초록 ▼

A premixer is provided for injecting premixed fuel-air mixture into the inlet of a combustion apparatus. In one embodiment, the premixer assembly comprises a plurality of concentric, aerodynamic injector rings, with radially-directed injection holes. The injection holes have a plurality of different

A premixer is provided for injecting premixed fuel-air mixture into the inlet of a combustion apparatus. In one embodiment, the premixer assembly comprises a plurality of concentric, aerodynamic injector rings, with radially-directed injection holes. The injection holes have a plurality of different diameters, facilitating good mixing over a broad power range. Due to configuration and hole sizes, the assembly is gas or liquid compatible. The radial, concentric injection formation allows for a short injection path.

대표청구항 ▼

1. A fuel/air premixing apparatus for use upstream of the inlet of the main fluid flow path of an energy release/conversion system and separate from the heat release region of said energy release/conversion system, comprising: (a) a plurality of concentric, coplanar, non-circular aerodynamically sha

1. A fuel/air premixing apparatus for use upstream of the inlet of the main fluid flow path of an energy release/conversion system and separate from the heat release region of said energy release/conversion system, comprising: (a) a plurality of concentric, coplanar, non-circular aerodynamically shaped ring elements positioned upstream of said inlet, axially aligned within said flow path, each said ring element having an interior passage for fuel, each said ring element further comprising a plurality of fuel injection orifices whereby fuel may flow from said interior passage into the inlet fluid flow proximate to said ring, and wherein each pair of said ring elements defines an annular passage therebetween; wherein said rings are further adapted, whereby (i) said fuel injection orifices are oriented to inject fuel at an angle having an absolute value of from about 0 to about 90 degrees from the axial direction; and(ii) said plurality of fuel injection orifices are of non-uniform diameters, said diameters being sized at different sizes, each of said sizes selected to provide for a specified range of fuel-air momentum flux ratios, with each orifice paired with an orifice of a different size on an adjacent ring; and(b) a plurality of radially arranged, aerodynamically shaped spoke elements coplanar with said ring elements and interconnecting with said ring elements, at least one of said spoke elements having an interior passage for fuel, said interior passage within said spoke element being in fluid communication with said interior passages in the ring elements to which it is attached, the connected interior passages defined in said rings and said spokes further being in fluid communication with a fuel source; and(c) wherein said premixing apparatus is positioned on a trapped vortex cavity so that the fuel/air mixture is introduced into said trapped vortex cavity at an angle tangential to the recirculation flow within the cavity such that said fuel-air mixture joins the flow of said vortex approximately codirectionally with said vortex flow. 2. The premixer of claim 1, wherein the absolute value of said fuel injection orifice angle is from about 30 to about 60 degrees from the axial direction. 3. The premixer of claim 1, wherein the absolute value of said fuel injection orifice angle is from about 60 to about 90 degrees from the axial direction. 4. The premixer of claim 1, wherein the absolute value of said fuel injection orifice angle is about 70 degrees from said axial direction. 5. The premixer of claim 1, wherein the absolute value of said fuel injection orifice angle is about 90 degrees from said axial direction. 6. The premixer of claim 1, comprising from about 2 to about 5 of said rings. 7. The premixer of claim 1, wherein the number and dimensions of said rings are chosen to provide for a flow blockage of said inlet of not more than 50%. 8. The premixer of claim 7, wherein the number and dimensions of said rings are chosen to provide for a flow blockage of said inlet of not more than 40%. 9. The premixer of claim 1, wherein the fluid communications with said fuel source enters said premixer through the interior passage in the most outer one of said concentric rings. 10. The premixer of claim 1, for use in a can combustor, further comprising a hub element situated approximately at the center of the cross-section of said inlet, said hub element being connected to said spoke elements and having an interior passage therein in fluid communication with said at least one spoke element having an interior passage therein for fuel. 11. The premixer of claim 10, wherein the fluid communication with said fuel source enters said premixer through the interior passage in said hub. 12. The premixer of claim 1, wherein said orifices comprise a set of smaller diameter orifices sized for low fuel-air momentum flux ratios and at least one set of larger diameter orifices sized for higher fuel-air momentum flux ratios. 13. The premixer of claim 2, wherein the orifices in adjacent pairs of said ring elements face toward each other. 14. The premixer of claim 12, wherein each of said sets of orifices are approximately evenly spaced circumferentially around said ring elements. 15. The premixer of claim 13, wherein said orifices comprise a set of smaller diameter orifices sized for low fuel-air momentum flux ratios and at least one set of larger diameter orifices sized for higher fuel-air momentum flux ratios, and wherein the orifices facing toward each other in adjacent pairs of said ring elements are of different diameters. 16. The premixer of claim 15, wherein said orifices comprise one set of smaller orifices adapted for low power operation, one set of orifices adapted for medium power operation and one set of orifices adapted for high power operation. 17. An assembly comprising a premixer and an energy release/conversion system in accordance with claim 1, further comprising a gas turbine, said assembly being adapted for electric power generation. 18. An assembly comprising a premixer and an energy release/conversion system in accordance with claim 1, further comprising a gas turbine, said assembly being adapted for use as a propulsion jet engine for aviation. 19. An assembly comprising a premixer and an energy release/conversion system in accordance with claim 1, further comprising a gas turbine, said assembly being adapted as an auxiliary electric power generation unit. 20. An assembly comprising a premixer and an energy release/conversion system in accordance with claim 1, further comprising a gas turbine, said assembly being adapted as a combustion turbine for a combined heat and power plant. 21. An assembly comprising a premixer and an energy release/conversion system in accordance with claim 1, further comprising a gas turbine, said assembly being adapted as a combustion turbine for an integrated gasification combined cycle plant.