Gas turbine engine flange assembly including flow circuit
The disclosure is directed to a unique apparatus having a gas turbine engine flange assembly. Also disclosed is a unique system having a gas turbine engine flange assembly in which a fluid flow circuit is provided. Also disclosed are apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engine flange assemblies, in which a fluid flow circuit extends between flanges or from a cavity within a turbine engine case to an interior portion of a flange assembly.
1. An apparatus comprising:
a gas turbine engine flange assembly including:
a first flange,
a second flange, and
a third flange,
the second flange being positioned intermediate the first flange and the third flange; and
a fluid flow circuit extending intermediate the first flange and the second flange, across the second flange, and intermediate the second flange and the third flange;
wherein the fluid flow circuit includes a first flow passage intermediate the first flange and the second flange, at least one opening provided in the second flange, and a second flow passage intermediate the second flange and the third flange;
wherein the first flow passage is bordered by a first shim plate, the first flange and the second flange;
further comprising a second shim plate positioned intermediate the second flange and the third flange, the second shim plate defining a boundary of a portion of the fluid flow circuit.
2. The apparatus of claim 1 , further comprising a fillet cavity intermediate the first flange and the second flange.
3. The apparatus of claim 1 , further comprising a fillet cavity intermediate the second flange and the third flange, the fillet cavity defining a boundary of a portion of the fluid flow circuit.
4. The apparatus of claim 1 , further comprising a recess provided in one of the first flange, the second flange, and the third flange, the recess defining a boundary of a portion of the fluid flow circuit.
5. The apparatus of claim 1 , further comprising means for routing fluid flow through the flange assembly.
6. The apparatus of claim 1 , wherein the flow circuit extends from a higher pressure cavity to a lower pressure cavity and includes a first recess provided in the second flange, a first fillet cavity intermediate the first flange and the second flange, the first flow passage the at least one opening provided in the second flange, the second flow passage, a second fillet cavity intermediate the second flange and the third flange, and a second recess provided in the second flange;
wherein the second flow passage is bordered by the second shim plate, the second flange and the third flange.
7. The apparatus of claim 1 , wherein the first flange extends from a compressor case, and the third flange extends from an outer combustor case.
8. The apparatus of claim 1 , wherein the first flange extends from an outer combustor case, and the third flange extends from a turbine case.
9. The apparatus of claim 1 , wherein the first flange extends from a combustor case, and the third flange extends from an afterburner case.
10. The apparatus of claim 1 , wherein the second flange extends from a support.
11. A system comprising:
a first gas turbine engine case;
a second gas turbine engine case;
a flange assembly coupling the first gas turbine engine case and the second gas turbine engine case, the flange assembly extending circumferentially about at least a portion of the first gas turbine engine case; and
a fluid flow circuit extending from a cavity within the first gas turbine engine case to an interior portion of the flange assembly;
wherein the flange assembly includes a first flange, a second flange, and a third flange, the second flange being positioned intermediate the first flange and the third flange;
wherein the fluid flow circuit extends from a higher pressure cavity to a lower pressure cavity and includes a first flow passage intermediate the first flange and the second flange, an opening provided in the second flange, and a second flow passage intermediate the second flange and the third flange; and
wherein the first flow passage is bordered by a first shim plate, the first flange and the second flange
further comprising a second shim plate positioned intermediate the second flange and the third flange, the second shim plate defining a boundary of a portion of the fluid flow circuit.
12. The system of claim 11 , wherein the first gas turbine engine case is a combustor case and the second gas turbine engine case is a compressor case.
13. The system of claim 11 , wherein the first gas turbine engine case is a combustor case and the second gas turbine engine case is a turbine case.
14. The system of claim 11 , wherein the first gas turbine engine case is an afterburner case and the second gas turbine engine case is a turbine case.