A component, such as for a turbine engine, can include an airfoil with an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a chord-wise direction and extending between a root and a tip to define a span-wise direction. The component can also include at least one cooling passage within the interior.

This disclosure relates to a refrigerant compressor including an impeller. The impeller has a blade with a wavy contour. The wavy contour reduces flow separation relative to smooth, non-wavy blades. In particular, the disclosed wavy contour creates smaller trailing edge vortexes adjacent the blades. In turn, the wavy contour of the blades improves overall compressor efficiency.

A turbomachine defines an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending concentrically around the axial direction. The turbomachine includes a nozzle having an inner platform, an outer platform, and an airfoil. The airfoil includes a leading edge, a trailing edge downstream of the leading edge, a pressure side surface, and a suction side surface opposite the pressure side surface. The trailing edge defines a circular arc between the inner platform and the outer platform.

A method for shaping an aerofoil by: (a) defining an aerofoil having a nominal shape, the nominal shape defined by; a leading edge, a trailing edge, a root and a tip, a span extending from the root to the tip, a pressure surface and a suction surface extending from the leading edge to the trailing edge; a nominal camber line extending from the leading edge to the trailing edge; (b) defining an edge region on one of the pressure and/or suction surface which extends distance of at least 0.1% but no more than 10% of the camber line length from one of the leading edge or the trailing edge of the aerofoil; and (c) adapting the shape of the pressure and/or suction surface within the edge region such that the edge region of the aerofoil achieves an asymmetric profile with respect to the nominal camber line.

A turbine stage includes an array of airfoils spaced apart circumferentially to define a flow passage therebetween for channeling a working medium. The airfoils extend radially outward from an inner endwall located at a hub side thereof. The inner endwall is inclined at an angle to an engine axis such that the flow passage is divergent from an upstream side to a downstream side. The inner endwall is non-axisymmetric about the engine axis, having a mid-passage bulge located between circumferentially adjacent first and second airfoils. The bulge has a peak at a position between 20-60% Cax.sub.ID and at a position between 30-70% pitch.sub.ID.

A method of manufacturing a component for a gas turbine engine includes applying a thermoplastic polymer sheet over a composite body for the component; applying a shield over part of the composite body, the shield terminating at an end which overlies the thermoplastic polymer sheet and defines an interface between shielded and unshielded regions of the component; and pressing the shield into the thermoplastic polymer sheet so that the thermoplastic polymer sheet deforms around the end of the shield, such that the exterior profile of the component at the interface between the shielded and unshielded regions is flush.

The invention relates to a profiled structure elongated in a direction in which the structure has a length exposed to an airflow and transversely to which the structure has a leading edge and/or a trailing edge, at least one of which is profiled and has, along said direction of elongation, geometric serration patterns defined by a succession of peaks and troughs. Along the profiled leading edge and/or trailing edge, the serration patterns have a geometric pattern that is repeated in the direction of elongation, the shape of which is stretched and/or contracted transversely to the direction of elongation and/or in the direction of elongation.

A turbine blade for a gas turbine, having a blade root and an aerodynamically curved blade airfoil arranged above the blade root. The blade airfoil has a pressure-side and a suction-side blade wall, together extending from a leading edge, that can receive a flow of working medium, to a trailing edge. A multiplicity of cooling air outlet openings are formed on the pressure-side blade wall, which extend upstream from the trailing edge with respect to the flow direction, and through these openings cooling air that is conveyed through the interior of the blade airfoil can exit. At least one of the cooling air outlet openings has a substantially rectangular or trapezoidal shape with rounded corners. At least the lower corner, pointing towards the leading edge, of the cooling air outlet opening forms a relief notch, which projects outwardly from the rectangular shape, with a rounded notch bottom.

Composite airfoils and methods for forming composite airfoils are provided. For example, a composite airfoil of a gas turbine engine comprises opposite pressure and suction sides extending radially along a span from a root to a tip, which define opposite radial extremities of the airfoil. The composite airfoil further comprises a body section and a tip section, which includes the tip, that each extend radially along the span. The composite airfoil is formed from a composite material comprising fibers disposed in a matrix material. The tip section has a tip fiber volume, and the body section has a body fiber volume that is greater than the tip fiber volume. Another composite airfoil comprises a tip cap applied over the tip that tapers from a first end to a second end such that each of the pressure and suction side walls of the tip cap narrows from a first thickness to a second thickness.

A centrifugal blower includes a centrifugal fan and a separation cylinder. The centrifugal fan has a separation plate. The separation cylinder is disposed inward of the blades in the radial direction of the centrifugal fan. The separation plate has an inner end surface extending from the one side to the other side in the axial direction at a position of an inner end in the radial direction. The separation cylinder has a separation cylinder end surface extending from the one side to the other side in the axial direction at a position of an end on the other side in the axial direction. A height of one of the separation cylinder end surface and the inner end surface in the axial direction is larger than a height of the other of the separation cylinder end surface and the inner end surface in the axial direction.