Pylon matched fan exit guide vane for noise reduction in a geared turbofan engine

Patent metadata

Field	Value
Publication number	US-9540938-B2
Application number	US-201213721498-A
Country	US
Kind code	B2
Filing date	Dec 20, 2012
Priority date	Sep 28, 2012
Publication date	Jan 10, 2017
Grant date	Jan 10, 2017

Abstract

A disclosed fan section of a gas turbine engine includes a fan rotor having a plurality of fan blades and a duct defining a passageway aft of the fan rotor. A fan exit guide vane is disposed within the duct downstream of the fan blades. The fan exit guide vane includes a plurality of exit guide vanes positioned downstream of the fan rotor with at least two of the plurality of exit guide vanes including different aft geometries for guiding airflow through the passage to reduce pressure distortions at the fan blades.

First claim

What is claimed is:

1. A method of assembling a fan exit guide vane assembly comprising:
defining an airfoil shape that provides desired performance;
defining a family of airfoils shapes including a common forward geometry and differing aft geometry;
determining an acoustic performance characteristic for each of a plurality of circumferential positions;
selecting an airfoil shape from the family of airfoil shapes for each circumferential position of the fan exit guide vane assembly based on an acoustic performance characteristic;
defining a common axial position of a leading edge of each of the exit guide vanes and a common axial spacing of a trailing edge of each of the exit guide vanes from the leading edge; and
installing vanes at each circumferential position of a fan exit guide vane assembly including the selected airfoils based on the acoustic performance characteristic.

2. The method as recited in claim 1 , including defining uniform circumferential spacing between each of the exit guide vanes.

3. The method as recited in claim 1 , including selecting the airfoil shape based on a position of the exit guide vane relative to a structure disposed within a duct downstream of the fan exit guide vane.

4. The method as recited in claim 1 , including selecting the airfoil shape based on a pressure distortion pattern of a fan.

Assignees

• United Technologies Corp

Inventors

• Topol David A
• Potter Glen E
• Thomas Flavien L

Classifications

• Y10T29/49245

  Vane type or other rotary, e.g., fan · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F01D5/142 Primary

  of the blades of successive rotor or stator blade-rows · CPC title

• F05D2260/961

  by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape · CPC title