MULTISTAGE GAS TURBINE

FIELD: multistage gas turbine of aircraft and ground application. ^ SUBSTANCE: according to invention, in multistage gas turbine with higher pressure relief chamber at outlet limited over periphery by labyrinth seal, said seal is made multistage, air space between first and second side from relief c...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	JAZEV V.M, SYCHEV V.K, LATYSHEV V.G, KUZNETSOV V.A, BELKANOV V.A, FADEEV S.I
Format:	Patent
Sprache:	eng ; rus
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	FIELD: multistage gas turbine of aircraft and ground application. ^ SUBSTANCE: according to invention, in multistage gas turbine with higher pressure relief chamber at outlet limited over periphery by labyrinth seal, said seal is made multistage, air space between first and second side from relief chamber stages of labyrinth seal is connected with gas chamber before last disk of turbine by channels made under feed of locks of working blades of last stage and slot spaces between ring flange on rim of disk of last stage and rim of disk from side of inlet in direction of gas flow at F1/F2=3...10 where F1 is passage area of first stage of labyrinth seal, and F2 is area of slot spaces. ^ EFFECT: improved reliability of multistage gas turbine owing to provision of effective cooling of last stage disk rim and disk-to-working blade lock joint. ^ 2 dwg