US 11,920,539 B1
Gas turbine exhaust nozzle noise abatement
Kishore Ramakrishnan, Rexford, NY (US); Steven B. Morris, Mason, OH (US); Nikolai N. Pastouchenko, Latham, NY (US); and Trevor Howard Wood, Clifton Park, NY (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Oct. 12, 2022, as Appl. No. 17/964,097.
Int. Cl. F02K 1/48 (2006.01); F01D 25/30 (2006.01)
CPC F02K 1/48 (2013.01) [F01D 25/30 (2013.01); F05D 2220/323 (2013.01); F05D 2240/128 (2013.01); F05D 2260/96 (2013.01)] 11 Claims
OG exemplary drawing
 
1. An exhaust nozzle for a gas turbine engine, the exhaust nozzle comprising:
a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end, wherein each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root; and
wherein at least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip, and wherein the inner wall extends along the first segment, the second segment and the third segment; and
wherein the first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment; and
wherein the inner wall along the first segment has a radius that is variable with respect to the axial centerline from the root to a first inflection or termination point, the inner wall along the second segment maintains a constant radius from the first inflection or termination point to a second inflection or termination point, and the inner wall along the third segment has a decreasing radius from the second inflection or termination point to the tip.