United Technologies Corporation

Raytheon Technologies Corporation

David P Houston

Frederick M Schwarz

Tracy A Propheter-Hinckley

Daniel Bernard Kupratis

Benjamin T Fisk

Michael Gonsor

Bryan C Atkins

Eric W Malmborg

Robert J Morris

Anita L Tracy

Richard A Lomenzo

James R Midgley

Robert J Esteve

Wieslaw A Chlus

Timothy Dale

Joseph W Bridges, Jr

Paul J Hiester

David M Nissley

Timothy B Winfield

Madeline Campbell

Marnie A Rizo

Natalie A Pelland

David Airey

William R Graves

Jason Elliott

Gregory M Dolansky

Robert A Grelotti

David F Cloud

Scott C Billings

Ethan C Drew

Paul D Kudra

Sanford E Kelley, Iii

Madeline N Campbell

Jason Elliot

Ethan Drew

A turbomachine airfoil element has an airfoil. The airfoil has an inboard end, an outboard end, a leading edge, a trailing edge, a pressure side, and a suction side. A span between the inboard and an outboard end is 1.4-1.6 inch. A chord length at 50% span is 0.9-1.4 inch. The element is remanufactured by providing first, second, third, fourth, and fifth mode resonance frequencies respectively of 2591.5&#xb1;10% Hz, 4675.2&#xb1;10% Hz, 7892.9&#xb1;10% Hz, 10098.2&#xb1;10% Hz, and 14808.2&#xb1;10% Hz.

Turbomachine blade

A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

Gas turbine engine with lifing calculations based upon actual usage

A dovetail root of a fan blade configured for operation within the fan assembly of a gas turbine engine. The dovetail root is imparted with a compressive residual stress layer along the outer faces of the dovetail root preventing crack formation within the dovetail root when the gas turbine engine is in operation. To further protect and structurally enhance the dovetail root, a wear covering is disposed on the dovetail root. The wear covering may consist of a composite laminate layer that is bonded to the metallic core of the dovetail root providing additional cracking protection of the dovetail root when the gas turbine engine is in operation.

Fan blade root

A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

Geared turbofan gas turbine engine architecture

An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge between a radially outer end and a radially inner end. The first sidewall and the second sidewall at least partially define a cavity extending radially in the airfoil body. A damper member has a free radially inner end in the cavity and a free radially outer end in the cavity. The damper member is free-floating in the cavity.

Airfoil including loose damper

A rotor stack assembly for a gas turbine engine includes a first rotor assembly and a second rotor assembly axially downstream from the first rotor assembly. The first rotor assembly and the second rotor assembly include a rim, a bore and a web that extends between the rim and the bore. A tie shaft is positioned radially inward of the bores. The tie shaft maintains a compressive load on the first rotor assembly and the second rotor assembly. The compressive load is communicated through a first load path of the first rotor assembly and a second load path of the second rotor assembly. At least one of the first load path and the second load path is radially inboard of the rims.

Gas turbine engine rotor stack assembly

An airfoil attachment according to one example of this disclosure includes an airfoil and a disk supporting the airfoil. Further, there are primary contact surfaces and secondary contact surfaces between the airfoil and the disk. The secondary contact surfaces are not engaged during a normal operating condition.

Redundant airfoil attachment

A turbomachine airfoil element has an airfoil. The airfoil has an inboard end, an outboard end, a leading edge, a trailing edge, a pressure side, and a suction side. A span between the inboard and an outboard end is 1.4-1.6 inch. A chord length at 50% span is 0.9-1.4 inch. At least three of the following resonance frequencies are present. A first mode resonance frequency is 2591.5&#xb1;10% Hz. A second mode resonance frequency is 4675.2&#xb1;10% Hz. A third mode resonance frequency is 7892.9&#xb1;10% Hz. A fourth mode resonance frequency is 10098.2&#xb1;10% Hz. A fifth mode resonance frequency is 14808.2&#xb1;10% Hz.

An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is loose within the cavity.

An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity and is free-floating within the cavity.

Airfoil with break-way, free-floating damper member

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Glastonbury, CT, United States of America

David P Houston