ROTOR ASSEMBLY FOR GAS TURBINE ENGINE Russian patent published in 2012 - IPC F01D5/30 

FIELD: machine building.

SUBSTANCE: rotor assembly for gas turbine engine includes a pair of metal discs with central hole for rotor shaft and many accurately processed through holes for a pin, uniformly distributed throughout the length of two concentric circles, and blade assembly arranged between metal discs. Blade assembly includes many double blades from composite laminated material, each of which has a pair of aerodynamically shaped feather parts and common root part in the form of U-seat the shape of which provides its seating in the pin. Blades are combined with two concentric load-carrying rings of the first and the second row relative to the shaft, and inter-blade inserts from composite laminated material. Inter-blade inserts are arranged on surface of load-carrying ring of the second row between each pair of feather parts of double blade and adjacent double blades. Inter-blade insert has box form with a hole for a pin on one end and aerodynamic shaping on the other end, constituting together with feather part of the blades the aerodynamic working surface of rotor assembly. Metal discs and blade assembly is attached to rotor assembly by means of pins of the first and the second row. Pins enter the holes of both discs and their ends protrude in order to fix discs on them. Pins of the first row enter the holes of the first circle of discs through the seat of double blade and conjugate its inner surface and load-carrying ring of the first row. Pins of the second row enter the holes of the second circle of discs through the hole of inter-blade inserts and conjugate feather parts of blades and load-carrying ring of the second row and are supported on the surface of load-carrying ring of the second row.

EFFECT: invention allows increasing service life and improving reliability of rotor of gas turbine engine.

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