Prestressed combustor liner for gas turbine engine

{
  "publication_number": "US4422300A",
  "country": "US",
  "kind": "A",
  "title": "Prestressed combustor liner for gas turbine engine",
  "abstract": "The walls of the liner of a gas turbine combustor are segmented and disposed axially and circumferentially to define a combustion chamber. The liner is formed by radially spaced walls preferably fabricated from a ceramic or other high temperature brittle material. The wall adjacent the hot combustion products is prestressed at room temperature and the juxtaposed wall is cooperatively shaped to define a supporting frame for the prestressed wall so as to minimize the overall stresses occasioned in the hostile environment to which the prestressed wall is subjected.",
  "claims": [
    "1. A combustor having a liner formed from a plurality of segments supported on a frame in an axial and circumferential direction defining an annularly shaped combustion chamber, each frame being a relatively open ended box-like member having radially extending side walls complimenting the shape of its cooperating segment so that the side edge of each segment is contiguous with the top surface of said side walls, means for affixing said segments to the frame and for supporting said segments so that each are prestressed to bear against the top surface of said side walls, whereby said segment distorts when said combustor is operating at its normal temperature level and is in a relatively free stress condition, and means for cooling said segments to its operating temperature.",
    "2. A combustor as in claim 1 wherein said cooling means includes a plurality of openings in the bottom wall of said box-like member for leading cooling air to impinge on the underside of each of said segments and opening in said segment for discharging said cooling air into said combustor.",
    "3. A combustor as in claim 2 wherein said openings in said segment are oriented such that the flow discharging therein is substantially in the same direction as the flow of gases in said combustor."
  ],
  "cpc": [
    "F23R 3/007",
    "F05B 2260/201",
    "F05B 2260/202",
    "F23R 3/002",
    "Y02T 50/60"
  ],
  "assignees": [
    "UNITED TECHNOLOGIES CORP"
  ],
  "filing_date": "1981-12-14",
  "publication_date": "1983-12-27",
  "grant_date": "1983-12-27",
  "priority_date": "1981-12-14",
  "application_number": "US-33075981-A",
  "family_id": "23291201",
  "citations": [
    "DE1211441B",
    "SU200964A1",
    "US2544538A",
    "US2919549A",
    "US3552178A",
    "US3918255A",
    "US3954389A",
    "US3956886A",
    "US4030875A",
    "US4220624A"
  ]
}