Cooled turbine vane assembly

A vane assembly (14) for a gas turbine engine (12) includes a plurality of vanes (28), each having a forward compartment (44) and an aft compartment (46), an inner vane support (30), a casing (16), and apparatus (50,54) for maintaining a pressure difference between the compartments. The casing (16),...

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Bibliographic Details
Main Authors PLANK, WILLIAM L, HALL, KENNETH B, SOECHTING, FRIEDRICH O
Format Patent
LanguageEnglish
French
German
Published 13.06.2001
Edition7
Subjects
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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Summary:A vane assembly (14) for a gas turbine engine (12) includes a plurality of vanes (28), each having a forward compartment (44) and an aft compartment (46), an inner vane support (30), a casing (16), and apparatus (50,54) for maintaining a pressure difference between the compartments. The casing (16), which includes an annulus (18), is positioned radially outside of the vanes. The vanes (28) extend between the inner vane support (30) and the casing (16). The apparatus for maintaining a pressure difference may comprise a flow meter (50,54) at the entrance to the aft compartment. A modulating valve (22) may be provided to control the flow of cooling air into the annulus, and thus into the vanes.
Bibliography:Application Number: EP19960307397