Compressor blade for an axial compressor
AssigneeSiemens Aktiengesellschaft
InventorsChristian Cornelius, Georg Kröger, Eberhard Nicke
Life of this patent
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Abstract
A compressor blade for an axially permeated compressor, preferably of a stationary gas turbine is provided. The camber line of the blade tip side profile of the blade of the compressor blade includes at least two inflection points for reducing radial gap losses. By means of two inflection points, there is a concavely designed suction side contour segment in a segment from 35% to 50% for the suction side contour, and a convexly implemented pressure side contour segment for the pressure side contour. It is possible by means of the geometry to generate low-loss gap vortices, in order to increase the overall efficiency of an axial compressor including the compressor blades.
Claims20
A compressor rotor blade for an axial compressor, comprising:
- a curved blade airfoil which includes a pressure-side wall and a suction-side wall which in one direction, extend in each case from a common leading edge to a common trailing edge and, and in another direction extend from a fastening-side blade airfoil end to a blade airfoil tip, forming a span,
- wherein for each blade airfoil height which exists along the span the blade airfoil includes:
- a profile with a suction-side contour and a pressure-side contour,
- an at least partially curved camber line, and
- a rectilinear profile chord,
- wherein the suction-side contour and the pressure-side contour, camber line and profile chord extend in each case from a leading edge point to a trailing edge point,
- wherein at least some of the camber lines of the blade tip-side profiles includes at least two inflection points.
Dependencies are inferred from the claim text.