FIELD: machine building; aviation.
SUBSTANCE: present invention relates to aircraft turbine crankcase (30), ring (28) sections unit intended for installation on it, which partially restricts channel of gas flow passage through turbine, containing ring (28) sections radial position dynamic adjustment devices, radial inlet tab (38), which connects each ring (28) section inlet end section with crankcase (30) and outlet radial tab (40), which connects each ring (28) section output end section with crankcase (30), wherein, at least, inlet radial tab (38) is made integral with crankcase (30) and directly connected to each ring (28) section inlet end section.
EFFECT: enabling reduction of crankcase weight and risk of leakages is limited.
8 cl, 4 dwg
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