US 11,913,342 B1
Variable guide vane assembly and control system thereof
Daniel Coutu, Longueuil (CA); and Pierre-Charles Payer, Hudson (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Apr. 18, 2023, as Appl. No. 18/302,441.
Int. Cl. F01D 17/14 (2006.01); F01D 17/16 (2006.01); F04D 27/02 (2006.01); F02C 9/20 (2006.01); F02C 7/042 (2006.01); F04D 27/00 (2006.01)
CPC F01D 17/14 (2013.01) [F01D 17/16 (2013.01); F02C 7/042 (2013.01); F02C 9/20 (2013.01); F04D 27/002 (2013.01); F04D 27/0246 (2013.01); F05D 2270/309 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A method of operating a variable guide vane assembly of an aircraft engine, the variable guide vane assembly including guide vanes rotatable about respective spanwise axes and circumferentially distributed about a central axis, the method comprising:
obtaining a target exit flow angle defined between a direction of a flow exiting the guide vanes and the central axis;
predicting an exit flow angle as a function of at least a geometric angle, the exit flow angle defined between the direction of the flow exiting the guide vanes and the central axis, the geometric angle defined between the guide vanes and the central axis; and
in response to a difference between the exit flow angle and the target exit flow angle is being above a threshold, modulating the guide vanes to modify the geometric angle until the difference between the exit flow angle and the target exit flow angle is at or below the threshold.