GAS TURBINE ENGINE AFTERBURNER CHAMBER Russian patent published in 2008 - IPC F02K3/10 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine afterburner chamber incorporates a diffuser arranged in its casing and formed by a part of the behind-the-turbine cowl surface and the cooling screen, each of the said parts representing a body of revolution and a front device. The cooling screen part and, at least, a part of the behind-the-turbine cowl surface in meridian section feature the profiles defined by polynomials. The cooling screen surface features a bend. At the point of the said bend there is an angle a between the tangent to the cooling screen surface and the afterburner chamber lengthwise axis making in meridian section 20 to 35°. The angle β between the tangent to cowl surface part defined by the polynomial at the point of its intersection with the cowl side surface and the afterburner chamber lengthwise axis in meridian section makes 10 to 25°. The diffuser outlet section area-to-diffuser section area at the bent point makes or exceeds 0.8.

EFFECT: reduced full pressure loss in the afterburner flow section due to optimum diffuser profile.

5 cl, 2 dwg