US 12,313,021 B1
Outer nacelle with inlet guide vanes and acoustic treatment
Arthur William Sibbach, Boxford, MA (US); Nicholas Joseph Kray, Mason, OH (US); Brandon Wayne Miller, Liberty Township, OH (US); and Gary Willard Bryant, Jr., Loveland, OH (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Mar. 14, 2024, as Appl. No. 18/604,610.
Int. Cl. F02K 3/06 (2006.01); F01D 9/04 (2006.01); F01D 25/24 (2006.01); F02C 7/045 (2006.01); F02C 7/24 (2006.01); F04D 29/52 (2006.01); F04D 29/54 (2006.01); F04D 29/66 (2006.01)
CPC F02K 3/06 (2013.01) [F02C 7/045 (2013.01); F02C 7/24 (2013.01); F04D 29/526 (2013.01); F04D 29/541 (2013.01); F04D 29/542 (2013.01); F04D 29/664 (2013.01); F04D 29/667 (2013.01); F01D 9/042 (2013.01); F01D 25/24 (2013.01); F05D 2220/36 (2013.01); F05D 2260/14 (2013.01); F05D 2260/96 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine defining an axial direction and a radial direction, the gas turbine engine comprising:
a turbomachine;
a fan rotatable by the turbomachine, the fan comprising a fan blade, the fan blade defining an outer tip along the radial direction, a trailing edge at the outer tip, and a length, LFB, at the outer tip along the axial direction; and
an outer nacelle surrounding the fan and surrounding at least in part the turbomachine, the outer nacelle comprising a stage of pre-swirl inlet guide vanes located upstream of the fan, the stage of pre-swirl inlet guide vanes having a pre-swirl inlet guide vane defining a 15% span location and a leading edge at the 15% span location, the pre-swirl inlet guide vane further defining a length, LIGV, along the axial direction at the 15% span location, the outer nacelle further comprising an inner surface along the radial direction and an acoustic treatment coupled to or integrated with the inner surface, the acoustic treatment defining a length, LAT, along the axial direction; wherein the gas turbine engine defines a length, LS, from the leading edge of the pre-swirl inlet guide vane at the 15% span location to the trailing edge of the fan blade at the outer tip of the fan blade, and wherein the length, LAT, of the acoustic treatment is as follows: (LIGV2/LS)×UCF1<LAT<(LFB3/LIGV)×UCF2, wherein UCF1 is a first unit correction factor equal to 1−1 inch and UCF2 is a second unit correction factor equal to 1−2 inch.