Abstract: An annular combustor of a gas turbine engine comprising a front burner device located in the inlet section of the combustor and a flame tube, featuring a longitudinal split coinciding with that of the engine. The flame tube is formed by two concentric, outer and inner, shells with curvilinear surfaces. Each one of the shells is split longitudinally into sections, the places of the split being sealed with sealing members. In addition, the combustor is provided with at least two ring-shaped longitudinally-split load-bearing members for each one of the shells. The ring-shaped load-bearing member located in the zone of the combustor inlet section is capable of longitudinal and radial movements while the load-bearing member located in the zone of the combustor outlet section is capable of only radial movement.

Abstract: The method of fuel burning in combustion chambers resides in predivision of the primary and secondary air into discrete coaxial annular streams, swirling of the coaxial annular streams of primary air tangentially about the longitudinal axis of the combustion chamber, the adjacent annular streams being swirled in opposite directions, admission of the swirled coaxial streams of primary air and a portion of the coaxial annular streams of secondary air simultaneously with fuel into the burning zone to form a recirculation flow of the fuel-air mixture, and delivery of the remaining portion of the coaxial annular streams of secondary air into the mixing zone of the combustion chamber. The annular combustion chamber carrying this method into effect comprises two concentric annular flame tubes for restriction of the burning zone, with an annular stabilizer disposed therebetween and having holes for fuel supply provided in the outer wall thereof.