FIELD: engines and pumps.
SUBSTANCE: aircraft engine comprises hollow nacelle (1) with air intake (2) at its front and jet nozzle (3) at its rear, central hot airflow generator (6), fan (8) arranged ahead of aforesaid generator to produce cold flow (9) for gas turbine engine. Proposed engine comprises also outer fairing (4) and inner fairing (10) embracing central generator (6). Aforesaid inner and outer fairings serve to make annular cross section duct (13) of the fan for cold flow (9). Note that engine comprises additionally precooler (18, 31, 38) that takes in hot air jet (19) from central generator (6) and cold air jet from cold airflow (9) to form cooled hot air jet intended for, for example air conditioning or anti-icing. Said precooler comprises at least one discharge pipe (12) arranged in chamber (12) to communicate precooler (18, 31, 38) with at least one outlet hole (26) made in inner fairing (10) where jet nozzle (3) comes out from nacelle (1), and directed upward, approximately, towards wing (16).
EFFECT: improved aerodynamic characteristics, longer life.
10 cl, 5 dwg
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RU2538350C2 |
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RU2411389C2 |
