FIELD: engines.
SUBSTANCE: invention relates to the field of aviation propulsion engineering, namely, to turbine pedestals of gas turbine engines. The turbine pedestal of gas turbine engine consists of the turbine inner shell with bearing housing, connected by spokes, coming through the blades of nozzle diaphragm subassemblies, and turbine outer shell. Hollow supporting elements with external spherical surface are located at the internal shelves of the nozzle diaphragm subassemblies. Hollow supporting elements are hinge installed into the counter cylinder sleeves, arranged at the turbine inner shell. Power spokes come through the supporting elements and cylinder sleeves.
EFFECT: enhancing reliability of turbine pedestals of gas turbine engines; ensuring temperature isolation of turbine shells in a radial direction.
3 cl, 2 dwg
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