Kühlluft-Übertragungsvorrichtung

An inducer 44 comprising vanes 76 (Fig. 3) receives pressurized cooling air 36 from the engine compressor and directs it in a substantially tangential direction to a radial flow impeller 46 formed by radial passageways (58, Fig. 4) defined between walls 52,54. An air seal 48,50, is provided. Cooling...

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Bibliographische Detailangaben
Hauptverfasser:	BERTKE, JAMES HERMAN, CINCINNATI, OHIO, US, CORSMEIER, ROBERT JAMES, CINCINNATI, OHIO, US, REIGEL, JAMES ROBERT, CINCINNATI, OHIO, US, LENAHAN, DEAN THOMAS, CINCINNATI, OHIO, US
Format:	Patent
Sprache:	ger
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:	An inducer 44 comprising vanes 76 (Fig. 3) receives pressurized cooling air 36 from the engine compressor and directs it in a substantially tangential direction to a radial flow impeller 46 formed by radial passageways (58, Fig. 4) defined between walls 52,54. An air seal 48,50, is provided. Cooling air is directed to the turbine blades 24 which are mounted on the rim of the rotating first turbine disk 22. A second portion of the cooling air from the inducer may be conveyed through a deswirler 62 into a circumferential channel surrounding the rotor shaft. The cooling air is then directed to a second inducer means 66 (via holes 65) which is mounted on the higher pressure turbine disk 28. The cooling air is then directed to a second annular impeller 68 mounted on the lower pressure turbine disk 28 to convey this portion of cooling air to the lower pressure turbine rotor blades 30.