Patent ID: 11939922
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 6:
7. A gas turbine engine having an axial centerline, the gas turbine engine comprising:
a combustor;
a bladed turbine rotor configured to rotate in response to a combustion gas flow from the combustor;
a first case extending circumferentially about the axial centerline, the first case surrounding at least a portion of the combustor;
a second case extending circumferentially about the axial centerline, the second case positioned axially adjacent the first case, the second case surrounding at least a portion of the bladed turbine rotor;
a flow divider valve mounted on and to the first case;
a fuel supply tube connected to the flow divider valve;
a fuel manifold adapter mounted to the second case, the fuel manifold adapter including a first mount portion and a second mount portion, the first mount portion connected to the fuel supply tube, the second mount portion connected to the second case, the first mount portion moveable relative to the second mount portion; and
a fuel manifold extending circumferentially about the axial centerline, the fuel manifold is mounted on and to the second case, and the fuel manifold is connected to the first mount portion;
wherein the fuel manifold is located axially between the fuel manifold adapter and the flow divider valve;
wherein the first mount portion includes a first fastener;
wherein the second mount portion includes a second fastener;
wherein the fuel manifold adapter includes a link including a link body, the link body rotatably mounted to each of the first fastener and the second fastener; and
wherein the link includes a first bearing and a second bearing, each of the first bearing and the second bearing mounted within the link body, the first bearing surrounding the first fastener, the second bearing surrounding the second fastener.