Assembly of two parts, one of which is made of composite material, the parts being assembled together by a mechanical anchor element

{
  "publication_number": "US10745109B2",
  "country": "US",
  "kind": "B2",
  "title": "Assembly of two parts, one of which is made of composite material, the parts being assembled together by a mechanical anchor element",
  "abstract": "An assembly of two parts, one of the parts being made of composite material with fiber reinforcement obtained from a fiber preform made by three-dimensional weaving and densified with a matrix, the assembly including a mechanical anchor element secured to one of the parts and inserted inside the other part.",
  "claims": [
    "1. An assembly of two parts, one of the parts being made of composite material with fiber reinforcement obtained from a fiber preform made by three-dimensional weaving and densified with a matrix, the assembly comprising a mechanical anchor element secured to, and extending from, one of the parts and inserted inside the other part, the mechanical anchor element extending from said one of the parts being inserted in a zone of non-interlinking of said other part provided during weaving of the fiber preform that is to make the fiber reinforcement of the composite material part, with the insertion taking place before a step of injecting a resin into said fiber preform, said fiber preform comprising layers of yarns that are interlinked, wherein the zone of non-interlinking of said other part is obtained by locally omitting interlinking between adjacent layers of yarns thereby forming two separate portions of the fiber preform, wherein said one of the parts, on which the anchor element is secured, is arranged on an external surface of the other part that includes the zone of non-interlinking.",
    "2. An assembly according to claim 1, wherein the composite material part is an airfoil of a turbojet blade and the other part is a metal strip for assembling on a leading edge of said airfoil.",
    "3. An assembly according to claim 2, wherein the mechanical anchor element comprises at least one metal rod that is secured to the metal strip and that extends into the inside of the airfoil in a direction that is transverse relative to the airfoil.",
    "4. An assembly according to claim 3, wherein the rod is secured to a flange of the metal strip that is positioned against a side face of the airfoil or is secured to a central portion of the metal strip interconnecting the flange.",
    "5. An assembly according to claim 2, wherein the mechanical anchor element comprises at least one crossbar that extends between two flanges of the metal strip and that passes through the airfoil in its thickness direction.",
    "6. An assembly according to claim 1, wherein the composite material part is a spar-forming structural core of a turboprop propeller blade, and the other part is a shell that is positioned around the propeller blade core, said shell being made of composite material.",
    "7. An assembly according to claim 6, wherein the mechanical anchor element comprises at least one lug secured to an inside face of the shell and inserted into the inside of the structural core of the propeller blade.",
    "8. An airfoil of a turbojet blade comprising an assembly according to claim 2.",
    "9. A turboprop propeller blade comprising an assembly according to claim 6.",
    "10. A turbine engine including at least one assembly according to claim 1."
  ],
  "description_excerpt": "The invention relates to the general field of assembling together two parts of a structure in which one of the parts is made of composite material with fiber reinforcement obtained from a fiber preform made by three-dimensional weaving and densified with a matrix.\n\nNon-limiting examples of applications of the invention include in particular assembling a metal strip on a leading edge of a turbojet blade made of composite material, and assembling a shell on a spar-forming structural core made of composite material for a turboprop propeller blade.\n\nIt is known to make a turbojet blade out of composite material by using fiber reinforcement obtained from a fiber preform made by three-dimensional weaving and densified with a matrix. Compared with other known techniques for fabricating a composite material blade, making a fiber preform by three-dimensional weaving presents numerous advantages, in particular such as that of not needing any recourse to inserts or fitting any other separate element. Reference made by made to Document EP 1 526 285, which describes a method of fabricating such a fan blade.\n\nFurthermore, it is known to fit a metal strip (or reinforcement) on the leading edge of such a composite material turbojet blade in order to protect the composite structure from abrasion/erosion and also in the event of an impact against a foreign body. This applies in particular for the fan blades of a turbojet, which are exposed to ingesting a bird, hail, ice, etc.",
  "cpc": [
    "B64C 11/26",
    "B23P 15/04",
    "B29B 11/16",
    "B29C 65/4835",
    "B29C 65/56",
    "B29C 65/64",
    "B29C 66/126",
    "B29C 66/21",
    "B29C 66/301",
    "B29C 66/71",
    "B29C 66/72141",
    "B29C 66/7394",
    "B29C 66/742",
    "B29C 70/68",
    "B29K 2063/00",
    "B29K 2079/08",
    "B29L 2031/082",
    "B29L 2031/087",
    "F01D 5/28",
    "F01D 5/282",
    "F01D 5/286",
    "F04D 29/023",
    "F04D 29/324",
    "F04D 29/388",
    "F05D 2230/23",
    "F05D 2240/303",
    "F05D 2300/603",
    "F16B 5/128",
    "Y02T 50/60",
    "Y02T 50/672",
    "Y02T 50/673"
  ],
  "ipc": [
    "B23P 15/04",
    "B29C 65/00",
    "B29C 65/48",
    "B29C 65/56",
    "B29C 65/64",
    "B29L 31/08",
    "B64C 11/26",
    "F01D 5/28",
    "F04D 29/02",
    "F04D 29/32",
    "F04D 29/38",
    "F16B 5/12"
  ],
  "assignees": [
    "Safran Aircraft Engines SAS"
  ],
  "inventors": [
    "Julien SCHNEIDER",
    "Johann FEUNTEUN",
    "Thierry Godon"
  ],
  "filing_date": "2015-10-19",
  "publication_date": "2020-08-18",
  "grant_date": "2020-08-18",
  "priority_date": "2014-10-23",
  "application_number": "US-201515520975-A",
  "family_id": "51987419",
  "cited_by_count": 1,
  "citations": [
    "US5112194A",
    "US6431837B1",
    "EP1526285A1",
    "EP1681440A2",
    "US20060216154A1",
    "US20120267039A1",
    "US20130017093A1",
    "FR2963055A1",
    "US20130270389A1",
    "WO2013021141A1",
    "US20160159460A1"
  ]
}