发明名称 |
COOLING SYSTEM OF GAS TURBINE OF DOUBLE-FLOW TURBOJET ENGINE WITH ADDITIONAL COMPRESSION OF AIR ION SMALL-SIZE FAN |
摘要 |
FIELD: double-flow turbojet engines. ^ SUBSTANCE: proposed cooling system of gas turbine of double-flow turbojet engine with additional compression of air in small-size fan contains space to take off secondary air flow from main combustion chamber, power diaphragm, set of vanes of nozzle assembly and disk deflectors. Inlet sections of central channels of nozzle assembly vanes are connected by air manifold with lips to take off air from outer loop. Outlet sections of said channels are connected with space to deliver air to central fan installed on shaft of high-pressure turbine. ^ EFFECT: improved specific parameters of double-flow turbojet engine. ^ 1 dwg |
申请公布号 |
RU2323359(C1) |
申请公布日期 |
2008.04.27 |
申请号 |
RU20060124303 |
申请日期 |
2006.07.06 |
申请人 |
IRKUTSKOE VYSSHEE VOENNOE AVIATSIONNOE INZHENERNOE UCHILISHCHE (VOENNYJ INSTITUT) |
发明人 |
KARAVAEV JURIJ ANDREEVICH;TATARNIKOV PAVEL GENNAD'EVICH |
分类号 |
F02C7/12 |
主分类号 |
F02C7/12 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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