| 摘要 |
aero-engine manufacture. SUBSTANCE: diverging members 54 and 55 limiting the flow 4 of hot exhaust gases in diverging section 48 of exhaust nozzle 14 of aircraft gas-turbine engine which are cooled selectively run longitudinal; they are symmetrical in circumferential direction and are used for turning diverging doors 54 and seals 55 of axisymmetrical guide nozzle 14. Device includes front and rear sections which are adjacent in axial direction; these sections belong to at least one of members limiting the exhaust flow (referred to as doors and seals); adjacent front and rear sections have respectively front and rear inner hot surfaces and fastening unit 56 for securing the rear section to front section in one of two positions. In first position, the sections are located at some distance relative to each other forming clearance between sections for flowing cooling air towards rear inner hot surface; in second position, sections tightly adjoin excluding flow of surrounding air to rear inner hot surface. EFFECT: possibility of shifting the exhaust nozzle of aircraft gas-turbine engine from ejector mode of cooling inner hot surfaces of diverging section of nozzle at suppression of engine infra-red radiation characteristics to non-ejector mode to obtain maximum operating characteristics. 5 cl, 6 dwg |
