Fuel manifold with integrally formed retainer for a pilot nozzle in a combustor of a gas turbine engine
A fuel manifold ( 10 ) configured to form a base support structure ( 12 ) to support a plurality of fuel nozzles ( 14 ) including a pilot fuel nozzle is provided. A restraining element ( 30 ) is arranged in the base support structure ( 12 ) to support the pilot fuel nozzle. Restraining element ( 30 ) is integrally formed with the base support structure. The restraining element being integrally formed with the base support structure is effective to arrange for an incremental thickness ( 34 ) in a portion ( 39 ) of a wall ( 34 ) interposed between the inner diameter ( 36 ) of restraining element ( 30 ) and respective proximate edges ( 40 ) of a number of pilot bolt holes ( 32 ) disposed around the restraining element.
1. A method to form a fuel manifold, wherein the fuel manifold comprises:
a base support structure configured to support a plurality of main fuel nozzles and a pilot fuel nozzle in a combustor section of a gas turbine engine;
at least one fuel feed boss axially protruding at an inlet side of the base support structure, wherein said at least one fuel feed boss is integrally connected to the inlet side of the base support structure;
a restraining element centrally arranged at a combustion side of the base support structure to support the pilot fuel nozzle, the combustion side of the base support structure opposite the inlet side of the base support structure, wherein the restraining element is integrally connected to the combustion side of the base support structure, wherein the restraining element extends along a longitudinal axis of the fuel manifold at a distance that protrudes beyond respective tips of rocket bases of the base support structure that support the main fuel nozzles, wherein the base support structure, the at least one fuel feed boss and the restraining element form a one-piece integral fuel manifold,
wherein the method comprises a casting configured to form the one-piece integral fuel manifold,
wherein the casting comprises:
forming a stage fuel gallery in the fuel manifold, said at least one fuel feed boss in fluid communication with the stage fuel gallery;
supporting a ceramic core in a conduit defined in said at least one fuel feed boss; and
removing the ceramic core by way of core leaching through the conduit in said at least one fuel feed boss.
2. A method to form a fuel manifold, the method comprising:
generating a computer-readable three-dimensional (3D) model of the fuel manifold, the model defining a digital representation comprising:
a base support structure configured to support a plurality of main fuel nozzles and a pilot fuel nozzle in a combustor section of a gas turbine engine;
at least one fuel feed boss axially protruding at an inlet side of the base support structure, wherein said at least one fuel feed boss is integrally connected to the inlet side of the base support structure;
a restraining element centrally arranged at a combustion side of the base support structure to support the pilot fuel nozzle, the combustion side of the base support structure opposite the inlet side of the base support structure, wherein the restraining element is integrally connected to the combustion side of the base support structure, wherein the restraining element extends along a longitudinal axis of the fuel manifold at a distance that protrudes beyond respective tips of rocket bases of the base support structure that support the main fuel nozzles, wherein the base support structure, the at least one fuel feed boss and the restraining element form a one-piece integral fuel manifold; and
manufacturing the fuel manifold in accordance with the generated three-dimensional model using an additive manufacturing process.