COOLING STRUCTURE FOR GAS TURBINE COMBUSTOR LINER

PURPOSE:To reduce the temperature of a liner wall by a method wherein the cooling of the liner wall is accelerated by increasing a liner wall-cooling calorie and increasing the flow-in quantity of cooling air to a cooling air hole as well. CONSTITUTION:Expanded heat transmission surface upstream end...

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Bibliographic Details
Main Author INNAMI TAMIO
Format Patent
LanguageEnglish
Published 22.12.1995
Edition6
Subjects
AIR
AIR INTAKES FOR JET-PROPULSION PLANTS
BLASTING
COMBUSTION APPARATUS
COMBUSTION ENGINES
COMBUSTION PROCESSES
CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
GAS-TURBINE PLANTS
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
LIGHTING
MECHANICAL ENGINEERING
METHODSOR APPARATUS FOR COMBUSTION USING FLUID FUELOR SOLID FUEL SUSPENDED IN
WEAPONS
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Summary:PURPOSE:To reduce the temperature of a liner wall by a method wherein the cooling of the liner wall is accelerated by increasing a liner wall-cooling calorie and increasing the flow-in quantity of cooling air to a cooling air hole as well. CONSTITUTION:Expanded heat transmission surface upstream ends 10 are provided to be close to cooling air holes 11, on the outer peripheral side of a liner 2. The expanded heat transmission surface upstream end 10 is provided in such a manner to be projected on a vertical surface of the cooling air hole 11. Then, cooling air hole jetting axes are provided to be tilted in the flowing direction of a combustion gas.
Bibliography:Application Number: JP19940130093