FIELD: engines and pumps.
SUBSTANCE: compressor contains many chambers forming annular flow separation space in gas-turbine engine. That compressor includes dividing nose part (10) continued with inner and outer ring-shaped walls (12a, 12b), which restricts annular space (V) of separation of primary flow (F1) and secondary flow (F2). Space (V) contains many ring-shaped segments in the form of chambers (20) divided into pairs with blades (15) of the first fan, which pass through primary flow (F1) and through secondary flow (F2), and chambers (20) are attached to ring-shaped collar (30) located at the front and ring-shaped collar (40) located at the back, which are brought into rotation with blades (15).
EFFECT: installation of composite fan blades with possibility of their passage through primary flow of compressed medium.
11 cl, 6 dwg
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