General Electric Company

John Duong

Jeremy Peter Latimer

Eric Richard Bonini

Michael James Dutka

Matthew John McKeever

Marc Edward Blohm

Christopher Edward LaMaster

Ya-Tien Chiu

Paul Griffin Delvernois

Kelvin Rono Aaron

Govindarajan Rengarajan

Venkata Siva Prasad Chaluvadi

Alexander David Shrum

San-Dar Gau

Franco Monteleone

Thomas Robbins Tipton

Peter Samuel King

Paul DeIvenois

Jamie Dean Lumpkin

The present application and the resultant patent provide an axial compressor for a gas turbine engine. The compressor may include a rotor disk positioned along an axis of the compressor. The rotor disk may include a slot defined about a radially outer surface of the rotor disk, and the slot may include a slot planar surface facing away from the rotor disk. The compressor also may include a compressor blade coupled to the rotor disk via the slot. The compressor blade may include a platform positioned over the radially outer surface of the rotor disk, and the platform may include a platform sealing edge facing toward the rotor disk. The compressor further may include a gap defined between the platform sealing edge and the slot planar surface, wherein the gap is configured to control a flow of leakage air from a high-pressure side of the compressor blade to a low-pressure side of the compressor blade. The present application and the resultant patent further provide a related method of controlling stage-to-stage leakage in an axial compressor of a gas turbine engine.

Axial compressor and method for controlling stage-to-stage leakage therein

An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table, the scalable table selected from the group of tables consisting of TABLES 1-11, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Airfoil shape for a compressor

An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Article of manufacture

An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a TABLE 1. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.

Growing community of inventors

Greer, SC, United States of America

John Duong