초록 ▼

The present invention relates to an endwall shape for reducing shock strength on transonic turbomachinery airfoils which define at least one flow passage. The endwall shape includes a non-axisymmetric trough which extends from a leading portion of the at least one flow passage to a point near a trai

The present invention relates to an endwall shape for reducing shock strength on transonic turbomachinery airfoils which define at least one flow passage. The endwall shape includes a non-axisymmetric trough which extends from a leading portion of the at least one flow passage to a point near a trailing edge portion of the at least one flow passage.

대표청구항 ▼

1. A flow directing assembly for use in a rotary machine comprising: a plurality of blades, each said blade having an airfoil and a platform; a plurality of flow passages defined by said airfoils of said blades; each of said flow passages having an inner endwall defined by platforms of adjacent

1. A flow directing assembly for use in a rotary machine comprising: a plurality of blades, each said blade having an airfoil and a platform; a plurality of flow passages defined by said airfoils of said blades; each of said flow passages having an inner endwall defined by platforms of adjacent ones of said blades; said inner endwall of each said flow passage having means for minimizing shock effects within and aft of each of said flow passages; said shock effect minimizing means comprising a non-axisymmetric trough which extends from a point within said flow passage to a point aft of said flow passage; and said trough having an initial amplitude at a location adjacent a leading edge portion of said flow passage, a maximum amplitude adjacent a flow passage throat axial location, and a final amplitude at a downstream extent of said platform and wherein said initial and final amplitudes are less than said maximum amplitude. 2. A flow directing assembly according to claim 1, wherein each said trough is located in a portion of said platform associated with a respective blade. 3. A flow directing assembly according to claim 1, wherein each said airfoil has a suction side and each said trough has a curvature substantially identical to the curvature of a rear portion of said airfoil suction side. 4. A flow directing assembly according to claim 1, wherein said plurality of blades comprises a plurality of turbine blades. 5. A flow directing assembly according to claim 1, wherein said plurality of blades comprises a plurality of compressor blades. 6. An endwall shape for reducing shock strength on transonic turbomachinery airfoils having at least one flow passage defined by at least two airfoils comprising a non-axisymmetric trough extending from a leading edge portion of said at least one flow passage to a point near a trailing edge portion of said at least one flow passage and said non-axisymmetric trough has having a maximum amplitude near a passage throat axial location. 7. An endwall shape according to claim 6, wherein said trough has an initial amplitude at said leading edge portion and a final amplitude adjacent said point near said trailing edge portion and wherein both said initial amplitude and said final amplitude are less than said maximum amplitude.