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Patexia Research
Patent No. US 11371700
Issue Date Jun 28, 2022
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Patent 11371700 - Deflector for conduit inlet within a combustor section plenum > Claims

  • 1. An assembly for a gas turbine engine, the assembly comprising: a combustor wall configured with a quench aperture;a case displaced from the combustor wall such that a plenum is formed by and extends between the combustor wall and the case;the case comprising an inner portion of a case wall extending between a compressor and a turbine, a deflector, a gate, and an outer portion of the case wall radially outward of the inner portion, wherein a conduit is defined between the inner portion and the outer portion of the case wall to supply air from the plenum to the turbine for cooling;the deflector projecting out from the inner portion of the case wall into the plenum towards the combustor wall, and the deflector arranged upstream of the quench aperture;the gate projecting out from the outer portion of the case wall into the plenum towards the combustor wall; andan inlet to the conduit arranged next to and downstream of the deflector and upstream of the gate, and the inlet to the conduit arranged axially upstream of the quench aperture.
    • 2. The assembly of claim 1, wherein the case is displaced radially inward of the combustor wall relative to an axis of the gas turbine engine.
    • 3. The assembly of claim 1, wherein the deflector is arranged axially upstream of the quench aperture relative to an axis of the gas turbine engine.
    • 4. The assembly of claim 1, wherein the deflector is axially overlapped by an axial upstream-most half of the combustor wall.
    • 5. The assembly of claim 1, wherein the deflector comprises a ramped deflector.
    • 6. The assembly of claim 1, wherein the deflector is cantilevered from the case wall.
    • 7. The assembly of claim 1, wherein the deflector projects out from the case wall in a direction that includes a radial outward component and an axially downstream component relative to an axis of the gas turbine engine.
    • 8. The assembly of claim 1, wherein the deflector is configured such that gas flowing within the plenum turns more than ninety degrees around a distal end of the deflector before entering the inlet.
    • 9. The assembly of claim 1, wherein the gate is configured to reduce or prevent recirculating gas within the plenum from flowing into the inlet.
      • 10. The assembly of claim 9, wherein the deflector has a deflector chord line that is angularly offset from an axis by a deflector angle; andthe gate has a gate chord line that is angularly offset from the axis by a gate angle that is equal to the deflector angle.
      • 11. The assembly of claim 9, wherein the deflector has a deflector chord line that is angularly offset from an axis by a deflector angle; andthe gate has a gate chord line that is angularly offset from the axis by a gate angle that is different than the deflector angle.
      • 12. The assembly of claim 9, wherein the gate is connected to the conduit at the inlet.
      • 13. The assembly of claim 9, wherein the gate is cantilevered from the conduit.
    • 14. The assembly of claim 1, wherein the inlet is arranged upstream of the quench aperture.
    • 15. The assembly of claim 1, further comprising a tangential onboard injector nozzle fluidly coupled with the plenum through the conduit.
    • 16. The assembly of claim 1, further comprising: a turbine component;the conduit fluidly coupling a passage in the turbine component with the plenum.
    • 17. The assembly of claim 1, further comprising: an annular combustor comprising an inner combustor wall, an outer combustor wall and a bulkhead, wherein the inner combustor wall comprises the combustor wall;the bulkhead extending radially between and connected to the inner combustor wall and the outer combustor wall.
  • 18. An assembly for a gas turbine engine, the assembly comprising: a combustor wall extending axially along and circumferentially about an axial centerline;a case radially displaced from the combustor wall, wherein a plenum extends radially from the case to the combustor wall;the case comprising an inner portion of a case wall extending between a compressor and a turbine, a deflector, a gate, and an outer portion of the case wall radially outward of the inner portion, wherein a conduit is defined between the inner portion and the outer portion of the case wall to supply air from the plenum to the turbine for cooling;the deflector projecting out from the inner portion of the case wall, into the plenum and towards the combustor wall, to a downstream distal end of the deflector, and the downstream distal end of the deflector axially overlapped by an axially upstream half of the combustor wall;the gate projecting out from the outer portion of the case wall into the plenum towards the combustor wall; andan inlet to the conduit arranged between the downstream distal end of the deflector and an upstream end of the gate.
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