United Technologies Corporation

Raytheon Technologies Corporation

United Technology Corporation

Carl S Richardson

Jonathan J Earl

Mark John Rogers

Richard K Hayford

Kenneth E Carman

Charles H Warner

Robert W Fessenden

Charles R Watson

Ling Liu

Sue-Li Chuang

Paul W Baumann

Dennis R Tremblay

Michael E McMahon

Brian J Schuler

John A Szymbor

Jeffrey S LeShane

Jeff M Carrico

Hope C Rowley

Edwin M Worth

Jonathan Earl

Kenneth E Carmen

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 1.01-1.15 inch (25.7-29.3 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 0.54-0.66 inch (13.6-16.8 mm). The airfoil element includes at least two of a first mode with a frequency of 2033 &#xb1; 15% Hz, a second mode with a frequency of 7023 &#xb1; 15% Hz, a third mode with a frequency of 12082 &#xb1; 15% Hz and a fourth mode with a frequency of 19769 &#xb1; 15% Hz.

Gas turbine engine airfoil frequency design

A vane seal system includes a first non-rotatable vane segment that has a first airfoil with a first pocket at one end thereof. A second non-rotatable vane segment includes a second airfoil with a second pocket at one end thereof spaced by a gap from the first pocket. A seal member spans across the gap and extends in the first pocket and the second pocket. The seal member includes a seal element and at least one spring portion configured to positively locate the seal member in a sealing direction. Also disclosed is a seal for a vane seal system and a method related thereto for damping relative movement between a first pocket and a second pocket.

Vane seal system and seal therefor

A turbomachine airfoil element includes an airfoil that 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 0.46-0.58 inch (11.6-14.7 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 0.66-0.79 inch (16.7-20.0 mm. A first mode has a frequency of 35681&#xb1;15% Hz and a second mode has a frequency of 39218&#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 0.78-0.91 inch (19.7-23.1 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 0.49-0.62 inch (12.5-15.6 mm). The airfoil element includes at least two of a first mode with a frequency of 3533&#xb1;15% Hz, a second mode with a frequency of 8291&#xb1;15% Hz, a third mode with a frequency of 17362&#xb1;15% Hz and a fourth mode with a frequency of 23365&#xb1;15% Hz.

A vane seal system includes a non-rotatable vane segment that has an airfoil with a pocket at one end thereof. The pocket spans in an axial direction between forward and trailing sides, with respect to the airfoil, and in a lateral direction between open lateral sides. A seal member extends in the pocket. The seal member includes a seal element and at least one spring portion that is configured to positively locate the seal member in the axial direction in the pocket. A method for positioning the seal member in a vane seal system includes positively locating the seal member in the axial direction in the pocket using the spring portion.

Vane seal system having spring positively locating seal member in axial direction

A vane tip machining fixture assembly includes a first clamp ring mountable to a fixture, the first clamp ring includes a rigid back ring mounted to a resilient ring.

Vane tip machining fixture assembly

One exemplary embodiment of this disclosure relates to a stator segment. The stator segment includes a first circumferential end face, and a second circumferential end face. Further, the first and second circumferential end faces are misaligned relative to one another.

Stator segment

An assembly for a turbine engine includes a stator vane arrangement and an anti-rotation lug that is rotatably connected to a turbine engine case. The stator vane arrangement includes a platform, an airfoil and an anti-rotation slot. The platform extends circumferentially around an axial centerline and is engaged with the case. The airfoil extends radially from the platform and is arranged circumferentially around the centerline. The slot extends radially into the platform, and is mated with the lug. The lug is configured with a substantially equilateral polygonal geometry.

Lug for preventing rotation of a stator vane arrangement relative to a turbine engine case

A vane cluster includes a split damped outer shroud and an inner shroud spaced from the split damped outer shroud with a multiple of stator vane airfoils that extend between the split damped outer shroud and the inner shroud.

Split damped outer shroud for gas turbine engine stator arrays

A gas turbine engine stator segment has a shroud band and a plurality of blade sections. Each of the blade sections has a first section with a first thickness, second section with a second thickness and a fairing section transitioning between the first and second section. The second section thickness is less than the first section thickness.

Turbine engine compressor stator

A stator assembly having an inner shroud assembly formed of an inner shroud and rubstrip is disclosed. Various construction details and features are developed which relate to durability and manufacturing feasibility are developed. In one detailed embodiment, at the rubstrip is bonded to the thermoplastic shroud. The method is applicable to joining an elastomer, such as silicone rubber material, to a thermoplastic substrate.

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South Berwick, ME, United States of America

Carl S Richardson