FIELD: engines and pumps.
SUBSTANCE: invention relates to axial pumps or compressors used turbojet engines. Proposed pump or compressor consists of rotor 2 with vanes 5 and stator 1 with guide vanes. In the pump lengthwise axis, vanes 5 are inclined towards the flow and/or axis of blade 5 makes geometrical location of points whereat, in each of them, the moment of radial-longitudinal component of aerodynamic force is equal in magnitude and opposite in direction to centrifugal force moment. To compensate for bending moment of aerodynamic forces acting on vane 5, centrifugal force is used. To this effect, vane 5 either deflects towards appropriate side or has corresponding flexure in lengthwise and crosswise planes.
EFFECT: higher reliability.
3 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| TURBINE ENGINE (VERSIONS) | 2008 |
|
RU2397351C2 |
| PROPELLER (VERSIONS) | 2007 |
|
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|
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|
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|
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|
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|
RU2630919C1 |
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|
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|
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|
RU2630922C1 |
