FIELD: engines and pumps.
SUBSTANCE: proposed device for optimisation of radial clearances by compressed air bled from compressor comprises housing with blading. Compressed air flows successively through inner chambers of compressor stages. Rotor of every stage comprises multiple radial blades secured to the disc. This device comprises case fitted on the shaft under discs of at least three last stages, system of seals and slots between said discs and case, holes in said discs and case outlets. Device inlet communicates with compressor end area wherein cyclic loads at aircraft engine define maximum air heating. Seals, slots and holes are arranged to create loop-like airflows in said case from inlet along disc webs towards outlets, opposite the airflow direction in blading.
EFFECT: decreased thermal stress at rotor discs, minimized compressed air inner leaks by optimized radial clearances.
6 cl, 5 dwg
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