Combustor liner cooling system

A gas turbine engine combustor cooling system for imperforate non-metallic combustor liners has a wall positioned adjacent to the liners forming therewith a cavity. The wall has a plurality of inlets for admitting cooling air into the cavity and a plurality of outlets for exhausting the cooling air...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	HALILA, ELY E, FOLTZ, HOWARD L
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FORCOMBUSTION CHAMBERS, e.g. FIREBRIDGES COMBUSTION APPARATUS COMBUSTION PROCESSES DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDEDFOR DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS INCOMBUSTION CHAMBERS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTIONAPPARATUS WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine combustor cooling system for imperforate non-metallic combustor liners has a wall positioned adjacent to the liners forming therewith a cavity. The wall has a plurality of inlets for admitting cooling air into the cavity and a plurality of outlets for exhausting the cooling air into a separate passageway after it impinges the liners. The exhausted cooling air is transferred upstream of the liner where it is combined with fuel for burning rather than discharged downstream as cooling film.