FIELD: gas turbine engines.
SUBSTANCE: invention relates to the field of compressors for low-thrust gas turbine engines on unmanned and small manned aircraft, ground, surface vehicles and power plants. The compressor contains two stages, and the working blades of the first and second stages are located on both sides of the common carrier disk, and their bladed diffusers are made of a radial-axial type. After the vaned diffusers, a cross manifold is placed with mutually perpendicular flows of the radial and axial directions, and the steps are connected to each other through a radial-axial channel, in which the reverse guide vane is located.
EFFECT: reduction in weight, dimensions and increase in compressor efficiency.
1 cl, 4 dwg
| Title | Year | Author | Number |
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|
RU2234623C2 |
