COMBUSTOR TRANSITION PART

PROBLEM TO BE SOLVED: To effectively cut a can-shaped combustor so as to avoid pulsation.SOLUTION: A combustor transition part 24 is adapted so as to guide combustion gas in a high temperature gas flow channel 15 extending between a can-shaped combustor and a first step of a turbine 3 in a gas turbi...

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Bibliographische Detailangaben
Hauptverfasser:	MICHAEL DUSING, MIRKO RUBEN BOTHIEN
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 ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION TECHNICAL SUBJECTS COVERED BY FORMER USPC TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To effectively cut a can-shaped combustor so as to avoid pulsation.SOLUTION: A combustor transition part 24 is adapted so as to guide combustion gas in a high temperature gas flow channel 15 extending between a can-shaped combustor and a first step of a turbine 3 in a gas turbine 9. The combustor transition part 24 includes a duct having: an inlet port that is provided at an upstream end part and is adapted for connection to the can-shaped combustor 2; and a downstream end part adapted for connection to the first step of the turbine 3. The combustor transition part has side wall extension parts 20, 20a and 20b in which at least one of side walls 21a and 21b extends in a downstream direction so as to project from an outlet port 22. The side wall extension parts 20, 20a and 20b at least partially enclose a first resonator volume 28, and at least one of the side wall extension parts 20, 20a and 20b has a resonator hole 26 constituted as the neck of a Helmholtz damper.