Pratt & whitney canada corp. (20240426218). AIRFOIL THICKNESS PROFILE FOR MINIMIZING TIP LEAKAGE FLOW
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AIRFOIL THICKNESS PROFILE FOR MINIMIZING TIP LEAKAGE FLOW
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AIRFOIL THICKNESS PROFILE FOR MINIMIZING TIP LEAKAGE FLOW
This abstract first appeared for US patent application 20240426218 titled 'AIRFOIL THICKNESS PROFILE FOR MINIMIZING TIP LEAKAGE FLOW
Original Abstract Submitted
a turbine engine assembly includes at least one rotor that has a plurality of blades, each of the blades includes an airfoil that has a pressure side and a suction side that each extend between a leading edge, a trailing edge, a tip and a base. the airfoil has a thickness between the pressure side and the suction side perpendicular to a camber line that varies between the leading edge and the trailing edge. the thickness includes a suction side thickness between the camber line and the suction side and a pressure side thickness between the camber line and the pressure side. a maximum ratio of the pressure side thickness to the suction side thickness is between 3 and 7.