Patent ID: 11867125
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
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.