: a root portion spaced apart from a tip portion by a main body portion. The main body portion is defined by a suction surface wall having a suction surface and a pressure surface wall having a pressure surface. The suction surface wall and the pressure surface wall meet at a leading edge and a trailing edge. The tip portion comprises a shoulder provided on the pressure surface wall. A tip wall extends from the aerofoil leading edge to the aerofoil trailing edge. A transition region of the pressure surface wall tapers from the shoulder in a direction towards the tip wall. The tip wall includes a squealer defined by a first tip wall region which extends from the trailing edge to a winglet.

A low-pressure compressor for an axial-flow turbomachine, such as a jet engine, includes an annular row of vanes and a between-vanes passage with a connecting surface that links the pressure surface of a first vane to the suction surface of a second vane of the row. The connecting surface includes a main protuberance which includes a first elevation and a second elevation that are spaced apart from one another.

A gas turbine has a rotor blade. The rotor blade has a blade root connected to an airfoil. The blade root has a root contour with respect to a cross-sectional view. From a lower end of the blade root, the blade root contour has convex contour portions and concave contour portions. From the lower end along the blade root contour between a convex contour portion and an adjoining concave contour portion, there is a contour portion as a flank portion that is load-bearing. From the lower end along the blade root contour between a concave contour portion and an adjoining convex contour portion, there is a contour portion as a flank portion that is not load-bearing in operation. At least one of the concave contour portions has a first arc portion, a second arc portion, and a straight portion disposed between the two arc portions.

Airfoil assemblies for gas turbine engines are provided. For example, an airfoil assembly comprises an airfoil, an inner band defining an inner opening shaped complementary to an inner end of the airfoil, and an outer band defining an outer opening shaped complementary to an outer end of the airfoil. The airfoil inner end is received with the inner opening, and the airfoil outer end is received within the outer opening. A strut extends radially through an airfoil cavity. A first pad is defined at a first radial location within the cavity. A second pad is defined within the cavity at a second, different radial location. In some embodiments, the airfoil assembly inner band includes a first inner flange, through which the inner band is secured to a support structure, and the outer band includes a first outer flange, through which the outer band is secured to a support structure.

An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.

A fluid machine has: first and second walls; a gaspath defined between the first wall and the second wall; a rotor having blades rotatable about the central axis; and a tandem having: a first row of first vanes having first airfoils including first leading edges, first trailing edges, first pressure sides and first suction sides opposed the first pressure sides, and a second row of second vanes downstream of the first vanes and having second airfoils including second leading edges, second trailing edges, second pressure sides and second suction sides opposed the second pressure sides, the first vanes being circumferentially offset from the second vanes; and depressions defined in the first wall, a depression of the depressions located circumferentially between a pressure side of the first pressure sides and a suction side of the second suction sides, the depressions axially overlapping the first airfoils and the second airfoils.

In some aspects, the techniques described herein relate to a refrigerant compressor, including: a stator; a rotor configured to rotate with respect to the stator; and at least one step seal between the rotor and the stator, wherein the step seal includes a first tooth and a second tooth extending from the rotor toward the stator, wherein a downstream surface of the first tooth and an upstream surface of the second tooth are arranged at an angle relative to one another, wherein the angle is less than 90°.

A rotor blade in an embodiment includes: a suction surface side projecting portion projecting from a suction surface on a leading edge side at a blade tip of the blade effective portion; and a pressure surface side projecting portion projecting from a pressure surface on a trailing edge side at the blade tip of the blade effective portion. The suction surface side projecting portion includes: a leading edge side end surface including a contact surface that comes into contact with the pressure surface side projecting portion of the adjacent rotor blade and a non-contact surface that does not come into contact with the pressure surface side projecting portion of the adjacent rotor blade during rotation; a groove portion formed from the non-contact surface to the trailing edge side; and a joining member joined to the groove portion, the joining member being formed of an erosion-resistance material.