Raytheon Technologies Corporation

United Technologies Corporation

Raytheon Technology Corporation

Xuedong Zhou

Konstantinos Panagiotis Giannakopoulos

John Joseph Papalia

Mark David Ring

Kurt R Heinemann

Christopher B Jelks

Joseph Wieser

Sumin Tao

Kate Hudon

Michael A Weisse

Joseph C Straccia

Zhen Wu

Evan K Fink

Daniel A Bales

Lisa I Brilliant

Eric W Malmborg

Russell Albert Beers

Dmitri Novikov

Linda S Li

William R Graves

Lee Drozdenko

Sue-Li Chuang

Christopher St Mary

Charles P Gendrich

Kenneth A Frisk

Robert C Dolan

Brian J Schuler

Kaliya Balamurugan

Randy P Salva

Francis B Parisi

Jordan J Franklin

Kimberly Pash Boyington

Steven T Gordon

Jeff M Carrico

Joseph Steele

Han J Yu

Danoris Garcia-Chabrier

Konstantinos Panagiotis Giannakopolous

Mouhamadou Diop

Daniel W Yebo

Christopher Treese

Tri Nguyen

David Mikol

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 4.47-4.77 inch (113.5-121.2 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 2.57-2.87 inch (65.3-72.9 mm). The airfoil element includes at least two of a first mode with a frequency of 297&#xb1;10% Hz, a second mode with a frequency of 1035&#xb1;10% Hz, a third mode with a frequency of 1488&#xb1;10% Hz, a fourth mode with a frequency of 1524&#xb1;10% Hz, a fifth mode with a frequency of 2855&#xb1;10% Hz and a sixth mode with a frequency of 4462&#xb1;10% 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 3.68-3.98 inch (93.5-101.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 1.75-2.05 inch (44.5-52.1 mm). The airfoil element includes at least two of a first mode with a frequency of 436&#xb1;10% Hz, a second mode with a frequency of 1557&#xb1;10% Hz, a third mode with a frequency of 1424&#xb1;10% Hz, a fourth mode with a frequency of 1870&#xb1;10% Hz, a fifth mode with a frequency of 3321&#xb1;10% Hz and a sixth mode with a frequency of 3957&#xb1;10% Hz.

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 2.99-3.29 inch (75.9-83.6 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 1.44-1.74 inch (36.6-44.2 mm). The airfoil element includes at least two of a first mode with a frequency of 430&#xb1;10% Hz, a second mode with a frequency of 1459&#xb1;10% Hz, a third mode with a frequency of 2036&#xb1;10% Hz, a fourth mode with a frequency of 3615&#xb1;10% Hz, a fifth mode with a frequency of 4722&#xb1;10% Hz and a sixth mode with a frequency of 5591&#xb1;10% Hz.

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 0.46-0.59 inch (11.8-14.9 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 0.73-0.86 inch (18.6-21.9 mm). The airfoil element includes at least two of a first mode with a frequency of 5133&#xb1;15% Hz, a second mode with a frequency of 8542&#xb1;15% Hz, a third mode with a frequency of 15487&#xb1;15% Hz, a fourth mode with a frequency of 18774&#xb1;15% Hz, a fifth mode with a frequency of 24295&#xb1;15% Hz and a sixth mode with a frequency of 27084&#xb1;15% Hz.

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 4.35-4.65 inch (110.5-118.1 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 2.45-2.75 inch (62.2-69.9 mm). The airfoil element includes at least two of a first mode with a frequency of 255&#xb1;10% Hz, a second mode with a frequency of 818&#xb1;10% Hz, a third mode with a frequency of 1439&#xb1;10% Hz, a fourth mode with a frequency of 2035&#xb1;10% Hz, a fifth mode with a frequency of 3033&#xb1;10% Hz and a sixth mode with a frequency of 3740&#xb1;10% Hz.

An airfoil 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 0.70-0.83 inch (17.8-21.1 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 0.34-0.45 inch (8.5-11.5 mm). The airfoil element includes at least three of a first mode with a frequency of 3748&#xb1;15% Hz, a second mode with a frequency of 6416&#xb1;15% Hz, a third mode with a frequency of 14418&#xb1;15% Hz, a fourth mode with a frequency of 17417&#xb1;15% Hz, a fifth mode with a frequency of 19326&#xb1;15% Hz and a sixth mode with a frequency of 26648&#xb1;15% Hz.

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 2.85-3.15 inch (72.4-80.0 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 1.52-1.82 inch (38.6-46.2 mm). The airfoil element includes at least two of a first mode with a frequency of 506&#xb1;10% Hz, a second mode with a frequency of 1732&#xb1;10% Hz, a third mode with a frequency of 2268&#xb1;10% Hz, a fourth mode with a frequency of 4007&#xb1;10% Hz, a fifth mode with a frequency of 4851&#xb1;10% Hz and a sixth mode with a frequency of 6416&#xb1;10% Hz.

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 3.45-3.75 inch (87.6-95.3 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 1.55-1.85 inch (39.4-47.0 mm). The airfoil element includes at least two of a first mode with a frequency of 424&#xb1;10% Hz, a second mode with a frequency of 1401&#xb1;10% Hz, a third mode with a frequency of 1770&#xb1;10% Hz, a fourth mode with a frequency of 3336&#xb1;10% Hz, a fifth mode with a frequency of 3378&#xb1;10% Hz and a sixth mode with a frequency of 4141&#xb1;10% Hz.

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 17.2-18.2 inches (436-462 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 10.0-11.0 inches (255-281 mm). The airfoil element includes at least two of a first mode with a frequency of 51&#xb1;10% Hz, a second mode with a frequency of 147&#xb1;10% Hz, a third mode with a frequency of 267&#xb1;10% Hz, a fourth mode with a frequency of 350&#xb1;10% Hz, a fifth mode with a frequency of 454&#xb1;10% Hz and a sixth mode with a frequency of 619&#xb1;10% Hz.

An airfoil including an airfoil body, a recessed portion of a first depth in a first side of the airfoil body, the recessed portion including a plurality of pockets of a second depth located within the recessed portion and ribs of the first depth located between the pockets, a cover configured to fit into the recessed portion such that an interior surface of the cover engages the ribs and an exterior surface of the cover is about flush with an exterior surface of the first side of the airfoil body, and a high energy beam weld configuration extending through the cover and into the ribs and positioned to attach the cover to the ribs.

Power beam welded cavity-back titanium hollow fan blade

Growing community of inventors

Glastonbury, CT, United States of America

Xuedong Zhou