Ansaldo Energia Switzerland Ag

General Electric Technology Gmbh

Wes Smith

Edward Len Miller

Stephen Wayne Fiebiger

Andreas Martin Mattheiss

Reiner Jochen Digele

Wilm Philipp Hecker

Gregory Edwin Vogel

Alex Torkaman

Richard Whiting

Jeff Tessier

An apparatus for providing improved cooling to a combustion liner of a gas turbine combustor is provided. A plurality of flow deflectors is secured to a flow sleeve in order to improve the flow of impingement air from a flow sleeve to the combustion liner outer surface, such that the amount of impingement air being swept away by a cross flow of cooling air is reduced.

Flow sleeve deflector for use in gas turbine combustor

A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor blade, has an increased surface area over a portion of the airfoil chord length. The increased surface area allows for a greater amount of air to be taken in by the airfoil, thus increasing the air flow through the gas turbine engine.

Adjusted rotating airfoil

A compressor component having an airfoil with a profile in accordance with Table 1 is disclosed. The compressor component, such as a compressor vane, has a decreased surface area over a portion of the airfoil chord length. The decreased surface area compressor vane operates in conjunction with a compressor blade having an increased surface area.

Adjusted stationary airfoil

Growing community of inventors

West Palm Beach, FL, United States of America

Wes Smith