发明名称 |
ADJUSTMENT OF AXIAL COMPRESSOR OF GAS TURBINE ENGINE |
摘要 |
FIELD: engines and pumps.SUBSTANCE: proposed process consists in feed of hot gas tapped from the channel arranged downstream of turbine into channel arranged between inlet device and engine compressor in amount sufficient for maintenance of gas preset temperature at compressor inlet. Gas temperature at compressor inlet is kept constant and equal to air deceleration temperature at aircraft cruising speed. Air flow rate through engine and pressure difference at nozzle (at permanent gas temperature at compressor inlet) vary with variation of engine inlet air pressure.EFFECT: higher fuel efficiency at high flight speeds.3 cl, 4 dwg |
申请公布号 |
RU2535186(C1) |
申请公布日期 |
2014.12.10 |
申请号 |
RU20130122829 |
申请日期 |
2013.05.17 |
申请人 |
PIS'MENNYJ VLADIMIR LEONIDOVICH |
发明人 |
PIS'MENNYJ VLADIMIR LEONIDOVICH |
分类号 |
F02C3/34 |
主分类号 |
F02C3/34 |
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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