Abstract: Various COx electrolyzer multi-cell architectures are provided, including various frame, flow field, gas diffusion layer, and repeat unit designs that may be particularly useful in the context of multi-cell COx electrolyzer cells.

Abstract: Various COx electrolyzer cell architectures are provided, including various flow field designs and gas diffusion layer designs that may be particularly useful in the context of COx electrolyzer cells.

Abstract: A mixer for a combustor includes a swirler having a plurality of vanes disposed at an upstream end of a mixing duct. A centerbody extends downstream from the vanes and includes a fuel chamber integrally joined to the vanes. Fuel injection openings extend from the chamber into passages between the vanes.

Abstract: A low NOx combustor and method improve dynamic stability of a combustion flame fed by a fuel and air mixture. The combustor includes a chamber having a dome at one end thereof to which are joined a plurality of premixers. Each premixer includes a duct with a swirler therein for swirling air, and a plurality of fuel injectors for injecting fuel into the swirled air for flow into the combustion chamber to generate a combustion flame therein. The fuel injectors are axially staged at different axial distances from the dome to uncouple the fuel from combustion to reduce dynamic pressure amplitude of the combustion flame.

Abstract: A combustor cooperating with a compressor in driving a gas turbine includes a cylindrical outer combustor casing. A combustion liner, having an upstream rich section, a quench section and a downstream lean section, is disposed within the outer combustor casing defining a combustion chamber having at least a core quench region and an outer quench region. A first plurality of quench holes are disposed within the liner at the quench section having a first diameter to provide cooling jet penetration to the core region of the quench section of the combustion chamber. A second plurality of quench holes are disposed within the liner at the quench section having a second diameter to provide cooling jet penetration to the outer region of the quench section of the combustion chamber.

Abstract: A combustor liner includes an inner layer for facing combustion gases, and an opposite outer layer for facing a cooling fluid. The outer layer has a greater coefficient of thermal conductivity than the inner layer for reducing temperature gradients in the liner. In a preferred embodiment, the outer layer significantly reduces temperature gradients in the liner which are caused by the varying cooling ability of impingement cooling air jets for more uniformly cooling the combustor liner and reducing the maximum temperature thereof.

Abstract: A low NOx combustor and method improve dynamic stability of a combustion flame fed by a fuel and air mixture. The combustor includes a chamber having a dome at one end thereof to which are joined a plurality of premixers. Each premixer includes a duct with a swirler therein for swirling air, and a plurality of fuel injectors for injecting fuel into the swirled air for flow into the combustion chamber to generate a combustion flame therein. The fuel injectors are axially staged at different axial distances from the dome to uncouple the fuel from combustion to reduce dynamic pressure amplitude of the combustion flame.

Abstract: A combustor comprises a hollow body defining a combustion chamber. The hollow body is typically annular in form and includes an outer liner, an inner liner, and an upstream dome plate. The dome plate includes a swirl cup with a mixer disposed therein to provide uniform mixing of fuel and air. The mixer comprises an inner swirler and an outer swirler that are mounted in the swirl cup. The outer swirler includes solid vanes. A shroud surrounds the mixer at the upstream end, which shroud includes an annular fuel chamber. The shroud further includes a number of axial fuel injection fuel injection openings that provide flow communication between the annular fuel chamber and the mixer and radially inject fuel within the mixer.

Abstract: A combustor liner includes an inner layer for facing combustion gases, and an opposite outer layer for facing a cooling fluid. The outer layer has a greater coefficient of thermal conductivity than the inner layer for reducing temperature gradients in the liner. In a preferred embodiment, the outer layer significantly reduces temperature gradients in the liner which are caused by the varying cooling ability of impingement cooling air jets for more uniformly cooling the combustor liner and reducing the maximum temperature thereof.