US 12,228,037 B1
Guide vane assembly with fixed and variable pitch inlet guide vanes
Nicholas Joseph Kray, Mason, OH (US); Brandon Wayne Miller, Liberty Township, OH (US); Gary Willard Bryant, Jr., Loveland, OH (US); and Arthur William Sibbach, Boxford, MA (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Dec. 4, 2023, as Appl. No. 18/527,567.
Int. Cl. F01D 17/16 (2006.01); F01D 9/04 (2006.01)
CPC F01D 17/16 (2013.01) [F01D 9/041 (2013.01); F05D 2220/36 (2013.01); F05D 2240/12 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A guide vane assembly for a nacelle of a gas turbine engine, the gas turbine engine defining a longitudinal axis and an axial direction, the nacelle circumferentially surrounding a plurality of fan blades of the gas turbine engine, the guide vane assembly comprising:
a forward vane; and
an aft vane located aft of the forward vane and forward of the plurality of fan blades when the guide vane assembly is positioned in the nacelle of the gas turbine engine, the forward vane defining a fixed pitch angle and the aft vane being movable between a first pitch angle and a second pitch angle when the guide vane assembly is positioned in the nacelle of the gas turbine engine;
wherein the forward vane defines a forward vane span, wherein the plurality of fan blades each defines a fan blade span, and wherein the forward vane span is from 5% to 50% of the fan blade span of the plurality of fan blades;
wherein the forward vane defines a forward axial length at a radial position, wherein the aft vane defines an aft axial length at the radial position, wherein a ratio of the aft axial length to the forward axial length is from 0.2 to 5.0.