Systems and methods for designing threads of turbine engine connectors

{
  "publication_number": "US6959553B2",
  "country": "US",
  "kind": "B2",
  "title": "Systems and methods for designing threads of turbine engine connectors",
  "abstract": "A connector that receives a threaded apparatus and reduces stresses induced from the treaded apparatus into the connector is described. The connector includes a top side, a bottom side, and an opening that extends therethrough. The opening is defined by an inner surface that includes a threadform including a plurality of threads. The threads extend radially outward from the inner surface into the connector opening and include a first thread portion and a cutback that extends through a portion of the threadform. The cutback facilitates less stresses being induced into the first thread portion.",
  "claims": [
    "1. A gas turbine engine assembly comprising: a gas turbine engine comprising a longitudinal axis; and a thrust link having a longitudinal axis substantially aligned with respect to said engine longitudinal axis, said thrust link comprising at least a portion of an engine mount for said gas turbine engine and comprising a first connector, a second connector, and a span section extending therebetween, said first connector comprising a first side, a second side, and an opening extending therebetween and defined by an inner surface, said inner surface comprising a plurality of threads extending radially outward into said connector opening such that said threads are axially spaced substantially constant along said inner surface, said plurality of threads comprises a first thread portion positioned proximate said first side and initially engaging a threaded apparatus coupled to said first connector, said plurality of threads comprising a cutback, wherein said cutback extends through said first thread portion, said first connector coupled to said turbine engine, said cutback configured to facilitate reducing stresses induced into said plurality of threads.",
    "2. A gas turbine engine assembly in accordance with claim 1 wherein said thrust link connector opening has a center axis of symmetry extending from said connector first side to said connector second side, said cutback oblique with respect to said center axis of symmetry.",
    "3. A gas turbine engine assembly in accordance with claim 2 wherein each said thread comprises a crest and a root, said cutback extending through said first thread portion crest.",
    "4. A gas turbine engine assembly in accordance with claim 3 wherein said thrust link connector first thread portion is positioned adjacent at least one of said connector first side and said connector second side.",
    "5. A gas turbine engine assembly in accordance with claim 3 wherein said thrust link connector cutback comprises a first end and a second end, said cutback first end extending through said thrust link connector first thread portion, said cutback second end between said connector first thread portion and said thrust link connector second side.",
    "6. A gas turbine engine assembly in accordance with claim 5 wherein said thrust link connector cutback first end is positioned a first distance from said thrust link connector opening center axis of symmetry, said thrust link connector cutback second end is positioned a second distance from said thrust link connector opening center axis of symmetry.",
    "7. A gas turbine engine assembly in accordance with claim 6 wherein said thrust link connector cutback first distance is longer than said thrust link second distance.",
    "8. A gas turbine engine assembly in accordance with claim 1 wherein said thrust link connector cutback is further configured to reduce a stiffness factor of at least a portion of said plurality of threads."
  ],
  "description_excerpt": "This application relates generally to connectors and, more particularly, to connectors sized to receive a threaded apparatus. Aircraft engines typically include a plurality of threaded connections that are torqued during assembly. For example, an aircraft engine may be mounted to an aircraft at various locations, such as on a wing, to a fuselage, or to a tail. The engine is typically mounted at a forward and an aft end with a mounting system that includes a plurality of thrust links including connectors at each end. The connectors include openings extending therethrough that are defined by substantially planar inner surfaces including a plurality of threads. The thrust link connectors are exposed to potential vibrational stresses that are induced during engine operation. To minimize the effect of exposure to such vibrational stresses, threaded components are torqued. When threaded components are loaded by torque or an external load, stresses are induced within the connectors. A highest stress area typically occurs in a first thread. More specifically, a highest stress is induced into a first thread root fillet that is defined between the first thread and a subsequent thread. Continued exposure to such stresses, may weaken the first thread and reduce a low cycle fatigue capability of the threaded connection. Prolonged reduced low cycle fatigue may shorten a useful life of the threaded connection.\n\nTo facilitate improving the low cycle fatigue capability of threaded connections, the threads of at least some known threaded components are rolled to provide a surface that is pre-stressed in compression.",
  "cpc": [
    "F01D 25/28",
    "F16B 33/02"
  ],
  "ipc": [
    "F01D 25/28",
    "F16B 33/02"
  ],
  "assignees": [
    "GEN ELECTRIC"
  ],
  "inventors": [
    "ANDERSON WILLIAM CARL"
  ],
  "filing_date": "2003-10-13",
  "publication_date": "2005-11-01",
  "grant_date": "2005-11-01",
  "priority_date": "2001-03-30",
  "application_number": "US-68424403-A",
  "family_id": "25235106",
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}