| 摘要 |
FIELD: engines and pumps. ^ SUBSTANCE: bypass gas-turbine engine for aircraft includes hollow nacelle with longitudinal axis, which is equipped from the front with an air inlet, and from behind - with air outlet, central hot flow generator located in axial direction in the nacelle, fan and pre-cooler. Fan is located in axial direction in the nacelle before central generator and has the possibility of generating the cold flow for gas turbine engine. Inside the nacelle there located is outer cowling, and inner cowling envelopes central generator. Outer and inner cowlings restrict between themselves the fan channel of annular cross section for cold flow. Inner cowling with central generator restricts intermediate chamber of annular cross section, which envelopes central generator, and is used for cold air flow circulation, by means of which it is possible to control central generator temperature. Pre-cooler includes inlet of hot air flow extracted from central generator, and outlet for hot air flow cooled by means of cold flow. Pre-cooler is located at least inside the section of rear part of inner cowling on the side similar to that of intermediate chamber and about longitudinal axis. Pre-cooler has thermal contact to rear part of inner cowling so that it can be cooled with cold flow supplied to rear part of inner cowling. ^ EFFECT: invention allows reducing aerodynamic disturbances in the fan channel and using cold air extracted from fan channel and supplied to rear part of inner cowling. ^ 8 cl, 10 dwg |
