Method of removing bearing compartment
The present disclosure provides a method of removing a bearing compartment from a gas turbine engine comprising inserting a tool between an aft portion of a low pressure turbine and a forward portion of a turbine exhaust case, the tool comprising one of a single wedge-shaped ring or a plurality of wedge-shaped segments, removing a plurality of fasteners coupling a flange of a bearing compartment housing to the turbine exhaust case, the bearing compartment housing containing the bearing compartment, and removing the bearing compartment housing from an aft portion of the gas turbine engine.
1. A method of removing a bearing compartment from a gas turbine engine, comprising:
inserting a tool between an aft portion of a low pressure turbine and a forward portion of a turbine exhaust case;
removing a plurality of fasteners coupling a flange of a bearing compartment housing to the turbine exhaust case, the bearing compartment housing containing the bearing compartment; and
removing the bearing compartment housing from an aft portion of the gas turbine engine, wherein the turbine exhaust case and the low pressure turbine remain attached to the gas turbine engine while removing the bearing compartment housing.
2. The method of claim 1 , wherein the tool comprises one of a single wedge shaped ring or a plurality of wedge shaped rings and is configured to redistribute weight of the low pressure turbine from the bearing compartment housing to the tool.
3. The method of claim 1 , further comprising decoupling the bearing compartment housing from a low pressure turbine shaft.
4. The method of claim 1 , wherein the tool contacts at least a portion of a radially inward surface of the low pressure turbine and at least a portion of a radially outward surface of the turbine exhaust case.
5. The method of claim 1 , wherein the tool is localized between an upper portion of the low pressure turbine and an upper portion of the turbine exhaust case.
6. The method of claim 1 , wherein the tool comprises a base, an inner ring, an outer ring, and a vertex.
7. The method of claim 1 , wherein the flange extends circumferentially around a radially outer surface of the bearing compartment housing and separates the bearing compartment housing into the bearing compartment and a second bearing compartment.
8. The method of claim 1 , wherein the low pressure turbine and the turbine exhaust case are coupled to the gas turbine engine.
9. The method of claim 1 , wherein removing the bearing compartment housing from the gas turbine engine comprises removing the bearing compartment housing from the gas turbine engine along a central longitudinal axis of the gas turbine engine.
10. The method of claim 1 , wherein removing the bearing compartment housing from the aft portion of the gas turbine engine comprises coupling an aft portion of the bearing compartment housing to a fixture and moving the fixture.
11. The method of claim 1 , further comprising:
inserting a second bearing compartment housing into the gas turbine engine, the second bearing compartment housing containing a second bearing compartment;
coupling the second bearing compartment housing to the turbine exhaust case using the plurality of fasteners; and
removing the tool between the low pressure turbine and the turbine exhaust case.
12. A method of disassembling a gas turbine engine, comprising:
removing from the gas turbine engine a bearing compartment housing that supports a low pressure turbine shaft when the gas turbine engine is in an assembled state without removing the low pressure turbine shaft, wherein a turbine exhaust case and a low pressure turbine coupled to the low pressure turbine shaft remain attached to the gas turbine engine while removing the bearing compartment housing.
13. The method of claim 12 , further comprising:
prior to removing the bearing compartment housing, inserting a tool between an aft portion of the low pressure turbine of the gas turbine engine and a forward portion of the turbine exhaust case of the gas turbine engine.
14. The method of claim 13 , wherein the tool is configured to redistribute weight of the low pressure turbine from the bearing compartment housing to the tool.
15. The method of claim 14 , wherein the tool comprises one of a single wedge-shaped ring or a plurality of wedge-shaped segments.
16. The method of claim 13 , wherein removing the bearing compartment housing comprises removing the bearing compartment housing from an aft portion of the gas turbine engine.