United Technologies Corporation

Raytheon Technologies Corporation

Raytheon Technology Corporation

Zhen Wu

Xuedong Zhou

John Joseph Papalia

Joseph Wieser

Konstantinos Panagiotis Giannakopoulos

Sue-Li Chuang

Christopher St Mary

Charles P Gendrich

Brian J Schuler

Kaliya Balamurugan

Brian C Lund

Scott C Billings

Kimberly Pash Boyington

Joseph Steele

Jeff M Carrico

Jianming Huang

Han J Yu

David Mikol

Danoris Garcia-Chabrier

Jiangming Huang

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 0.46-0.59 inch (11.8-14.9 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 0.73-0.86 inch (18.6-21.9 mm). The airfoil element includes at least two of a first mode with a frequency of 5133&#xb1;15% Hz, a second mode with a frequency of 8542&#xb1;15% Hz, a third mode with a frequency of 15487&#xb1;15% Hz, a fourth mode with a frequency of 18774&#xb1;15% Hz, a fifth mode with a frequency of 24295&#xb1;15% Hz and a sixth mode with a frequency of 27084&#xb1;15% Hz.

Gas turbine engine airfoil frequency design

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.

A heated inlet guide vane is disclosed. The disclosed guide vane may include a body having an inlet cavity disposed alongside of an outlet cavity wherein the outlet cavity is disposed alongside the leading edge of the vane. The inlet cavity is in communication with a source of heated air. The inlet cavity is in communication with the outlet cavity by way of a plurality of impingement holes spaced along the inner wall disposed between the two cavities. Bleed holes are spaced along the length of the outlet cavity. Fresh, heated air enters the outlet cavity along the entire length of the outlet cavity and quickly exits the outlet cavity with minimal cooling so that a uniform d-icing capability is provided along the entire leading edge of the inlet guide vane.

Heated inlet guide vane

A turbine rotor balancing system comprises a circumferential array of mounting features. One or more balance weights are each mounted to the respective associated said mounting feature. Each balance weight comprises: a front wall along the forward face of the mounting feature; an aft wall along the aft face of the mounting feature; and a radially inboard wall. One or more fasteners each extend at least partially through holes of the front wall and rear wall of an associated said balance weight and through a hole of the associated said mounting feature. An abutment surface of the rotor is positioned to engage an outboard end of at least one of the front wall and aft wall of each said balance weight to resist outward radial movement of the weight.

Turbomachine rotor balancing system

Growing community of inventors

Hopkinton, MA, United States of America

Zhen Wu