Heat shield assembly for use with an aircraft engine

{
  "publication_number": "US11781482B2",
  "country": "US",
  "kind": "B2",
  "title": "Heat shield assembly for use with an aircraft engine",
  "abstract": "A heat shield assembly for use with an aircraft engine. The heat shield assembly includes a structural member, a heat shield panel adapted for exposure to aircraft engine exhaust, an index joint coupling the heat shield panel to the structural member in a fixed positional location, and a plurality of slip joints coupling the heat shield panel to the structural member. Each slip joint includes at least one wear buffer coupled to the heat shield panel, and a slip fastener insertable through a slip joint hole in the heat shield panel with a clearance fit. A gap defined by the clearance fit is sized to provide a tolerance for expansion and contraction of the heat shield panel relative to the fixed positional location, and the at least one wear buffer is engageable by the slip fastener during expansion and contraction of the heat shield panel.",
  "claims": [
    "1. A heat shield assembly for use with an aircraft engine, the heat shield assembly comprising: a structural member; a heat shield panel adapted for exposure to aircraft engine exhaust; an index joint coupling the heat shield panel to the structural member in a fixed positional location; and a plurality of slip joints coupling the heat shield panel to the structural member, each slip joint comprising: at least one wear buffer coupled to the heat shield panel; and a slip fastener insertable through a slip joint hole in the heat shield panel with a clearance fit, wherein a gap defined by the clearance fit is sized to provide a tolerance for expansion and contraction of the heat shield panel relative to the fixed positional location, and wherein the at least one wear buffer is engageable by the slip fastener during expansion and contraction of the heat shield panel.",
    "2. The heat shield assembly in accordance with claim 1, wherein the index joint is centrally located on the heat shield panel.",
    "3. The heat shield assembly in accordance with claim 1, wherein the at least one wear buffer comprises a wear bushing coupled within the slip joint hole.",
    "4. The heat shield assembly in accordance with claim 3 further comprising a wear washer between the structural member and the wear bushing.",
    "5. The heat shield assembly in accordance with claim 4, wherein the slip fastener is coupled to the at least one wear buffer with a friction fit to enable the expansion and contraction of the heat shield panel.",
    "6. The heat shield assembly in accordance with claim 1, wherein the heat shield panel is formed from titanium.",
    "7. A heat shield assembly for use with an aircraft engine, the heat shield assembly comprising: a structural member; a heat shield panel adapted for exposure to aircraft engine exhaust; and a plurality of slip joints coupling the heat shield panel to the structural member, each slip joint comprising: at least one wear buffer coupled to the heat shield panel; and a slip fastener insertable through a slip joint hole in the heat shield panel with a clearance fit, wherein a gap defined by the clearance fit is sized to provide a tolerance for thermal movement of the heat shield panel relative to the structural member, and wherein the at least one wear buffer is engageable by the slip fastener during thermal movement of the heat shield panel.",
    "8. The heat shield assembly in accordance with claim 7 further comprising an index joint coupling the heat shield panel to the structural member in a fixed positional location, wherein the thermal movement is defined by expansion and contraction of the heat shield panel relative to the fixed positional location.",
    "9. The heat shield assembly in accordance with claim 8, wherein the index joint is centrally located on the heat shield panel.",
    "10. The heat shield assembly in accordance with claim 7, wherein the at least one wear buffer comprises a wear bushing coupled within the slip joint hole.",
    "11. The heat shield assembly in accordance with claim 10 further comprising a wear washer between the structural member and the wear bushing.",
    "12. The heat shield assembly in accordance with claim 7, wherein the slip fastener is coupled to the at least one wear buffer with a friction fit to enable the thermal movement of the heat shield panel.",
    "13. The heat shield assembly in accordance with claim 7, wherein the heat shield panel is formed from titanium.",
    "14. An aircraft comprising: an engine configured to discharge exhaust; a heat shield panel positioned for exposure to aircraft engine exhaust; and a plurality of slip joints coupling the heat shield panel onto the aircraft, wherein each slip joint comprises: at least one wear buffer coupled to the heat shield panel; and a slip fastener insertable through a slip joint hole in the heat shield panel with a clearance fit, wherein a gap defined by the clearance fit is sized to provide a tolerance for thermal movement of the heat shield panel relative to the slip fastener, and wherein the at least one wear buffer is engageable by the slip fastener during thermal movement of the heat shield panel.",
    "15. The aircraft in accordance with claim 14 further comprising a wing and a pylon extending from the wing, wherein the heat shield panel defines a skin panel of an aft fairing section of the pylon.",
    "16. The aircraft in accordance with claim 15 further comprising a structural member extending from the wing, wherein the structural member and the heat shield panel are coupled together with the slip fastener.",
    "17. The aircraft in accordance with claim 16, wherein the structural member is one of a frame member extending from the wing, or a side skin panel of the aft fairing section extending from the heat shield panel.",
    "18. The aircraft in accordance with claim 14 further comprising an index joint coupling the heat shield panel onto the aircraft in a fixed positional location, wherein the thermal movement is defined by expansion and contraction of the heat shield panel relative to the fixed positional location.",
    "19. The aircraft in accordance with claim 18, wherein the index joint is centrally located on the heat shield panel.",
    "20. The aircraft in accordance with claim 14, wherein the slip fastener is coupled to the at least one wear buffer with a friction fit to enable the thermal movement of the heat shield panel."
  ],
  "description_excerpt": "The field relates generally to heat shields and, more specifically, to heat shields for aircraft engines that enable thermal expansion and contraction.\n\nAircraft engines are typically supported on or coupled to an aircraft structure, such as a wing, with pylons. At least some known pylons include a support structure that supports the engine, and an aerodynamic fairing extending from the support structure. Some fairings are located aft of the engine such that a lower skin panel of the fairing may be exposed to exhaust gas discharged from the engine during operation thereof. Exposure to the exhaust gas use may cause the lower skin panel to undergo thermal expansion and contraction. Existing skin panels are generally continuously fastened to the support structure and to other skin panels with rivets. Temperature gradients may be formed across the fairing as the hotter lower skin panel is restrained by comparatively cooler side skin panels of the fairing. Thus, thermal cycling from exposure to the exhaust gas and subsequent cooling can repeatedly cause high stress to the fairing.\n\nThis section is intended to introduce the reader to various aspects of art that may be related to various aspects of the disclosure, which are described and/or claimed below. This discussion is believed to be helpful in providing the reader with background information to facilitate a better understanding of the various aspects of the present disclosure. Accordingly, it should be understood that these statements are to be read in this light, and not as admissions of prior art.",
  "cpc": [
    "F02C 7/20",
    "B64D 27/18",
    "B64D 27/402",
    "B64D 29/02",
    "B64D 29/06",
    "B64D 33/04",
    "F02C 7/24",
    "F05D 2220/323",
    "F05D 2260/231",
    "F16B 43/002",
    "F16B 5/0241"
  ],
  "ipc": [
    "B64D 27/18",
    "B64D 27/40",
    "B64D 29/02",
    "B64D 33/04",
    "F02C 7/20",
    "F02C 7/24"
  ],
  "assignees": [
    "Boeing Co"
  ],
  "inventors": [
    "John F. Summers"
  ],
  "filing_date": "2021-09-03",
  "publication_date": "2023-10-10",
  "grant_date": "2023-10-10",
  "priority_date": "2021-09-03",
  "application_number": "US-202117465959-A",
  "family_id": "82163543",
  "cited_by_count": 0,
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}