# US 8,465,259 B2 · Gas turbine spindle bolt structure with reduced fretting motion > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,465,259 B2 - Document ID: US8465259B2 - Status: Granted - Kind: B2 - Application number: 12/769,928 - Filed: 2010-04-29 - Published: 2011-11-03 - Granted: 2013-06-18 - Earliest claimed: 2010-04-29 - Assignees: Siemens Energy, Inc. - Applicants: Kevin M. Light; Manish S. Gurao; David M. Shaefer - Inventors: Kevin M. Light; Manish S. Gurao; David M. Shaefer - Web page: https://patentgrep.com/patent/US8465259B2 ## CPC - F04D 29/644: {especially adapted for elastic fluid pumps} - F01D 5/066: {Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps} - F04D 29/054: Arrangements for joining or assembling shafts - F05D 2260/311: of the frangible or shear type - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A spindle bolt structure is provided in a gas turbine engine. The gas turbine engine includes a rotor including a plurality of turbine disks for supporting rows of blades, a torque tube located on a compressor side of the turbine disks, and a seal disk located between the torque tube and a first stage turbine disk. The spindle bolt structure includes a plurality of spindle bolts extending through the turbine disks and disposed offset from a rotational axis of the turbine disks. The spindle bolts include a first terminal end located adjacent to the compressor side of the turbine disks, and a sleeve member is provided extending over a portion of the first terminal end of each spindle bolt and embedded within a compressor side of the seal disk for effecting a reduction in fretting movement of the spindle bolt relative to the seal disk. ## Claims ### Claim 1 In a gas turbine engine, a rotor including a plurality of turbine disks for supporting rows of blades, a torque tube located on a compressor side of the turbine disks, and a seal disk located between the torque tube and a first stage turbine disk, a spindle bolt structure comprising: a spindle bolt extending through the turbine disks and disposed offset from a rotational axis of the turbine disks; the spindle bolt including a first terminal end located adjacent to the compressor side of the turbine disks; and a sleeve member extending over a portion of the first terminal end of the spindle bolt and embedded within a compressor side of the seal disk for effecting a reduction in fretting movement of the spindle bolt relative to the seal disk. ### Claim 2 (depends on 1) The spindle bolt structure of claim 1, wherein the sleeve member includes an engagement end engaged on a shoulder defined inside the seal disk. ### Claim 3 (depends on 2) The spindle bolt structure of claim 2, wherein the seal disk has opposing axial faces comprising an upstream axial face adjacent to the torque tube and a downstream axial face adjacent to the first turbine disk and a seal disk thickness defined between the axial faces, and the seal disk shoulder is located a distance from the downstream axial face less than one-half the distance between the upstream and downstream axial faces. ### Claim 4 (depends on 1) The spindle bolt structure of claim 1, wherein the sleeve is rigidly affixed at a predetermined axial location on the first terminal end of the spindle bolt. ### Claim 5 (depends on 4) The spindle bolt structure of claim 4, wherein the first terminal end of the spindle bolt comprises a threaded end, and the first terminal end is threadably engaged into the sleeve. ### Claim 6 (depends on 5) The spindle bolt structure of claim 5, wherein the sleeve comprises a generally cylindrical exterior, and including an anti-rotation key between the seal disk and the sleeve. ### Claim 7 (depends on 1) The spindle bolt structure of claim 1, wherein the spindle bolt includes a second terminal end located adjacent an exhaust side of the turbine disks opposite from the compressor side of the turbine disks. ### Claim 8 (depends on 7) The spindle bolt structure of claim 7, wherein the plurality of turbine disks define a rotor and the second terminal end of the spindle bolt is located at a last stage turbine disk. ### Claim 9 (depends on 1) The spindle bolt structure of claim 1, further including a shear bolt offset from the rotational axis and extending through the seal disk and the torque tube for effecting a rigid connection between the seal disk and the torque tube. ### Claim 10 In a gas turbine engine a rotor including a plurality of turbine disks for supporting rows of blades, a torque tube located on a compressor side of the turbine disks, and a seal disk located between the torque tube and a first stage turbine disk, a spindle bolt structure comprising: spindle bolts extending through the turbine disks, the spindle bolts being disposed circumferentially around and offset from a rotational axis of the turbine disks; the spindle bolts including a first terminal end located adjacent to the compressor side of the turbine disks; a plurality of holes in the seal disk aligned with corresponding holes in the turbine disks for receiving the spindle bolts, each hole in the seal disk comprising a stepped portion defining a shoulder between opposing axial faces of the seal disk; a sleeve member extending over a portion of the first terminal end of each of the spindle bolts and embedded within a compressor side of the seal disk; and each of the sleeve members including an engagement end engaged on a shoulder within a respective hole in the seal disk for effecting a reduction in fretting movement of the spindle bolt relative to the seal disk. ### Claim 11 (depends on 10) The spindle bolt structure of claim 10, wherein the opposing axial faces of the seal disk comprise an upstream axial face adjacent to the torque tube and a downstream axial face adjacent to the first turbine disk and a seal disk thickness defined between the axial faces, and the seal disk shoulders within the holes of the seal disk are located a distance from the downstream axial face less than one-half the distance between the upstream and downstream axial faces. ### Claim 12 (depends on 10) The spindle bolt structure of claim 10, wherein the sleeves are rigidly affixed at a predetermined axial location on the first terminal end of the spindle bolts. ### Claim 13 (depends on 12) The spindle bolt structure of claim 12, wherein the first terminal end of the spindle bolts comprises a threaded end, and the first terminal ends are threadably engaged into the sleeves. ### Claim 14 (depends on 13) The spindle bolt structure of claim 13, wherein each sleeve comprises a generally cylindrical exterior, and including an anti-rotation key between each sleeve and a respective hole in the seal disk. ### Claim 15 (depends on 10) The spindle bolt structure of claim 10, wherein the spindle bolts include a second terminal end located adjacent an exhaust side of the turbine disks opposite from the compressor side of the turbine disks. ### Claim 16 (depends on 15) The spindle bolt structure of claim 15, wherein the plurality of turbine disks define a rotor and the second terminal end of the spindle bolts is located at a last stage turbine disk. ### Claim 17 (depends on 10) The spindle bolt structure of claim 10, further including a plurality of shear bolts located circumferentially around and offset from the rotational axis and extending through the seal disk and the torque tube for effecting a rigid connection between the seal disk and the torque tube.