Raytheon Technologies Corporation

United Technologies Corporation

Daniel C Falk

Jason Elliott

Myron Klein

Byron R Monzon

Darryl Whitlow

William R Graves

Ethan C Drew

Normand P Jacques

James H Moffitt

Jay Thomas Abraham

Normand P Jaques

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.

An impeller includes first and second impeller portions that are secured to one another. An interior cavity is formed between the first and second portions. The first impeller portion supports multiple blades. The first and second impeller portions respectively include first and second surfaces that are secured to one another near a tip of the impeller. Inlet and outlet apertures are provided in the impeller and are in communication with the inner cavity to provide a cooling flow path there through. A circumferential gap is arranged between the first and second impeller portions opposite the tip to permit relative axial movement between the first and second impeller portions during centrifugal loading of the impeller.

Tip clearance centrifugal compressor impeller

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Middletown, CT, United States of America

Daniel C Falk