Impingement-cooled integral turbine rotor

Impingement-cooled integral turbine rotor

An integral turbine rotor (20, 120) includes a forward hub section (56, 156) and an aft hub section (60, 160). The forward hub section and the aft hub section are metallurgically coupled to one another along an annular interface (54, 157) that resides within a plane generally orthogonal to a rotatio...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: MINER, Amandine, JAN, David K
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
BLASTING
ENGINE PLANTS IN GENERAL
HEATING
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 integral turbine rotor (20, 120) includes a forward hub section (56, 156) and an aft hub section (60, 160). The forward hub section and the aft hub section are metallurgically coupled to one another along an annular interface (54, 157) that resides within a plane generally orthogonal to a rotational axis (26) of the axially-split turbine. The turbine further includes an airfoil blade ring metallurgically coupled to a radial outer surface of the coupled forward and aft hub sections and an impingement cavity (68b, 70b, 168b, 170b) formed within an interior portion of the coupled forward and aft hub sections. The impingement cavity includes an interior surface (75, 175) that is positioned proximate to the radial outer surface of the coupled forward and aft hub sections. Further, an impingement cooling air flow (88, 188) impinges against the interior surface of the impingement cavity to provide convective and conductive cooling to the radial outer surface of the coupled forward and aft hub sections.