US 11,808,455 B2
Gas turbine engine combustor with integral fuel conduit(s)
Lawrence A. Binek, Glastonbury, CT (US); Timothy S. Snyder, Glastonbury, CT (US); and Sean R. Jackson, Palm City, FL (US)
Assigned to RTX CORPORATION, Farmington, CT (US)
Filed by Raytheon Technologies Corporation, Farmington, CT (US)
Filed on Nov. 24, 2021, as Appl. No. 17/535,133.
Prior Publication US 2023/0160574 A1, May 25, 2023
Int. Cl. F23R 3/00 (2006.01); F23R 3/28 (2006.01)
CPC F23R 3/28 (2013.01) [F23R 3/002 (2013.01)] 18 Claims
OG exemplary drawing
 
1. An assembly for a gas turbine engine, comprising:
a combustor comprising a combustor wall that forms a peripheral boundary of a combustion chamber within the combustor;
a fuel conduit extending along and formed integral with the combustor wall, the fuel conduit disposed outside of the combustion chamber;
a turbine engine case with a plenum formed by and disposed between the turbine engine case and the combustor wall; and
a fuel manifold extending along and formed integral with the turbine engine case, the fuel manifold fluidly coupled with the fuel conduit.