Aperture insert for the combustion chamber of a gas turbine

An air admisstion insert (40) particularly adapted for air admission holes (25) in a combustor liner (15) in a gas turbine combustion system, comprises a pair of sleeve members, one of which (42) is inserted in the other in axial but eccentric relationship so that the sides of the sleeves contact ea...

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Bibliographische Detailangaben
Hauptverfasser:	RASMUSSEN, NEIL SIDNEY, ABUAF, NESIM, SZEMA, LIIEH
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING BURNERS COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	An air admisstion insert (40) particularly adapted for air admission holes (25) in a combustor liner (15) in a gas turbine combustion system, comprises a pair of sleeve members, one of which (42) is inserted in the other in axial but eccentric relationship so that the sides of the sleeves contact each other, with the intervening space (46) between the sleeves being crescent shaped. The insert is positioned concentrically in a combustor liner air admission hole. Combustion air flows through the insert and into the combustor liner and axially through the crescent space to cool the insert as well as the liner hole perimeter.