A blade for a gas powered turbine includes a platform having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a suction side mateface and by a pressure side mateface. A blade extends outward from the platform. The blade has a foil shaped cross section and a suction side of the blade faces the suction side mateface and a pressure side of the blade faces the pressure side mateface. A radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position.

A device (1) for enabling access to a rotor blade (2) of a wind turbine is described, said device (1) comprising a frame (3) having connecting means (4) located at an upper region of said frame (3) and being structured in the range to be connected to a hoisting device. Such a device should be of simple construction, which is easy to control. To this end said frame (3) is in form of a triangle, said connecting means (4) being located in a region of an edge of said triangle.

A gas turbine engine compressor blade includes an airfoil and a root section connected to a blade platform therebetween and an at least partially curved cropped corner of the blade platform. The corner shape and size may avoid resonance of blade during engine operation. Corner may be J-shaped including a straight section extending from pressure side edge towards suction side edge of platform and curved section extending from straight section to uncropped portion of platform trailing edge of the platform. A method of designing the cropped corner includes choosing shapes sizes of the cropped corner for numerically analyzing and determining shape and size for cropped corner using numerical model to iteratively numerically analyze aerodynamically cropped platform with different shapes and sizes of cropped corner. Numerical model may be validated with engine or component testing of blade having a cropped platform with at least one of the shapes and sizes.