US 11,867,125 B2
Fuel manifold adapter
Gavin Rohiteshwar Kisun, Mississauga (CA); and Guy Lefebvre, St-Bruno-de-Montarville (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Jun. 30, 2021, as Appl. No. 17/363,423.
Prior Publication US 2023/0003171 A1, Jan. 5, 2023
Int. Cl. F02C 7/22 (2006.01); F23R 3/60 (2006.01)
CPC F02C 7/222 (2013.01) [F05D 2220/323 (2013.01); F05D 2240/35 (2013.01); F05D 2260/31 (2013.01); F23R 3/60 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A fuel system of an aircraft engine, comprising:
the aircraft engine having a centerline axis;
a fuel manifold having an inlet nozzle, the fuel manifold mounted at a first mounting point of the aircraft engine, the inlet nozzle having a nozzle bore facing in a first direction;
a fuel source mounted at a second mounting point of the aircraft engine, the fuel source having a source bore facing in a second direction;
a fuel manifold adapter mounted in fluid communication between the fuel source and the inlet nozzle, the fuel manifold adapter including:
a body having a body-output interface defining a downstream end of a body passage relative to a fuel flow through the fuel manifold adapter, the body passage including a body bore extending through the body about a bore axis parallel to the centerline axis, the body-output interface movably and fluidly connected to the inlet nozzle of the fuel manifold, and a body-input interface defining an upstream end of the body passage, the body-input interface rigidly and fluidly connected to the fuel source; and
a transfer tube having an upstream-tube end slidably engaged with the body along the bore axis via the body bore, the transfer tube having a downstream-tube end opposite the upstream-tube end slidably engaged along the bore axis with the nozzle bore of the inlet nozzle of the fuel manifold, the downstream-tube end defining a downstream end of the fuel manifold adapter.