Methods and apparatus for isolating gas turbine engine bearings

{
  "publication_number": "US6582187B1",
  "country": "US",
  "kind": "B1",
  "title": "Methods and apparatus for isolating gas turbine engine bearings",
  "abstract": "A gas turbine engine including a rotor shaft includes a bearing isolation system including an isolation shaft and a pair of pilots. The pilots are disposed between the isolation and rotor shafts and connect the isolation shaft to the rotor shaft to form a gap between the isolation and rotor shafts. The pilots are positioned axially along the rotor shaft and permit the isolation shaft to move axially with respect to the rotor shaft. Each pilot includes a plurality of openings to permit cooling air to flow within the gap defined between the isolation shaft and the rotor shaft.",
  "claims": [
    "1. A method of reducing thermal conduction between a turbine engine rotor shaft and a bearing assembly using a bearing isolation system, the bearing isolation system including a shaft disposed a distance from the rotor shaft and between the turbine rotor shaft and the bearing, the bearing isolation system shaft including a plurality of pilots disposed between the turbine rotor shaft and the bearing assembly, said method comprising the steps of: operating the turbine engine; and directing cooling air into a gap defined between the bearing isolation system shaft and the turbine rotor shaft.",
    "2. A method in accordance with claim 1 wherein the plurality of pilots include a plurality of openings, said step of directing cooling air further comprising the step of directing cooling air through the plurality of pilot openings into the gap disposed between the turbine rotor shaft and the bearing isolation system shaft.",
    "3. A method in accordance with claim 2 wherein the step of operating the turbine engine further comprises the step of permitting the bearing isolation system shaft to move axially with respect to the turbine rotor shaft during engine operation.",
    "4. A method in accordance with claim 3 wherein said step of directing cooling air further comprises the step of directing cooling air through a plurality of pilot openings disposed in a pilot disposed downstream of the bearing and through a plurality of pilot openings disposed in a pilot disposed upstream of the bearing.",
    "5. A bearing isolation system for a gas turbine engine including a main rotor shaft including at least one rotor, and a bearing rotatably coupled to the main rotor shaft, said bearing isolation system comprising a shaft disposed between the main rotor shaft and the bearing, said bearing isolation system shaft connected to the bearing and configured to isolate the bearing from the main rotor shaft, said main rotor shaft and said bearing isolation system shaft defining a gap coupled in flow communication with an air source for receiving cooling air therethrough for cooling said bearing.",
    "6. A bearing isolation system in accordance with claim 5 further comprising a plurality of pilots disposed between said bearing isolation system shaft and the main rotor shaft.",
    "7. A bearing isolation system in accordance with claim 6 wherein said plurality of pilots create a thermal barrier to reduce conduction of heat to the bearing from the main rotor shaft.",
    "8. A bearing isolation system in accordance with claim 7 wherein the bearing is interference fit on said bearing isolation system shaft.",
    "9. A bearing isolation system in accordance with claim 8 wherein at least one of said plurality of pilots disposed a distance upstream from the bearing, at least one of said plurality of pilots disposed a distance downstream from the bearing.",
    "10. A bearing isolation system in accordance with claim 9 wherein each of said plurality of pilots comprises a plurality of openings.",
    "11. A bearing isolation system in accordance with claim 10 wherein said bearing isolation system shaft is disposed a distance from the main rotor shaft such that said bearing isolation system and the main rotor shaft define a gap, the plurality of pilot openings configured to permit cooling air to flow into said gap between said bearing isolation system shaft and the main rotor shaft.",
    "12. A bearing isolation system in accordance with claim 11 wherein said bearing isolation system shaft is configured to move axially with respect to the main rotor shaft.",
    "13. A gas turbine engine rotor assembly comprising: a first rotor comprising a rotor shaft; at least one bearing rototably coupled to said rotor shaft; and a bearing isolation system configured to isolate said bearing from said rotor shaft, said bearing isolation system comprising a bearing isolation system shaft disposed between said rotor shaft and said bearing, said bearing isolation system shaft coupled to an air source for receiving cooling air to facilitate reducing conduction of heat to said bearing.",
    "14. A rotor assembly in accordance with claim 13 wherein said bearing isolation system shaft is disposed a distance from said rotor shaft.",
    "15. A rotor assembly in accordance with claim 14 wherein said bearing isolation system further comprises a plurality of pilots disposed between said bearing isolation system shaft and said rotor shaft.",
    "16. A rotor assembly in accordance with claim 15 wherein said bearing isolation system plurality of pilots create a thermal barrier to reduce conduction of heat to said bearing from said rotor shaft.",
    "17. A rotor assembly in accordance with claim 16 wherein at least one of said plurality of pilots disposed a distance upstream from said bearing and at least one of said plurality of pilots disposed a distance downstream from said bearing.",
    "18. A rotor assembly in accordance with claim 17 wherein said plurality of pilots comprise a plurality of openings configured to permit cooling air to flow between said bearing isolation system shaft and said rotor shaft.",
    "19. A rotor assembly in accordance with claim 18 wherein said plurality of pilots configured to attenuate thermal and mechanical growths of said first rotor such that thermal and mechanical growths of said bearing assembly are reduced.",
    "20. A rotor assembly in accordance with claim 19 wherein said bearing isolation system shaft configured to move axially with respect to said rotor shaft, said bearing isolation system configured with said first rotor to reduce a radial spring rate of said rotor shaft."
  ],
  "description_excerpt": "This application relates generally to gas turbine engines and, more particularly, to gas turbine engine bearing assemblies.\n\nA gas turbine engine typically includes a multi-stage axial compressor, a combustor, and a turbine. Airflow entering the compressor is compressed and directed to the combustor where it is mixed with fuel and ignited, producing hot combustion gases used to drive the turbine. The turbine is coupled to the compressor with a rotor shaft supported by a plurality of assemblies. As a result of hot combustion gases, the turbine, and rotor shaft are subjected to thermal stresses. Additionally, the bearing assemblies supporting the rotor shaft are, subjected to thermal conduction from contact with the rotor shaft.\n\nAs turbine engines have evolved, higher stage loading turbo-machinery, including larger bearing assemblies and rotor shafts, have been included within the engines to provide increased pressure ratio cycles for the turbine engines. Higher pressure ratios increase cycle temperatures and air temperatures within the engine. Specifically, higher stage loading causes an operating speed of the turbines to increase, resulting in temperature increases in the rotor and bearing assemblies.\n\nTo minimize the effects of increased pressure ratio cycles, known bearing assemblies include isolation systems that attempt to isolate the bearing assemblies from the rotor shaft. Isolation systems often include shaft oil cooling systems, increased bearing compliance or trilobing, reduced inner race to shaft fits, and decreased bearing support stiffness'.",
  "cpc": [
    "F01D 25/162",
    "F01D 25/125",
    "F02C 7/06",
    "F05B 2230/606",
    "F05D 2230/642",
    "Y02T 50/60"
  ],
  "ipc": [
    "F01D 25/12",
    "F01D 25/16",
    "F01D 5/08",
    "F02C 7/06",
    "F02C 7/18",
    "F16C 37/00"
  ],
  "assignees": [
    "General Electric Co"
  ],
  "inventors": [
    "Robert Edwin Shockley",
    "Gary Charles Liotta"
  ],
  "filing_date": "2000-03-10",
  "publication_date": "2003-06-24",
  "grant_date": "2003-06-24",
  "priority_date": "2000-03-10",
  "application_number": "US-52256200-A",
  "family_id": "24081360",
  "cited_by_count": 8,
  "citations": [
    "US2469732A",
    "US2620123A",
    "US3951573A",
    "US2788951A",
    "US3133693A",
    "US3393024A",
    "US3531167A",
    "US3673802A",
    "US3734649A",
    "US3764236A",
    "US3903690A",
    "US3909085A",
    "US3925979A",
    "US4222705A",
    "US4500143A",
    "US4709545A",
    "US4653267A",
    "US5046920A",
    "US5160251A",
    "US5232335A",
    "US5611661A",
    "US5438756A",
    "US5555721A",
    "US5619850A",
    "US6053701A",
    "US6048101A"
  ]
}