tangential to skirt ring 52 or u03b2 being equal to 90 u00b0 because baffles 56 are flat sheets and flange 54 and skirt ring 52 are curved surfaces in order to fit baffle 56 in the annular region between flange 54 and skirt ring 52 the intersects between baffle 56 and flange 54 and between baffle 56 and skirt ring 52 are curvilinear lines and in an embodiment where u03b2 is less than 90 u00b0 the angle is approximately and calculated in relation to the midpoint of baffle 56 thus optimum results are achieved by the above described angles in this manner the favorable mixing pattern of gas and combustion air is created which results in a short turbulent flame that is away from the components of burner body 22 and burner face 27 again with reference to fig1 the operation of the swirl combuster burner 20 of the present invention will be understood combustion air is provided through conduit 35 to inlet 34 into the burner body 22 the combustion air travels past the baffles 56 which induces turbulence of the combustion air simultaneously gas or other suitable fuel is supplied through gas piping train 40 and enters inner gas chamber 36 the gas passing through the angular openings 46 of nozzle 44 is forced along the sides of inner chamber 36 which induces a turbulent flow of the gas which is isolated from the combustion air while in the inner chamber 36 the turbulent gas and turbulent combustion air mix in a region a above the burner face 27 known as a mixing zone the mixture of gas and air rises into combustion chamber 12 and is ignited by the end 30 of ignition and flange.