{
  "$type": "site.standard.document",
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  "description": "A method for forming a coolant system for a rocket engine combustion chamber is provided. The method comprises the steps of providing a plurality of tubes 22 formed and shaped into the profile of a nozzle with each of the tubes having a constantly expanding cross section in an upper chamber area…",
  "path": "/patents/1081750",
  "publishedAt": "2004-12-08T00:00:00.000Z",
  "site": "at://did:plc:oql6ds5vnff4ugar6rruliwd/site.standard.publication/3mn3ohu7oxx5w",
  "tags": [
    "F02K9/64",
    "UNITED TECHNOLOGIES CORP [US]"
  ],
  "textContent": "A method for forming a coolant system for a rocket engine combustion chamber is provided. The method comprises the steps of providing a plurality of tubes 22 formed and shaped into the profile of a nozzle with each of the tubes having a constantly expanding cross section in an upper chamber area, providing an inlet manifold 32 and an exit manifold 30 with a plurality of holes 29 for receiving an end of each tube 22, inserting a brazing preform 31 into each hole 29, inserting a first end of each tube 22 into the inlet manifold 32 and a second end of each tube 22 into the outlet manifold 30 so that the first end is surrounded by a first brazing preform 31 and the second end is surrounded by a second brazing preform 31, and brazing the inlet and outlet manifolds 32,30 to the tubes 22. The brazing step forms a series of brazed joints between the tubes and the manifolds. The method further includes the steps of forming a layer of coating material 34 on exposed portions of the tubes 22 and forming a single piece jacket construction 36 around the tubes 22.",
  "title": "Rocket engine tubular combustion chamber with single piece jacket"
}