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Patexia Research
Patent No. US 11226098
Issue Date Jan 18, 2022
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Patent 11226098 - Film-cooled multi-walled structure with one or more indentations > Claims

  • 1. A combustor for a turbine engine, comprising: a combustor wall comprising a heat shield;the heat shield defining a plurality of cooling apertures and an indentation in a side of the heat shield that forms a portion of a peripheral boundary of a combustion chamber within the combustor;the heat shield including a first surface and a second surface with the first surface forming an outlet of a first of the plurality of cooling apertures and the second surface forming the indentation;each of the plurality of cooling apertures extending through the heat shield;the indentation configured such that at least a portion of cooling air directed out from the first of the plurality of cooling apertures into the combustion chamber circulates against the side of the heat shield; andthe first surface overlapping an upstream portion of the second surface of the indentation.
    • 2. The combustor of claim 1, wherein the plurality of cooling apertures in the heat shield are effusion apertures.
    • 3. The combustor of claim 1, wherein the first and second surfaces are adjacent and contiguous with one another.
    • 4. The combustor of claim 1, wherein the outlet of the first of the plurality of cooling apertures crosses an edge of the indentation.
    • 5. The combustor of claim 1, wherein the heat shield further defines a second indentation in the side of the heat shield, and the second indentation is configured such that at least a portion of cooling air directed from a second of the plurality of cooling apertures circulates against the side of the heat shield.
    • 6. The combustor of claim 1, wherein the heat shield includes an arcuate panel in which the first of the plurality of cooling apertures and the indentation are defined.
    • 7. The combustor of claim 1, wherein the combustor wall further includes a shell; a cooling cavity extends between and is formed by the shell and the heat shield; and the plurality of cooling apertures are fluidly coupled with the cooling cavity.
    • 8. The combustor of claim 1, wherein an edge of the indentation extends circumferentially around the outlet of the first of the plurality of cooling apertures such that the outlet of the first of the plurality of cooling apertures is completely within the upstream portion of the indentation.
    • 9. The combustor of claim 1, wherein the heat shield comprises a surface that defines the indentation; and the indentation has a circular peripheral geometry.
  • 10. A combustor for a turbine engine, comprising: a combustor wall comprising a heat shield;the heat shield defining a plurality of cooling apertures and an indentation in a side of the heat shield that forms a portion of a peripheral boundary of a combustion chamber within the combustor;the heat shield including a first surface and a second surface with the first surface forming an outlet of a first of the plurality of cooling apertures and the second surface forming the indentation;the plurality of cooling apertures extending through the heat shield, and the first surface of the outlet of the first of the plurality of cooling apertures is located on an edge of the second surface of the indentation; andthe indentation configured such that at least a portion of cooling air directed out from the outlet into the combustion chamber circulates against the side of the heat shield.
    • 11. The combustor of claim 10, wherein the heat shield extends between a chamber surface and a cavity surface that defines a portion of a cooling cavity; a point of an indentation surface that defines the indentation is located a distance from the cavity surface; and the distance is between fifty percent and ninety percent of a thickness of the heat shield measured between the cavity and the chamber surfaces.
    • 12. The combustor of claim 10, wherein a cross-sectional area of the outlet is between one percent and fifty percent of an area of an indentation surface that defines the indentation.
    • 13. The combustor of claim 10, wherein the plurality of cooling apertures in the heat shield are effusion apertures.
  • 14. A combustor for a turbine engine, comprising: a combustor wall comprising a heat shield;the heat shield configured with a plurality of cooling apertures and a plurality of indentations in a side of the heat shield that defines a portion of a peripheral boundary of a combustion chamber within the combustor;the heat shield including a first surface and a second surface with the first surface forming an outlet of each of the plurality of cooling apertures and the second surface forming each of the plurality of indentations;the plurality of indentations comprising a first indentation and a second indentation located downstream of the first indentation;the plurality of cooling apertures extending through the heat shield;the first surface overlapping an upstream portion of the second surface of the indentation;the first indentation configured such that at least a portion of cooling air directed from a first of the plurality of cooling apertures into the combustion chamber circulates in the first indentation against the side of the heat shield; andthe second indentation configured such that at least a portion of cooling air directed from a second of the plurality of cooling apertures into the combustion chamber circulates in the second indentation against the side of the heat shield downstream of the first indentation.
    • 15. The combustor of claim 14, wherein the indentation comprises an oval peripheral geometry.
    • 16. The combustor of claim 14, wherein the indentation has a peripheral geometry with one or more concave sections and one or more convex sections.
    • 17. The combustor of claim 14, wherein at least one of the first surface and the second surface is an annular surface of the heat shield.
    • 18. The combustor of claim 14, wherein an opening to the first indentation is directly radially adjacent and fluidly coupled with the combustion chamber; and an opening to the second indentation is directly radially adjacent and fluidly coupled with the combustion chamber.
    • 19. The combustor of claim 14, wherein the heat shield extends between a first side of the heat shield and a second side of the heat shield that is opposite the first side of the heat shield, and the first side of the heat shield is the side of the heat shield that defines the portion of the peripheral boundary of the combustion chamber within the combustor; an opening to the first indentation is on the first side of the heat shield; and an opening to the second indentation is on the first side of the heat shield.
    • 20. The combustor of claim 14, wherein the heat shield extends circumferentially around the combustion chamber; the heat shield extends radially between an inner side of the heat shield and an outer side of the heat shield that is opposite the inner side of the heat shield, and the inner side of the heat shield is the side of the heat shield that defines the portion of the peripheral boundary of the combustion chamber within the combustor; an opening to the first indentation is on the inner side of the heat shield; and an opening to the second indentation is on the inner side of the heat shield.
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