A blade cascade of a continuous-flow machine is disclosed. The blade cascade has at least one side wall that is constructed in a wave-like manner in the peripheral direction and has at least one elevation and at least one depression. At least a profile-like rib is integrated in or combined with the side wall, which has a blade profile with a pressure side and with an opposite suction side. A continuous-flow machine with such a blade cascade is also disclosed.

A turbine blade that includes an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade further may include a rib configuration that partitions the chamber of the airfoil into radially extending flow passages. A first flow passage may include a first side on which turbulators are positioned, wherein each of the turbulators comprises a canted configuration.

An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades.

A blade cascade of a turbomachine having at least one shape variation of a blade situated on the blade side in the proximity of a side wall and extending downstream, and at least one side wall contouring of the side wall or at least one second shape variation of an adjacent blade near the side wall, as well as a turbomachine, are disclosed.

A compressor aerofoil for a turbine engine or an axial process compressor, the compressor aerofoil includes 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 and define a tip having a tip surface, the aerofoil has a maximum thickness T.sub.max. A mean camber line is defined as passing through the leading edge and the trailing edge. The compressor aerofoil further includes a winglet at the tip and which extends from the suction surface, the winglet has an overhang W that has a perpendicular extent from the suction surface in the range 0.1 T.sub.max to 1.5 T.sub.max. The winglet has a maximum overhang W.sub.max that occurs within 50% of the length of the mean camber line from the leading edge.

Airfoils for gas turbine engines are disclosed herein. The airfoils each include a pressure side and a suction side. Vortex-reduction passageways extend from the pressure side to the suction side.

A turbine blade is provided. The turbine blade may include a blade body including a leading edge, a trailing edge, a suction side, a pressure side, and a tip region, a squealer tip extending upward from the tip region of the blade body, a winglet extending outward from the squealer tip on the suction side of the blade body, and a cooling hole obliquely formed through the winglet to communicate with an inner cavity of the blade body.

A turbine blade that includes an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may further include a rib configuration that partitions the chamber into radially extending flow passages, and a blade outer shell that defines an outer surface of the airfoil. The rib configuration is a non-integral component to the blade outer shell.

A turbine blade comprising an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may further include: a rib configuration that partitions the chamber into radially extending flow passages that include a first flow passage and a second flow passage; and a crossover passage that fluidly connects an inlet formed in the first flow passage to an outlet formed in the second flow passage. The crossover passage may include a canted configuration relative to the second flow passage.

A fan blade includes a metallic body, a first composite cover, and a second composite cover. The metallic body may have a first side, a second side, a plurality of first retention slots, and a plurality of second retention slots, in accordance with various embodiments. The first and second retention slots may extend from the first side to the second side of the metallic body. The first composite cover may be coupled to the first side of the metallic body and may include a plurality of first fingers that extend through the first retention slots and are coupled to the second side of the metallic body. The second composite cover may be coupled to the second side of the metallic body and may include a plurality of second fingers that extend through the second retention slots and are coupled to the first side of the metallic body.