United Technologies Corporation

Pratt-whitney Canada Corp

Raytheon Technologies Corporation

Pratt & Whitney Rocketdyne, Inc.

Myron Klein

Paul Stone

Peter Townsend

Ignatius Theratil

Krishna Prasad Balike

Aldo Abate

Jason Elliott

Ronald Dutton

Milica Kojovic

Robert Venditti

Sean Kelly

Daniel C Falk

Anthony Brown

Byron R Monzon

Darryl Whitlow

William R Graves

Larry Foster

Carl Brian Klinetob

Yehia M El-Aini

Thomas D Kasprow

Andrew Pope

William Richard Ganoe

Ethan C Drew

James H Moffitt

Douglas J Morgan

Jay Thomas Abraham

Stephen J Lindahl

The gas turbine compressor for an aircraft gas turbine engine includes a compressor rotor having a plurality of compressor blades circumferentially distributed around a hub. Each of the compressor blades has an airfoil extending radially outward from the hub to a blade tip. A circumferential row of the compressor blades includes two or more different blade types, at least one modified blade of the two or more different blade types having means for generating different shock patterns between adjacent ones of the two or more different blade types when the gas turbine compressor operates in supersonic flow regimes. The means for generating different shock patterns on the modified blade aerodynamically mistune the two or more different blade types.

Compressor rotor for supersonic flutter and/or resonant stress mitigation

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

In one exemplary embodiment, a turbofan engine comprises a fan section. A core section includes a turbine section arranged fluidly downstream from the compressor section. A combustor is arranged fluidly between the compressor and turbine sections. The fan and core sections are configured to produce a thrust in a range 27,000-35,000 pounds-f (120,102-156,688 N). An airfoil is arranged in the fan section. The airfoil has first and second modes each having a frequency. The first mode has the lowest frequency, and the second mode has the second lowest frequency wherein the second mode frequency is 140 Hz or less at a redline engine speed.

A compressor rotor, such as a fan, for a gas turbine engine is described which includes alternating at least first and second blade types. The leading edge of the second blade types includes a leading edge tip cutback extending to the blade tip thereof. The leading edge tip cutback of the second blade type defines a chord length at the blade tip of the second blade types that is less than that of the first blades types. The first and second blade types generate different shock patterns when the fan or compressor rotor operates in supersonic flow regimes.

A gas turbine engine includes a fan mounting a first group of blades and a second group of blades. The first group of blades and the second group of blades share a profile shape. The first group of blades have a first laminate composition, and the second group of blades have a second laminate composition, distinct from the first laminate composition. A frequency of a vibratory mode of the first group of blades is offset from a frequency of a vibratory mode of the second group of blades.

Mistuned laminate airfoil

A stationary guide vane includes a top platform, a bottom platform, and a vane body located between the top platform and the bottom platform. The vane body includes one or more cavities formed on a side wall of the vane body. One or more of the cavities are filled with vibration damping material and a vane cover is bonded to the vane body over the one or more containers.

Vibration damping for structural guide vanes

A section of a gas turbine engine includes a damper which extends from a disk between a first blade and a second blade to provide a dissipating vibratory motion energy in the form of friction heating.

Non-integral platform and damper for an airfoil

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Higganum, CT, United States of America

Myron Klein