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 turbomachine includes at least one local vortex generator array defined on the suction side so as to extend onto the hub or the shroud. The at least one local vortex generator array is defined downstream of the leading edge.
Claims18
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, a pressure side opposite a suction side, and a span defined as 0% at the hub and 100% at the shroud;
- and
- a plurality of local vortex generator arrays defined on the suction side so as to extend onto the hub or the shroud, the plurality of local vortex generator arrays defined downstream of the leading edge, the plurality of local vortex generator arrays include at least a plurality of first flow features and a plurality of second flow features arranged in pairs, and one of the plurality of local vortex generator arrays is defined on the suction side between 0% span and less than or equal to 40% span.
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, a pressure side opposite a suction side, and the at least one airfoil has a span defined as 0% at the hub and 100% at the shroud;
- and
- a first local vortex generator array defined on the suction side and the shroud, the first local vortex generator array is defined downstream of the leading edge, and the first local vortex generator array is defined on the suction side between greater than or equal to 60% span and 100% span.
A method for manufacturing a stator for a turbomachine, the stator including at least one local vortex generator array, the method comprising:
- receiving, by a processor, design criteria for the stator, the stator including a shroud, a hub, and a plurality of airfoils that each extend between the shroud and the hub in the spanwise direction, at least one airfoil of the plurality of airfoils including a leading edge spaced apart from a trailing edge in a chordwise direction and a pressure side opposite a suction side, and the design criteria including blade row pressure losses and airflow turning deviation for the stator;
- receiving, by the processor, a shape, and a location of the at least one local vortex generator array defined on the suction side of the at least one airfoil and at least one of the hub and the shroud;
- determining, by the processor, whether the shape and location of the at least one local vortex generator array defined on the suction side of the at least one airfoil and the at least one of the hub and the shroud meets the blade row pressure losses and the airflow turning deviation associated with the design criteria for the stator, the at least one local vortex generator array including a first local vortex generator array defined on the suction side and the shroud;
- and
- manufacturing the stator including the at least one local vortex generator array based on the determining.
Dependencies are inferred from the claim text.