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Abstract
The interrelations between the size of the gas turbine engine (GTE) and the size and workflow of the combustion chamber (CC) were considered. On the base of analysis of workflow organization the design of CC with toroidal recirculation mixing zone was proposed. The theoretical justification of chosen design was carried out on the base of comparison of combustion volumes, which formed in traditional CC with swirlers and in proposed CC. The comparison of combustion volumes, schematic display of combustion zones with a discrete flame and a combined combustion zone were given.
Highlights
A large number of different requirements can be offered to small-sized gas turbine engine (GTE) due to the wide range of tasks it solve
The fulfillment of most of these requirements is related to the choice of the combustion chamber design and is one of the most important problems of preliminary design
With a reduction of the size of the engine relative to the prototype, its combustion chamber cannot be reduced by scaling its elements, because of the changes in the preparation of fuel-air mixture, the organization of the cooling system and air mixing
Summary
Where γengine – engine specific weight, Mengine – engine weight, N – engine power, D – linear engine size. The geometric limitations imposed on the choice of the scheme and design of the CC are dictated by the ratio of the diametrical dimensions of the last stage of the compressor, the first stage of the turbine and the axial dimension between them These parameters determine the length of the combustion chamber, the angle of its tilt, the overall size of the body and other geometric characteristics. As an alternative to these methods of organizing combustion, a method of forming a toroidal recirculation zone can be used, with a rotating vortex capable of stabilizing the focus of the flame [4] This method allows us to: use cheaper and easier to manufacture jet nozzles as the main ones, reduce the height of the flame tube and increase the compactness of the compressor.
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