SYSTEM FOR PROTECTING INNER WALL OF COMBUSTOR

PROBLEM TO BE SOLVED: To provide a combustor which is a thermal barrier coating spallation initiated effusion cooling system, an oxidation initiated effusion cooling system, or a combination thereof.SOLUTION: A gas turbine combustor 16 includes an inner wall disposed about a combustion chamber, and...

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Bibliographische Detailangaben
Hauptverfasser:	KYLE LEE KIDDER, JEROME D BROWN
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FORCOMBUSTION CHAMBERS, e.g. FIREBRIDGES COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDEDFOR DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS INCOMBUSTION CHAMBERS ENGINE PLANTS IN GENERAL 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 MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTIONAPPARATUS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To provide a combustor which is a thermal barrier coating spallation initiated effusion cooling system, an oxidation initiated effusion cooling system, or a combination thereof.SOLUTION: A gas turbine combustor 16 includes an inner wall disposed about a combustion chamber, and an outer wall disposed about the inner wall, where a coolant flow path extends between the inner and outer walls, where the inner wall comprises a material blocking a plurality of openings, and the plurality of openings are configured to open after the material is consumed or depleted to define a plurality of coolant passages through the inner wall.