United Technologies Corporation

Li Xing Pan

Yuan Dong

Sean Nolan

Robert W Fessenden

Simon W Evans

Sue-Li Chuang

Sue-Li Kingsley Chuang

Abhir A Adhate

Rotor of a gas turbine engines having a rotor hub and a plurality of blades extending from the rotor hub, wherein each blade has a full-span forward sweep along a leading edge of the blade that starts at an airfoil root of the blade at the hub and extends to a blade tip, wherein a sweep of a blade is a percentage of a root axial chord length of the respective blade.

Full-span forward swept airfoils for gas turbine engines

A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be between 1.5 to 2.5 percent.

Gas turbine engine airfoil

Growing community of inventors

Middletown, CT, United States of America

Li Xing Pan