TRANSITION MULTI-HOLE COMBUSTOR LINER

PROBLEM TO BE SOLVED: To suppress the occurrence of breakage due to a thermal fatigue crack and to improve durability of a combustor, in the inner cylinder of a gas turbine, in particular a multi-hole combustor liner. SOLUTION: A combustor liner 20 comprises an outer surface 40; and a wall 20a havin...

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Hauptverfasser:	DUNCAN BEVERLY STEPHENSON, WIEHE GLENN EDWARD, BURNS CRAIG PATRICK, THOMSON JAMES EDWARD
Format:	Patent
Sprache:	eng
Schlagworte:	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 WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To suppress the occurrence of breakage due to a thermal fatigue crack and to improve durability of a combustor, in the inner cylinder of a gas turbine, in particular a multi-hole combustor liner. SOLUTION: A combustor liner 20 comprises an outer surface 40; and a wall 20a having an inner surface 42 opposite to the outside surface. A plurality of first holes 44 are formed in a multi-hole pattern and inclined and extended through the wall 20a. Through a flow of cooling air 16 through the holes, a cooling film layer 16b is formed along the inner surface. A second hole 46 is extended, in a multi-hole pattern, vertically through the wall 20a and a notched shade 48 of the first hole is formed along an inner surface. Transition holes 50 are extended in an inclining state through the wall 20a at inclination higher than that of the first hole and the wall 20a is cooled at the shadow 48.