US 11,815,268 B2
Main mixer in an axial staged combustor for a gas turbine engine
Zhongtao Dai, West Hartford, CT (US); Lance L. Smith, West Hartford, CT (US); and Jeffrey M. Cohen, Hebron, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Jul. 8, 2021, as Appl. No. 17/370,154.
Application 17/370,154 is a division of application No. 15/371,653, filed on Dec. 7, 2016, granted, now 11,149,952.
Prior Publication US 2021/0372622 A1, Dec. 2, 2021
Int. Cl. F23R 3/28 (2006.01); F23R 3/14 (2006.01)
CPC F23R 3/286 (2013.01) [F23R 3/14 (2013.01); F23R 2900/03041 (2013.01); F23R 2900/03042 (2013.01); F23R 2900/03044 (2013.01); Y02T 50/60 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A main mixer, comprising:
a swirler along an axis; and
a swirler hub along the axis, the swirler hub having a fuel manifold and a centerbody, the centerbody forms an inner surface of a contoured annular mixer passage, and an inner surface of the swirler forms an outer surface of the contoured annular mixer passage, wherein the centerbody of the swirler hub forms a non-circular inner surface of the contoured annular mixer passage and an inner surface of the swirler forms a non-circular outer surface of the contoured annular mixer passage, and wherein an outer surface of the centerbody of the swirler hub forms a multiple of lobes of the contoured annular mixer passage and the inner surface of the swirler forms a multiple of lobes of the contoured annular mixer passage.