Abstract: Method of operating an autothermal reformer (ATR) to produce a high temperature reformate including preheating steam and air inputs to the ATR with heat from the reformate. The steam is heated by the reformate, and the air is then heated by the steam. There is no direct heat exchange between the reformate and the air. In the heat exchangers effecting the heat transfer, the steam is kept at a higher pressure that both the reformate and the air.

Abstract: Apparatus and method for mixing fuel and an oxidant for use in an autothermal reformer that provides hydrogen to a fuel cell. The apparatus includes a mixing vessel (10), a first inlet (4) to the mixing vessel for movement of gaseous fuel or oxidant therethrough, a second inlet for movement of gaseous fuel or oxidant therethrough, and an exit (60) from the vessel adjacent the autothermal reformer. The discharge ends of the inlets are spaced apart from each other and from the exit which is near a POX reactor (61) that combusts the mixture of fuel and oxidant exiting from the mixing vessel. The first inlet is comprised of a plate (26) with a plurality of tubes (24) extending therefrom through which fuel or oxidant passes.

Abstract: An apparatus for premixing fuel and air prior to combustion in a gas turbine engine, including: a linear mixing duct having a circular cross-section defined by a wall; a centerbody located along a central axis of the mixing duct and extending substantially the full length of the mixing duct, the centerbody having a plurality of orifices therein to inject fuel into the mixing duct with an axial velocity component; a fuel supply in flow communication with the centerbody orifices; an outer annular swirler located adjacent an upstream end of the mixing duct and including a plurality of circumferentially spaced vanes oriented so as to swirl air flowing therethrough in a first direction; an inner annular swirler located adjacent the mixing duct upstream end and including a plurality of circumferentially spaced vanes, the vanes having an outer radial portion having a leading edge and a trailing edge oriented so as to swirl air flowing therethrough in a second direction opposite the first swirl direction by the outer

Abstract: A gas turbine engine hot section component such as a turbine blade or vane having an airfoil is provided a non-film cooled portion of a heat transfer wall having a hot surface and a plurality of longitudinally extending micro-grooves disposed in the portion of the wall along the hot surface in a direction parallel to the direction of the hot gas flow. The depth of the micro-grooves is very small and on the order of magnitude of a predetermined laminar sublayer of a turbulent boundary layer. The grooves are sized so as to alter the boundary layer thickness near the leading edge of the airfoil to reduce heat transfer from the hot gas flow to the airfoil near the leading edge. In one embodiment the micro-grooves are about 0.001 inches deep and have a preferred depth range of from about 0.001 inches to 0.005 inches and which are square, rectangular, or triangular in cross-section and the micro-grooves are spaced about one width apart.