A cooling arrangement for a gas turbine

A gas turbine comprises an inner casing (3) and a rotor (1) having rotating blades (5) with a shroud (7) and a fin (8), and a cooling arrangement arranged in a cavity (9) in the casing (3) and about the rotating blade (5). According to the invention, the blade shroud (7) comprises a protrusion (12)...

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Bibliographic Details
Main Authors Kreiselmaier, Erich, Zambetti, Chiara, Wilhelm, Thomas
Format Patent
LanguageEnglish
French
German
Published 25.04.2018
Subjects
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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Summary:A gas turbine comprises an inner casing (3) and a rotor (1) having rotating blades (5) with a shroud (7) and a fin (8), and a cooling arrangement arranged in a cavity (9) in the casing (3) and about the rotating blade (5). According to the invention, the blade shroud (7) comprises a protrusion (12) extending away from the blade leading edge (te5) into the cavity (9) and openings (11') in the cavity wall (9a) for a cooling fluid. The protrusion (12) is defined by angles in relation to the flow channel wall (4'). The protrusion (12) effects a vortex flow of cooling fluid entering through the openings (11') and a vortex flow of hot gas entering from the flow channel (4) into the cavity (9). The double-vortex formation reduces a mixing of the cooling flow with the hot gas flow and increases the efficiency of the cooling arrangement of the blade shroud and cavity walls.
Bibliography:Application Number: EP20100164084