GAS TURBINE COMBUSTOR HAVING LINER COOLING GUIDE VANES

The present disclosure is directed to a combustor having an annularly shaped liner that at least partially defines a hot gas path of the combustor. A flow sleeve (54) circumferentially surrounds at least a portion of the liner. The flow sleeve (54) is radially spaced from the liner to form a cooling...

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Bibliographische Detailangaben
Hauptverfasser:	GODFREY, Andrew Grady, PORZIO, David Philip, CIHLAR, David William, WILLIS, Christopher Paul
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING 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:	The present disclosure is directed to a combustor having an annularly shaped liner that at least partially defines a hot gas path of the combustor. A flow sleeve (54) circumferentially surrounds at least a portion of the liner. The flow sleeve (54) is radially spaced from the liner to form a cooling flow annulus (56) there-between. A bluff body extends radially between the flow sleeve (54) and the liner through the cooling flow annulus (56). A guide vane (68) is disposed within the cooling flow annulus (56) and extends between the flow sleeve (54) and the liner downstream and proximate to the bluff body.