| 摘要 |
FIELD: aircraft industry; turbojet engines. ^ SUBSTANCE: according to proposed method, intensive cooling of high-pressure compressor housing is carried out by flow from external circuit at relative velocity of lambda>0.1 for 0.2.t0<▵t<0.8.t0 after which air is returned into passage part of external circuit, where t0 is time at a lapse of which additional increase of radial clearances caused by nonstandard thermal process after completion of engine pickup becomes equal to zero. Device to prevent surging of aircraft double-flow turbojet engine at take-off regime has cooler made in form of circular screen arranged around high-pressure compressor housing and forming ring channel around said housing. Area of passage section of ring channel is protected by claim of invention. Ring channel is connected by intake and outlet branch pipes with passage part of external circuit of aircraft double-flow turbojet engine. Adjustable-area air intakes with drive are installed on intake branch pipes. ^ EFFECT: prevention of surges in aircraft turbojet engine at take off regime owing to prevention of increase of radial clearances in high pressure compressor and gas temperature rise before turbine. ^ 3 cl, 2 dwg, 6 charts |
