FIELD: engines and pumps.
SUBSTANCE: proposed system comprises radial-flow compressor feeing ring combustion chamber via diffuser, ring compartment arranged axially from diffuser to zone adjoining combustion chamber outlet and diffuser flange rear end. Diffuser ring flange features, in fact, L-like cross-section and is located behind and along radial-flow compressor impeller to form radial annular airflow channel communicated with compressor outlet via its radially outer end. Ring compartment is located radially between combustion chamber and diffuser flange. Note here that said compartment has radially outward ring wall to direct airflow from diffuser along radially inner wall of combustion chamber and radially inner ring wall to constrict ring air passage together with diffuser flange.
EFFECT: better ventilation, higher operating performances of gas turbine engine.
14 cl, 2 dwg
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