United Technologies Corporation

Raytheon Technologies Corporation

Raytheon Technology Corporation

Kaliya Balamurugan

Daniel Benjamin

Daniel R Kapszukiewicz

Jason Husband

Xuedong Zhou

Christopher St Mary

Charles P Gendrich

John Joseph Papalia

Joseph Wieser

Zhen Wu

Jeff M Carrico

Joseph Steele

Danoris Garcia-Chabrier

Robert B Berkley

Robert L Williston

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.

Gas turbine engine airfoil frequency design

A multi-shaft assembly includes an inner shaft and an outer shaft coaxially aligned with the inner shaft to establish a shared axis of rotation. The multi-shaft assembly also includes an ablatable shaft feature with a lubricant surface coating on an interior surface of the outer shaft and an ablatable metallic alloy layer overlaying a portion of the lubricant surface coating with a radial air gap formed between the ablatable metallic alloy layer and an exterior surface of the inner shaft.

Ablatable shaft feature in a gas turbine engine

Systems and methods for reducing friction during gas turbine engine assembly may comprise, a rear hub which may comprise a conical web, a horizontal arm coupled to the conical web, and/or a hub kickstand coupled to the conical web. The conical web, horizontal arm, and/or hub kickstand may converge at a pivot point. The hub kickstand may be removably coupled to the tie shaft.

Systems and methods for reducing friction during gas turbine engine assembly

A fastener arrangement has first and second threaded members. The fastener arrangement includes the first threaded member having threads that extend from a first end to a second end. The threads have a thread contour that is provided by load and clearance flank surfaces that are joined to one another by crests and roots. The crest provides a crest diameter. A root provides a root diameter and is arranged between adjoining threads. At least one thread near the first end has a weakened thread contour that decreases rigidity of the one thread compared to other threads. The threads extend along an axis. The crest diameter of the second threaded member varies and lies along crest angle relative to the axis and comprises a second threaded member that has load flank surfaces that are engaging the load flank surfaces of the first threaded member at thread contact interfaces. The thread contact interfaces are smaller towards the second end than thread contact interfaces toward the first end.

Thread load distribution

A fastener arrangement includes a threaded member having threads extending from a first end to a second end. The threads have a thread contour provided by a load and clearance flank surfaces joined to one another by a crest and root. For the external threaded member the crest provides a crest diameter, and a root provides a root diameter and is arranged between adjoining threads. At least one thread near the first end has a weakened thread contour that decreases rigidity of the one thread compared to other threads, enabling axial loads to be distributed more evenly between the threads.

An exemplary device for testing a gas turbine engine component includes a shaft that is configured to be rotated. A first hub is selectively fixed to the shaft near a first end of the first hub with an opposite, second end spaced from the shaft. A second hub is selectively fixed to the shaft near a first end of the second hub with an opposite, second end spaced from the shaft. The second ends of the hubs each have a feature for supporting the component between the first and second hubs at a location spaced from the shaft for introducing a load on the component near the location.

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Newington, CT, United States of America

Kaliya Balamurugan