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A fuel-air premixer for use in a combustor of a gas turbine includes an air inlet, a fuel inlet, a shroud, a central body and a cascade of vanes. The premixer mixes fuel and air in the annular mixing passage into a uniform mixture for injecting into a combustor reaction zone. The air from a compress

A fuel-air premixer for use in a combustor of a gas turbine includes an air inlet, a fuel inlet, a shroud, a central body and a cascade of vanes. The premixer mixes fuel and air in the annular mixing passage into a uniform mixture for injecting into a combustor reaction zone. The air from a compressor is injected into the mixer through an air inlet. The fuel is introduced into air stream via fuel injection holes that pass through the walls of the vanes which contain internal fuel flow passages. The flow field inside the premixer is broken up by the arrayed vanes into a series of small regions each containing a well designed small size mixing eddy which is steadily attached to the surface of the vanes.

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1. A premixer for use in a combustor of a gas turbine, the premixer comprises: a circular shroud and a cylinder central body which contains a fuel flow passage wherein the shroud and the central body confine an annular mixing passage between them, whereinan air inlet is located at an upstream end of

1. A premixer for use in a combustor of a gas turbine, the premixer comprises: a circular shroud and a cylinder central body which contains a fuel flow passage wherein the shroud and the central body confine an annular mixing passage between them, whereinan air inlet is located at an upstream end of the mixing passage and a fuel inlet is located at an upstream end of the fuel flow passage inside the central body, wherein fuel and air are premixed in the annular mixing passage into a mixture for injecting into a combustor reaction zone, andthe mixing passage comprises a cascade of arrayed vanes including from upstream to downstream:a plurality of fuel nozzle vanes, each comprising a forehead with curved outer surface and a thin tail along the middle line of the vane to form mixing eddies which are symmetrically attached on both sides of the thin tail, each of the fuel nozzle vanes further comprising multiple fuel injection holes on the wall thereof and an internal fuel flow passage communicated with the fuel passage inside the central body receiving the fuel from the fuel inlet,a plurality of mixing vanes, each comprising a forehead with curved outer surface and a thin tail along the middle line of the vane to form mixing eddies which are symmetrically attached on both sides of the thin tail, anda plurality of turning vanes imparting swirl to the incoming mixture. 2. The premixer according to claim 1, wherein each of the turning vanes is initially parallel with the axis of the central body, then bend circumferentially and the thickness of the vanes gradually reduced. 3. The premixer according to claim 1, wherein the central body comprises a non-airfoil downstream end, which causes the separation of the fuel-air mixture flow, forming a recirculation zone downstream the central body and improving the performance of flame holding. 4. A gas turbine combustor comprising: a reaction zone in which a mixture of air and fuel is combusted, anda premixer the premixer comprising: a circular shroud and a cylinder central body which contains a fuel flow passage wherein the shroud and the central body confine an annular mixing passage between them, whereinan air inlet is located at an upstream end of the mixing passage and a fuel inlet is located at an upstream end of the fuel flow passage inside the central body, wherein fuel and air are premixed in the annular mixing passage into the mixture for injecting into the combustor reaction zone, andthe mixing passage comprises a cascade of arrayed vanes including from upstream to downstream:a plurality of fuel nozzle vanes, each comprising a forehead with curved outer surface and a thin tail along the middle line of the vane to form mixing eddies which are symmetrically attached on both sides of the thin tail, each of the fuel nozzle vanes further comprising multiple fuel injection holes on the wall thereof and an internal fuel flow passage communicated with the fuel passage inside the central body receiving the fuel from the fuel inlet,a plurality of mixing vanes, each comprising a forehead with curved outer surface and a thin tail along the middle line of the vane to form mixing eddies which are symmetrically attached on both sides of the thin tail, anda plurality of turning vanes imparting swirl to the incoming mixture, and the mixture is injected from the premixer into the reaction zone. 5. The gas turbine combustor according to claim 4, wherein each of the turning vanes is initially parallel with the axis of the central body, then bend circumferentially and the thickness of the vanes gradually reduced. 6. The gas turbine combustor according to claim 4, wherein the central body comprises a non-airfoil downstream end, which causes the separation of the fuel-air mixture flow, forming a recirculation zone downstream the central body and improving the performance of flame holding.