United Technologies Corporation

Raytheon Technologies Corporation

Robert W Fessenden

Charles H Warner

Yuan Dong

Sean Nolan

Carl S Richardson

Li Xing Pan

Ling Liu

Simon W Evans

Sue-Li Chuang

Sue-Li Kingsley Chuang

Jeff M Carrico

Abhir A Adhate

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 1.01-1.15 inch (25.7-29.3 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.54-0.66 inch (13.6-16.8 mm). The airfoil element includes at least two of a first mode with a frequency of 2033 &#xb1; 15% Hz, a second mode with a frequency of 7023 &#xb1; 15% Hz, a third mode with a frequency of 12082 &#xb1; 15% Hz and a fourth mode with a frequency of 19769 &#xb1; 15% Hz.

Gas turbine engine airfoil frequency design

A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.78-0.91 inch (19.7-23.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.49-0.62 inch (12.5-15.6 mm). The airfoil element includes at least two of a first mode with a frequency of 3533&#xb1;15% Hz, a second mode with a frequency of 8291&#xb1;15% Hz, a third mode with a frequency of 17362&#xb1;15% Hz and a fourth mode with a frequency of 23365&#xb1;15% Hz.

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

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Manchester, CT, United States of America

Robert W Fessenden