General Electric Company

Curtis Moeckel

Peter John Wood

Eric Andrew Falk

Andrew Breeze-Stringfellow

Mark Joseph Mielke

Michael Anthony Thomas

Steven Mitchell Taylor

Carlos Ivan Flores

Brian Richard Green

Mark Joseph Frisch

Joseph Michael Bruni

David William Fasig

Matthew Ford Adam

Mark Joseph Stecher

A circular row of non-uniformally spaced vanes includes only one first group and only one second group of adjacent vanes, unequal first and second spacing between adjacent vanes in the first and second groups, and first spacing greater than second spacing. An embodiment with second group including only three adjacent vanes. Second spacing may be about 25%-35% smaller than a nominal uniform spacing used as a design parameter for designing spacing of the non-uniformly spaced stator vanes. Circular row may be sectored. A gas turbine engine section may include one or more rings or circular rows of fixed and/or variable non-uniformally spaced vanes. Method for designing non-uniform vane spacing for circular row includes determining nominal uniform spacing and forming first spacing and second spacing from nominal uniform spacing of vanes.

Non uniform vane spacing

An apparatus and method of controlling a multi-stage compressor of a gas turbine engine having a front-block of stages with variable stator vanes (VSVs), a rear block of stages downstream of the front-block, and a bleed air off-take from at least one of the stages. The method includes sensing the pressure of the bleed air from the bleed air off-take and adjusting the position of the VSV for the front-block.

Controlling a compressor of a gas turbine engine

Gas turbine engine compressor bleed assembly includes annular bleed plenum between annular outer and inner casings circumscribing compressor flowpath of compressor, upstream and downstream bleed ports disposed through inner casing and between compressor flowpath and plenum at upstream and downstream stages. Bleed path extends from downstream bleed port through bleed plenum and out bleed outlet disposed through outer casing. Autonomously actuated valve such as poppet valve disposed in bleed path or downstream bleed port. Autonomously actuated or poppet valve may be set to open at take-off and/or climb. Bleed outlet may be customer and domestic or engine bleed outlet disposed through outer casing and in fluid bleed air communication with bleed plenum. Another assembly may include annular forward and aft bleed outlets connected to plenums. Bleed path extends from downstream bleed port through plenums and out forward bleed outlet.

High pressure compressor augmented bleed with autonomously actuated valve

An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can have decreasing sweep angles for the leading edge and the trailing edge from 50% span to the tip and can have decreasing leading and trailing edge dihedral angles from 50% span to the tip.

Turbine engine compressor blade

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Cincinnati, OH, United States of America

Curtis Moeckel