Methods and systems for turbine rotor balancing
Methods and apparatus for a balance weight access assembly are provided. The assembly includes an access cover, and an access tube including a first opening, a second opening, and a substantially hollow body extending therebetween. The first opening is positioned proximate to a balance weight retainer, the second opening is positioned proximate to the access cover, and the body is positioned in substantial alignment with an installation axis of the balance weight retainer.
1. A balance weight access assembly comprising:
an access cover;
a plenum defined adjacent to said access cover;
a cooling circuit coupled in flow communication with said plenum, said cooling circuit configured to channel cooling air to said plenum; and
an access tube comprising a first opening, a second opening, and a substantially hollow body extending therebetween, said first opening positioned proximate to a balance weight retainer, said second opening positioned proximate to said plenum, said body in substantial alignment with an installation axis of the balance weight retainer.
2. An assembly in accordance with claim 1 further comprising a plug configured to substantially block fluid flow through said tube.
3. An assembly in accordance with claim 1 wherein said balance weight retainer is coupled to a rotor of a rotatable machine.
4. An assembly in accordance with claim 1 wherein said balance weight retainer is coupled to a turbine rotor of a gas turbine engine.
5. An assembly in accordance with claim 1 wherein said tube is coupled to a baffle assembly centerbody of a gas turbine engine.
6. An assembly in accordance with claim 1 wherein an upstream end of said tube is coupled to a forward baffle of a baffle assembly centerbody of a gas turbine engine.
7. An assembly in accordance with claim 1 wherein a downstream end of said tube is coupled to a baffle assembly centerbody of a gas turbine engine.
8. A method for assembling a gas turbine engine, said method comprising:
providing a coverable aperture between a flow path of combustion gases through the gas turbine engine and an engine cooling circuit, wherein the aperture is positioned to receive cooling air channeled through the engine cooling circuit; and
coupling an access tribe to the gas turbine engine in substantial alignment between a balance weight retainer on a rotor of the gas turbine engine and the aperture.
9. A method in accordance with claim 8 wherein providing a coverable aperture comprises providing a cover configured to couple to a liner separating the flow path from the engine cooling circuit such that a flow of combustion gases through the aperture is substantially blocked.
10. A method in accordance with claim 8 wherein providing a coverable aperture comprises providing a cover configured to couple to a liner using removable fasteners.
11. A method in accordance with claim 8 wherein coupling an access tube to the gas turbine engine comprises coupling an upstream end of the access tube to a forward baffle of the gas turbine engine.
12. A method in accordance with claim 8 wherein coupling an access tube to the gas turbine engine comprises coupling a downstream end of the access tube to a baffle assembly centerbody of the gas turbine engine.
13. A method in accordance with claim 8 further comprising coupling a plug to the access tube such that a flow through the aperture is substantially blocked.
14. A gas turbine engine comprising:
a turbine; and
a balance weight access assembly coupled in a position adjacent said turbine, said balance weight access assembly comprising:
an access cover;
a plenum defined adjacent to said access cover;
a cooling circuit coupled in flow communication with said plenum, said cooling circuit configured to channel cooling air to said plenum; and
an access tube comprising a first opening, a second opening, and a substantially hollow body extending therebetween, said first opening positioned proximate to a balance weight retainer coupled to said turbine, said second opening positioned proximate to said plenum, said body in substantial alignment with an installation axis of the balance weight retainer.
15. A gas turbine engine in accordance with claim 14 further comprising a plug configured to substantially block fluid flow through said tube.
16. A gas turbine engine in accordance with claim 14 wherein said balance weight retainer is coupled to the turbine.
17. A gas turbine engine in accordance with claim 14 wherein said balance weight retainer is coupled to a third stage rotor rim of the turbine.
18. A gas turbine engine in accordance with claim 14 wherein said tube is coupled to a baffle assembly centerbody of the gas turbine engine.
19. A gas turbine engine in accordance with claim 14 wherein an upstream end of said tube is coupled to a forward baffle of a baffle assembly centerbody of the gas turbine engine.
20. A gas turbine engine in accordance with claim 14 wherein a downstream end of said tube is coupled to a baffle assembly centerbody of a gas turbine engine.