Compressor rotor destacking apparatus and method

{
  "publication_number": "US12352180B2",
  "country": "US",
  "kind": "B2",
  "title": "Compressor rotor destacking apparatus and method",
  "abstract": "A disassembly tool for a rotor assembly of a gas turbine engine includes a plurality of legs configured for installation into a rotor bore of a rotor of the rotor assembly. Each leg includes one or more keys extending radially inwardly toward a center of the rotor bore. A puck is configured for installation into the rotor bore radially inboard of the plurality of legs. The puck includes a groove receptive of the one or more keys to retain the puck to the plurality of legs.",
  "claims": [
    "1. A disassembly tool for a rotor assembly of a gas turbine engine, comprising: a plurality of legs configured for installation into a rotor bore of a rotor of the rotor assembly, each leg of the plurality of legs including one or more keys configured to extend radially inwardly toward a center of the rotor bore; and a puck configured for installation into the rotor bore radially inboard of the plurality of legs, the puck including a plurality of puck arms extending radially outwardly from a puck body, each puck arm including a groove receptive of the one or more keys of a corresponding leg of the plurality of legs to retain the puck to the plurality of legs.",
    "2. The disassembly tool of claim 1, wherein the one or more keys are configured to engage the groove via rotation of the puck in the rotor bore.",
    "3. The disassembly tool of claim 1, wherein each leg of the plurality of legs includes: a leg body having a radial inner surface from which the one or more keys extend; a first axial arm extending radially outwardly from the leg body and configured to be positioned at a first axial side of the rotor; and a second axial arm extending radially outwardly from the leg body and configured to be positioned at a second axial side of the rotor opposite the first axial side, wherein the first axial arm and the second axial arm are configured to retain each leg of the plurality of legs at the rotor.",
    "4. The disassembly tool of claim 3, wherein the leg body further includes an axially facing surface extending radially inwardly from the leg body.",
    "5. The disassembly tool of claim 1, wherein the one or more keys are one or more radially-extending pins or one or more circumferentially elongated ribs.",
    "6. The disassembly tool of claim 1, wherein the puck includes a puck axial surface configured to react a force applied via a disassembly force application device.",
    "7. A disassembly system for disassembly of a first rotor of a rotor assembly of a gas turbine engine from an axially adjacent second rotor of the rotor assembly, comprising: a disassembly tool including: a plurality of legs configured for installation through a first rotor bore of the first rotor and further configured to be secured at a second rotor bore of the second rotor, each leg of the plurality of legs including one or more keys configured to extend radially inwardly toward a center of the second rotor bore; and a puck configured for installation into the second rotor bore radially inboard of the plurality of legs, the puck including a plurality of puck arms extending radially outwardly from a puck body, each puck arm including a groove receptive of the one or more keys of a corresponding leg of the plurality of legs to retain the puck to the plurality of legs; and a disassembly force application device configured to be operably connected to the first rotor, and further configured to be operably connected to the second rotor at the puck, the disassembly force application device configured to apply an axial force to remove the first rotor from the second rotor.",
    "8. The disassembly system of claim 7, wherein the disassembly force application device is a pneumatic ram.",
    "9. The disassembly system of claim 7, wherein the one or more keys are configured to engage the groove via rotation of the puck in the rotor bore.",
    "10. The disassembly system of claim 7, wherein each leg of the plurality of legs includes: a leg body having a radial inner surface from which the one or more keys extend; a first axial arm extending radially outwardly from the leg body and configured to be positioned at a first axial side of the rotor; and a second axial arm extending radially outwardly from the leg body and configured to be positioned at a second axial side of the rotor opposite the first axial side, wherein the first axial arm and the second axial arm are configured to retain each leg of the plurality of legs at the rotor.",
    "11. The disassembly system of claim 10, wherein the leg body further includes an axially facing surface extending radially inwardly from the leg body.",
    "12. The disassembly system of claim 7, wherein the one or more keys are one or more radially-extending pins or one or more circumferentially elongated ribs.",
    "13. The disassembly system of claim 7, wherein the puck includes a puck axial surface configured to react a force applied via the disassembly force application device."
  ],
  "description_excerpt": "Exemplary embodiments of the present disclosure pertain to the art of gas turbine engines, and in particular to disassembly of compressor rotor of a gas turbine engine. During service or repair of gas turbine engines, it is often necessary to disassemble the rotor assembly by unstacking successive rotor stages. The rotor stages are connected to each other via an interference fit at a rotor flange, also known as a snap connection, and application of a high degree of force is necessary to separate the rotor stages. A pneumatic ram is typically utilized to apply a pulling force on one of the stages, while tooling installed to an adjacent stage is used to react the pulling force applied by the pneumatic ram device. The currently utilized tooling can slip or other wise move during operation and may consequently damage the rotor stage. The rotor stages, which are often integral-bladed rotors (IBRs), are costly components and damage resulting from use of the tooling during disassembly may result is the need for extensive repair and/or replacement of the rotor stage. The art would therefore appreciate improved tooling for disassembly of the rotor stages from each other,\n\nIn one exemplary embodiment, a disassembly tool for a rotor assembly of a gas turbine engine includes a plurality of legs configured for installation into a rotor bore of a rotor of the rotor assembly. Each leg includes one or more keys extending radially inwardly toward a center of the rotor bore. A puck is configured for installation into the rotor bore radially inboard of the plurality of legs.",
  "cpc": [
    "F01D 25/285",
    "B23P 19/025",
    "B23P 19/027",
    "B25B 27/02",
    "F05D 2230/70",
    "F05D 2240/24",
    "F05D 2270/65"
  ],
  "ipc": [
    "B23P 19/02",
    "B23P 19/027",
    "F01D 25/28"
  ],
  "assignees": [
    "RTX CORP"
  ],
  "inventors": [
    "FISCHBACH MITCHELL J",
    "BARNES JACOB"
  ],
  "filing_date": "2023-12-13",
  "publication_date": "2025-07-08",
  "grant_date": "2025-07-08",
  "priority_date": "2023-12-13",
  "application_number": "US-202318538423-A",
  "family_id": "93924117",
  "citations": [
    "CN110340848A",
    "CN113263476A",
    "CN114571401A",
    "CN115805556A",
    "KR101869650B1",
    "US10968779B2",
    "US2014000084A1",
    "US2016069259A1",
    "US2016146103A1",
    "US2022048647A1",
    "US2023001524A1",
    "US5473883A",
    "US8776347B2",
    "US9802302B1"
  ]
}