FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft engine technology, particularly to aircraft gas turbine engines axial fans. High-speed axial fan impeller comprises disc, blades installed in disc and path flanges arranged on disc between blades with formation of blade channel inner surface. Blades are made with forward sweep in peripheral part, and leading and trailing edges generatrices projections on meridian plane contain convexity towards against flow, located in blades middle part. Leading edge generatrix projection on each blade meridian plane has straight line section. Straight line section height, as well as shape of working blade leading edge generatrix projection on meridian plane is defined by relationships protected by this invention.
EFFECT: invention allows to increase high-speed axial fan impeller efficiency while maintaining gas dynamic stability and absence of impeller blades bending-torsional flutter.
1 cl, 7 dwg
| Title | Year | Author | Number |
|---|---|---|---|
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|
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| BIROTARY SCREW-TYPE BLOWER | 2008 |
|
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|
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|
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|
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|
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|
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|
RU2636998C1 |
| BIROTARY SREW-TYPE BLOWER | 2008 |
|
RU2367822C1 |
