FIELD: engines and pumps.
SUBSTANCE: fixed unit of gas turbine engine blades contains inner housing, angular sectors provided with blades, and angular sectors radial support pins. Each angular sector contains a platform and a back plate for angular sector fastening on housing, the plate protruding from the platform radially inside. Housing contains the first annular groove opening radially outside and receiving back plates. Radial support pins are installed in holes made in housing and back plates and provided with axes parallel to longitudinal axis of gas turbine engine. Housing also contains the second annular groove opening radially outside and receiving a ring of axial support of radial support pins. Ring of axial support is located on combustion chamber side relative to the first groove. The other invention of the group refers to gas turbine engine containing the above fixed unit of blades.
EFFECT: group of inventions allows reducing weight of gas turbine engine blades unit.
12 cl, 10 dwg
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