United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Darryl Whitlow

Edward J Gallagher

Byron R Monzon

Barry M Ford

Ling Liu

Linda S Li

William R Graves

Sue-Li Chuang

Jason Elliott

William D Owen

Myron Klein

Scott C Billings

Mani Sadeghi

Daniel C Falk

Ethan C Drew

James H Moffitt

Michael K Gottschalk

Jay Thomas Abraham

An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 0&#xb0; to 10&#xb0; in a range of 10-20% span position. The trailing edge sweep angle is in a range of the trailing edge sweep angle is positive from 0% span to at least 95% span.

Gas turbine engine airfoil

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 27.5-28.5 inches (699-724 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 13.0-14.0 inches (330-356 mm). The airfoil element includes at least two of a first mode with a frequency of 34&#xb1;10% Hz, a second mode with a frequency of 90&#xb1;10% Hz, a third mode with a frequency of 178&#xb1;10% Hz, a fourth mode with a frequency of 222&#xb1;10% Hz, a fifth mode with a frequency of 307&#xb1;10% Hz and a sixth mode with a frequency of 389&#xb1;10% Hz.

Gas turbine engine airfoil frequency design

A gas turbine engine includes a combustion section arranged between a compressor section and a turbine section that extend in an axial direction. A fan section is arranged upstream from the compressor section. An airfoil is arranged in one of the fan section, the compressor section and the turbine section. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a leading edge that is projected onto a plane from various views and the plane is perpendicular to a viewing direction which corresponds to the various views. The plane is parallel with the axial direction in a 0&#xb0; view. The various views include the 0&#xb0; view which projects into an axial plane in the axial direction. A 90&#xb0; view projects into a tangential plane in a tangential direction normal to the axial direction and views between the 0&#xb0; and 90&#xb0; views. The airfoil has a maximum leading edge projection in a 20&#xb0; to&#xb0; view. The radial direction is normal to the axial and tangential directions.

An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve. The airfoil extends from a root and a zero axial reference point corresponds to axial center of the root. Xcorresponds to an axial distance from a leading edge to the reference point at a given span position. Xcorresponds to a axial distance from a trailing edge to the reference point at a given span position. Xcorresponds to an axial stacking offset at a given span position. (X&#x2212;X)/(X&#x2212;X) at 100% span position is about 1 and (X&#x2212;X)/(X&#x2212;X) at 90% span position is about 1.

An airfoil for a turbine engine includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between an axial leading edge location and a span position that is at least a third order polynomial with a generally U-shaped curve having an initial negative slope followed by a positive slope. The positive slope leans aftward and the negative slope leans forward. The curve has a critical point in the range of 30-50% span position at which the curve changes from the negative slope to the positive slope. The curve is generally linear from 55% span to 75% span and has a positive slope that increases at a rate of about 0.0875 inch (2.22 mm) per 1% span, +/&#x2212;0.04 inch (1.01 mm) per 1% span.

An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential leading edge location and a span position that corresponds to a curve that is at least a third order polynomial with a generally S-shaped curve that has an initial negative slope followed by a positive slope and then a second negative slope. The positive slope leans toward the suction side and the negative slopes lean toward the pressure side.

In one exemplary embodiment, an airfoil for a turbine engine includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to tangential leading and trailing edge curves and a tangential stacking offset curve. The airfoil extends from a root. A zero tangential reference point corresponds to tangential center of the root. Ycorresponds to a tangential distance from a leading edge to the reference point at a given span position. Ycorresponds to a tangential distance from a trailing edge to the reference point at a given span position. Yd corresponds to a tangential stacking offset at a given span position. (Y&#x2212;Y)/(Y&#x2212;Y) at 40% span position is about 1.5 and (Y&#x2212;Y)/(Y&#x2212;Y) at 20% span position is about 2.

An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starts at the 0% span position is either zero or positive. The first critical point is less than 15% span.

An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a stacking offset and a span position that includes at least one positive and negative slope. The positive slope leans aftward and the negative slope leans forward relative to an engine axis. The positive slope crosses an initial axial stacking offset corresponding to the 0% span position at a zero-crossing position. A first axial stacking offset X1 is provided from the zero-crossing position to a negative-most value on the curve. A second axial stacking offset X2 is provided from the zero-crossing position to a positive-most value on the curve. A ratio of the second to first axial stacking offset X2/X1 is less than 2.0.

In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10&#xb0;. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.

An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10&#xb0; to 20&#xb0; in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning. The trailing edge sweep angle is positive from 0%-95% span. A positive-most trailing edge sweep angle is within the range of 10&#xb0; to 20&#xb0; in the range of 40-70% span position. The airfoil is a fan blade for the turbine engine.

An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains constant or has a decreasing total chord length from the first peak toward the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm). The curve is at least a third order polynomial and has an initial positive slope.

An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10&#xb0; to 20&#xb0; in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span.

A gas turbine engine include a combustor section arranged between a compressor section and a turbine section. A fan section has multiple fan blades. A geared architecture couples the fan section to the turbine section or compressor section. The fan blades include an airfoil that has pressure and suction sides. The airfoil extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.

An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral is positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning. The airfoil includes at least one of a least negative dihedral in a range of 5-15% span position, a least negative dihedral in a range of 0-10% span position and a least positive trailing edge dihedral in a 40%-55% span position.

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Middletown, CT, United States of America

Darryl Whitlow