Exhaust gas liner used for gas turbine, and gas turbine with the same

An exhaust gas liner (18) for a gas turbine comprises an annular inner shell (21) and an annular outer shell (19), which are arranged concentrically around a machine axis of said gas turbine to define an annular exhaust gas channel in between, whereby said inner shell (21) and/or said outer shell (1...

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Bibliographische Detailangaben
Hauptverfasser:	MLADEN MATAN, JUERGEN PACHOLLECK, MIRJANA MIHELIC, PEDJA MILANKOVIC, IGOR MIHALIC, CHRISTIAN JOERG KREUTLE
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION ENGINES 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 HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	An exhaust gas liner (18) for a gas turbine comprises an annular inner shell (21) and an annular outer shell (19), which are arranged concentrically around a machine axis of said gas turbine to define an annular exhaust gas channel in between, whereby said inner shell (21) and/or said outer shell (19) are composed of a plurality of liner segments (22, 23; 26, 27; 28), which are attached to a support structure. To compensate thermal expansion and achieving resistance against dynamic loads said liner segments (22, 23; 26, 27; 28) are fixed to said support structure at certain fixation spots (29a-c; 30a-c), which are distributed over the area of said liner segments (22, 23; 26, 27; 28), such that said liner segments (22, 23; 26, 27; 28) are clamped to said support structure through a whole engine thermal cycle without hindering thermal expansion.