Liner for a gas turbine combustor

Liner for a gas turbine combustor

The invention concerns a sequential liner (10) for a gas turbine combustor, comprising a sequential liner outer wall (12) spaced apart from a sequential liner inner wall (22) to define a sequential liner cooling channel between the sequential liner outer wall (12) and the sequential liner inner wall...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: Maurer, Michael Thomas, De Jonge, Jeffrey, Meng, Patrik, Baumgartner, Felix
Format: Patent
Sprache:eng ; fre ; ger
Schlagworte:
BLASTING
COMBUSTION APPARATUS
COMBUSTION PROCESSES
ENGINE PLANTS IN GENERAL
GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
HEATING
LIGHTING
MACHINES OR ENGINES IN GENERAL
MECHANICAL ENGINEERING
NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES
STEAM ENGINES
WEAPONS
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Beschreibung
Zusammenfassung:The invention concerns a sequential liner (10) for a gas turbine combustor, comprising a sequential liner outer wall (12) spaced apart from a sequential liner inner wall (22) to define a sequential liner cooling channel between the sequential liner outer wall (12) and the sequential liner inner wall (22). The sequential liner outer wall (12) comprises a first face (14), a first adjacent face (16) and a second adjacent face (16), the first (16) and second (16) adjacent faces each being adjacent to the first face (14), the first face (14) of the sequential liner outer wall (12) comprising a first convective cooling hole (18) adjacent to the first adjacent face (16) and a second convective cooling hole (18) adjacent to the second adjacent face (16), each convective cooling hole (18) being arranged to direct a convective cooling flow into the sequential liner cooling channel adjacent to each adjacent face (16). The invention also concerns a method of cooling using the sequential liner (10) and a method of retrofitting a gas turbine.