Importance

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Abstract

An airfoil array for a turbomachine, in particular a turbine or compressor stage of a gas turbine. The airfoil array includes at least two airfoils and at least one contoured circumferential surface which connects a pressure side of one airfoil to a suction side of the other airfoil and includes an upstream first section and a downstream second section which adjoins the first section along an elevation contour line; the first section being depressed relative to a rotationally symmetric reference surface containing this elevation contour line away from the airfoils, and the second section not being depressed relative to this reference surface away from the airfoils; this elevation contour line lying in an axial area which terminates at most 30% of an axial chord length of one of the airfoils downstream of its leading edge; and an axial distance of this elevation contour line increasing toward the pressure side and toward the suction side, starting at a point between the pressure and suction sides that is closest to the leading edge; and the first section extending over at least 90% of the space between the pressure side and the suction side.

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First Claim