FIELD: power industry.
SUBSTANCE: fuel feed system of combustion chamber of gas turbine engine, which contains fuel injector (80) with two flows for spray of primary fuel flow supplied by primary fuel feed circuit, and secondary fuel flow supplied by secondary fuel feed circuit. Primary fuel flow forms fuel cone (83) formed by primary and secondary fuel flows. Spray device of fuel leaving injector (80) has rotational symmetry about Y axis and includes sliding traverse (20) in the centre of which injector (80) is arranged, radial spirals (40, 41, 42) connected by means of outlet ends to mixing tank (60), and they are all located at the inlet and outlet in fuel flow direction. Radial spirals (40, 41, 42) contain Venturi pipe (50) equipped with inner wall (51) with developed section, which contains inlet converging part (51a) connected to outlet diverging part (51b) by means of transition zone. Venturi pipe (50) has minimum inner diameter at the level of transition zone and has the length, shape and axial position, which are such that cone (83) of primary flow covers flow pipe (50). Fuel cone (83) at the outlet of Venturi pipe (50) has semiangle β at the top constituting 30 to 40 degrees. Fuel cone (83) contains the first central part (83a) and the second peripheral part (83b). The first central part (83a) forms cone with semiangle α0 at the top, which is tangent at point A0 to the outlet diverging part (51b) of Venturi pipe 50, and at that, α0 is less than β. The second peripheral part (83b) forms the cone the semiangle at the top of which at the injector outlet is α0 to β. Fuel cone (83) at injector outlet (80) covers inner wall (51) of Venturi pipe (50) along the surface above tangent point A0 to point A1 arranged above minimum inner diameter of Venturi pipe (50).
EFFECT: reducing oscillations of thermal effects on Venturi pipe and reducing its carbonisation.
7 cl, 4 dwg
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Authors
Dates
2011-12-20—Published
2007-06-28—Filed