Gas turbine engine and fuel nozzle therefor
A gas turbine engine comprising a combustion section having a case and a combustor, the combustor disposed at least partially in the case. The combustor comprises a dome assembly, a liner at least partially defining a combustion chamber, a plurality of mounting arms extending forward from the dome assembly, and a fuel nozzle assembly coupled with the dome assembly and including a mounting base. The mounting base couples with the case and engages with a first mounting arm of the plurality of mounting arms and a second mounting arm of the plurality of mounting arms.
1 . A gas turbine engine comprising:
a compressor section, a combustion section, and a turbine section in a serial flow arrangement, the combustion section comprising:
a case; and
a combustor disposed at least partially in the case and comprising:
a dome assembly;
a liner coupled with the dome assembly and at least partially defining a combustion chamber;
a plurality of mounting arms extending forward from the dome assembly; and
a fuel nozzle assembly coupled with the dome assembly and including a mounting base, the mounting base coupled with the case and engaged with a first mounting arm of the plurality of mounting arms and a second mounting arm of the plurality of mounting arms.
2 . The gas turbine engine of claim 1 , wherein the mounting base is rigidly fixed to an inner surface of the case.
3 . The gas turbine engine of claim 1 , wherein a fastener extends through the case and is fastened to the first mounting arm.
4 . The gas turbine engine of claim 1 , wherein the first mounting arm restricts rotation of the mounting base.
5 . The gas turbine engine of claim 1 , wherein a protrusion extends from one of the mounting base or the first mounting arm, and the protrusion is received in a recess of the other of the mounting base or the first mounting arm.
6 . The gas turbine engine of claim 5 , wherein the protrusion extends from the mounting base.
7 . The gas turbine engine of claim 6 , wherein the first mounting arm includes a pair of projections that at least partially define the recess.
8 . The gas turbine engine of claim 7 , wherein the mounting base and the first mounting arm include a first engaged configuration in which the protrusion is spaced from the first mounting arm, and a second engaged configuration in which the protrusion is in contact with one projection of the pair of projections to restrict movement of the mounting base relative to the dome assembly.
9 . The gas turbine engine of claim 7 , wherein at least one projection of the pair of projections is located forward of the first mounting arm.
10 . The gas turbine engine of claim 5 , wherein a distal end of the protrusion includes a bulbous tip.
11 . The gas turbine engine of claim 5 , wherein the mounting base includes the recess; and
wherein the protrusion extends from an outer radial surface of the first mounting arm relative to a centerline of the combustor and is received in the recess of the mounting base.
12 . The gas turbine engine of claim 11 , wherein the fuel nozzle assembly is a first fuel nozzle assembly, the mounting base is a first mounting base, and the recess is a first recess;
wherein the combustor further comprises a second fuel nozzle assembly including a second mounting base;
wherein the second mounting base defines a second recess; and
wherein the protrusion is partially received in both the first recess and the second recess.
13 . The gas turbine engine of claim 12 , wherein the first mounting base is in contact with the second mounting base.
14 . The gas turbine engine of claim 12 , wherein the first mounting base and the second mounting base are in contact with the first mounting arm.
15 . The gas turbine engine of claim 12 , wherein the second mounting base includes a first pair of second nozzle projections that extends toward the first mounting base to at least partially define the second recess.
16 . The gas turbine engine of claim 15 , wherein a first pair of first nozzle projections extend from the first mounting base, and the first pair of second nozzle projections is in contact with the first pair of first nozzle projections.
17 . A method of assembling a turbine engine including a case and a combustor with a dome assembly, a combustor liner, a plurality of mounting arms extending forward from the dome assembly, and a fuel nozzle assembly, the method comprising:
coupling the fuel nozzle assembly with the dome assembly;
restricting movement of a mounting base of the fuel nozzle assembly relative to the dome assembly between a first mounting arm and a second mounting arm;
inserting the combustor at least partially into the case; and
coupling the mounting base with the case.
18 . The method of claim 17 , wherein a protrusion extends from one of the mounting base or the first mounting arm and a recess is formed in the other of the mounting base or the first mounting arm; and
wherein the restricting the movement of the mounting base includes receiving the protrusion in the recess.
19 . The method of claim 17 , wherein the restricting the movement of the mounting base includes rigidly fixing the mounting base to an inner surface of the case.
20 . The method of claim 17 , wherein the restricting the movement of the mounting base includes inserting a fastener through the case, the mounting base, and the first mounting arm.