FIELD: engines and pumps.
SUBSTANCE: subject of invention is aircraft engine with installation of diffuser at azimuth angle between diffuser and combustion chamber. Fixed blades (15) of diffuser (14) are installed under azimuth angle (α) relative to nozzles (9) of combustion chamber so that trajectories (35), leading from rear edges (34), pass through gaps (38) between nozzles (9) and more preferably in the middle there between, such that those portions of the stream which can contain condensed water have no effect on the initiation of combustion. In other words, angular position of diffuser blades is set so that to limit accumulation of water in front of nozzles and to ensure their obtaining of more dry air at simultaneous concentration of water and providing possibility of its passage between nozzles, as a result of which it will not damage combustion.
EFFECT: disclosed is an aircraft engine with installation of diffuser at azimuth angle relative to combustion chamber.
6 cl, 3 dwg
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