Endwall shape for use in turbomachinery
AssigneeUnited Technologies Corporation
InventorsJ. Brent Staubach, Joel H. Wagner, Andrew S. Aggarwala
Life of this patent
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Abstract
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.
Claims10
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;
- and
- said inner endwall of each said flow passage having means for minimizing shock effects within and aft of each of said flow passages.
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 portion of said at least one flow passage to a point near a trailing edge portion of said at least one flow passage.
Dependencies are inferred from the claim text.