System and method for turbomachine with local vortex generator array
AssigneeHoneywell International Inc.
InventorsBruce D. Reynolds, John Repp
Life of this patent
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Abstract
A turbomachine includes a shroud and a hub spaced apart from the shroud to channel an airflow along a direction. The turbomachine includes a plurality of airfoils coupled between the shroud and the hub. At least one airfoil of the plurality of airfoils includes a leading edge spaced apart from a trailing edge in the direction of the airflow and a pressure side opposite a suction side. The at least one airfoil has a chord that is 0% chord at the leading edge and 100% chord at the trailing edge, and a span defined as 0% at the hub and 100% at the shroud. The turbomachine includes at least one local vortex generator array defined onto the hub between 0% chord to −10% chord at 0% span so as to extend forward of the leading edge.
Claims20
A turbomachine comprising:
- a shroud;
- a hub spaced apart from the shroud, the hub and the shroud configured to channel an airflow along a direction;
- a plurality of airfoils coupled between the shroud and the hub, at least one airfoil of the plurality of airfoils including a leading edge spaced apart from a trailing edge in the direction of the airflow and a pressure side opposite a suction side, the at least one airfoil has a chord that is 0% chord at the leading edge and 100% chord at the trailing edge, and a span defined as 0% at the hub and 100% at the shroud;
- and
- at least one local vortex generator array defined onto the hub between 0% chord to −10% chord at 0% span so as to extend forward of the leading edge.
A turbomachine comprising:
- a shroud;
- a hub spaced apart from the shroud, the hub and the shroud configured to channel an airflow along a direction;
- a plurality of airfoils coupled between the shroud and the hub, at least one airfoil of the plurality of airfoils including a leading edge spaced apart from a trailing edge in the direction of the airflow and a pressure side opposite a suction side, the at least one airfoil has a chord that is 0% chord at the leading edge and 100% chord at the trailing edge, and a span defined as 0% at the hub and 100% at the shroud;
- and
- at least one local vortex generator array defined on the shroud between 0% chord to −10% chord at 100% span so as to extend forward of the leading edge.
Dependencies are inferred from the claim text.