FIELD: engines and pumps.
SUBSTANCE: invention relates to control over clearance between the edges of aircraft gas turbine blades and outer housing turbine shroud. Valve is arranged in air channel opens to cool the turbine shroud at high rpm phase (TO+CL) corresponding to aircraft takeoff and climb phases and at rated rpm phase (CR) following after high-rpm phase and corresponding to aircraft cruising phase. Invention covers also the system to implement described method.
EFFECT: simplified design, decreased weight.
10 cl, 4 dwg
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2006 |
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- Grant Karl
|
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2010 |
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2016 |
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2017 |
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|
RU2704056C2 |
| JET TURBINE ENGINE |
2011 |
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2012 |
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2013 |
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|
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2010 |
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