TORCH IGNITER COOLING SYSTEM

An embodiment of a torch igniter (10) for a combustor of a gas turbine engine includes a combustion chamber (16) oriented about an axis, a cap (34) defining the axially upstream end of the combustion chamber and situated on the axis, a tip (30) defining the axially downstream end of the combustion c...

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Bibliographische Detailangaben
Hauptverfasser:	PROCIW, Lev Alexander, RYON, Jason
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS EXTINGUISHING-DEVICES GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS IGNITION LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	An embodiment of a torch igniter (10) for a combustor of a gas turbine engine includes a combustion chamber (16) oriented about an axis, a cap (34) defining the axially upstream end of the combustion chamber and situated on the axis, a tip (30) defining the axially downstream end of the combustion chamber (16), an igniter wall (38) extending from the cap to the tip and defining a radial extent of the combustion chamber, a structural wall (36) coaxial with and surrounding the igniter wall, an outlet passage (40) defined by the igniter wall within the tip, wherein the outlet passage fluidly connects the combustion chamber to the combustor of the gas turbine engine, and a cooling system. The cooling system has an air inlet, a cooling channel (28), and an aperture. The cooling channel (28) forms a flow path having a first axial section, a second axial section, a radially inward section, and a radially outward section.