# US 7,465,146 B2 · Methods and systems for turbine rotor balancing > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 7,465,146 B2 - Document ID: US7465146B2 - Status: Granted - Kind: B2 - Application number: 11/294,863 - Filed: 2005-12-05 - Published: 2007-06-07 - Granted: 2008-12-16 - Earliest claimed: 2005-12-05 - Assignees: General Electric Company - Inventors: Dale Michael Kennedy; Wayne Garcia Edmondson, Sr. - Web page: https://patentgrep.com/patent/US7465146B2 ## CPC - F01D 5/027: {Arrangements for balancing (for balancing rotating bodies in general F16F15/32; for compensating imbalance G01M1/36)} - F01D 25/285: {Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures} - F04D 29/321: {for axial flow compressors} - F04D 29/662: {Balancing of rotors (compensating imbalance G01M1/36)} - G01M 1/32: by adding material to the body to be tested, e.g. by correcting-weights - F05D 2230/60: Assembly methods - Y10T 74/2109: Balancing for drum, e.g., washing machine or arm-type structure, etc., centrifuge, etc. - Y10T 74/2117: Power generating-type flywheel - Y10T 428/13: Hollow or container type article [e.g., tube, vase, etc.] - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - G01M: TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) An assembly in accordance with claim 1 further comprising a plug configured to substantially block fluid flow through said tube. ### Claim 3 (depends on 1) An assembly in accordance with claim 1 wherein said balance weight retainer is coupled to a rotor of a rotatable machine. ### Claim 4 (depends on 1) An assembly in accordance with claim 1 wherein said balance weight retainer is coupled to a turbine rotor of a gas turbine engine. ### Claim 5 (depends on 1) An assembly in accordance with claim 1 wherein said tube is coupled to a baffle assembly centerbody of a gas turbine engine. ### Claim 6 (depends on 1) 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. ### Claim 7 (depends on 1) 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. ### Claim 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. ### Claim 9 (depends on 8) 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. ### Claim 10 (depends on 8) 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. ### Claim 11 (depends on 8) 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. ### Claim 12 (depends on 8) 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. ### Claim 13 (depends on 8) 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. ### Claim 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. ### Claim 15 (depends on 14) A gas turbine engine in accordance with claim 14 further comprising a plug configured to substantially block fluid flow through said tube. ### Claim 16 (depends on 14) A gas turbine engine in accordance with claim 14 wherein said balance weight retainer is coupled to the turbine. ### Claim 17 (depends on 14) 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. ### Claim 18 (depends on 14) A gas turbine engine in accordance with claim 14 wherein said tube is coupled to a baffle assembly centerbody of the gas turbine engine. ### Claim 19 (depends on 14) 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. ### Claim 20 (depends on 14) 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.