The Problem of Creating Intermediate Gas Preheat Combustion Chambers in a Gas Turbine Unit

摘要

A preliminary research study on the development of an annular combustion chamber with a preheating process is described. The chamber design is shown. The external liner and internal liner circumscribe the chamber volume which contains stabilizer combined with the fuel nozzle. The internal channel of the stabilizer-fuel nozzle unit contains blading apparatus with a 45 degrees flow deflection angle. The fuel flows from annular collector through a series of slots 0.35 mm in diameter. The fuel is injected at a pressure exceeding that of gases by 0.5-1.5 ata. The fuel-air mixing takes place in internal channels of the stabilizer-fuel nozzle. The telescopic liner confines the flame to the combustion zone. Up to 25 percent of the air is bypassed through annular channels and for cooling purposes. (Author)