General Electric Company

Robert A Walter

Caroline Curtis Granda

Jeffrey Howard Nussbaum

Michael Macrorie

Zaher Milad Moussa

David K Christensen

Tara Chaidez

Albert Samuel Melilli

George A Fischer

Anna Wei

David Christensen

A compressor assembly for a gas turbine engine is provided. The compressor assembly includes a rotating impeller including an inlet, an outlet, and a body extending therebetween. The compressor assembly further includes a non-rotating impeller shroud. The body and the shroud define an impeller chamber including a radially inner surface and a radially outer surface. The radially inner surface includes an arcuate flow surface. The flow surface includes a first portion and a second portion extending downstream from the first portion. The impeller chamber includes a variable area wherein a first cross-sectional area is defined between the radially outer surface and the first portion, and a second cross-sectional area is defined downstream from the first cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. A method of operating the compressor assembly is also included.

Engine compressor assembly and method of operating the same

Methods and apparatus for fabricating a rotor blade for a gas turbine engine are provided. The rotor blade includes an airfoil having a first sidewall and a second sidewall, connected at a leading edge and at a trailing edge. The method includes forming the airfoil portion bounded by a root portion at a zero percent radial span and a tip portion at a one hundred percent radial span, the airfoil having a radial span dependent chord length C, a respective maximum thickness T, and a maximum thickness to chord length ratio (T/C ratio), forming the root portion having a first T/C ratio, forming the tip portion having a second T/C ratio, and forming a mid portion extending between a first radial span and a second radial span having a third T/C ratio, the third T/C ratio being less than the first T/C ratio and the second T/C ratio.

Methods and apparatus for reducing vibrations induced to airfoils

The field of this invention is fluid flow control through large conduits. In particular, this invention is contemplated for use in a combined cycle power plant wherein gas turbine exhaust gas is either sent through a heat recovery steam generator (HRSG) or diverted to the atmosphere. The invention is a damper and frame assembly believed to be well suited to the purpose of channeling the hot exhaust gas within the context of a combined cycle power plant either as an isolation damper to the HRSG or a bypass damper to the exhaust stack. One key consideration is the thermal relationship between the damper blade and its adjacent frame and provision is made to provide a damper blade that will not warp and a frame wherein thermal growth and distortion are limited.

Damper

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Melrose, MA, United States of America

Robert A Walter