GAS TURBINE ENGINE WITH A COOLED NOZZLE SEGMENT

An apparatus and method of cooling a hot portion of a gas turbine engine within a nozzle segment (100) comprising an outer and inner band (116) and at least one vane (72) extending between the outer and inner band (116). The outer band (118) includes a forward and aft cavity (136). The apparatus com...

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Bibliographische Detailangaben
Hauptverfasser:	DEMERS, Daniel Edward, CORREIA, Victor Hugo Silva, HOOPER, Tyler Frederick, HERNANDEZ, Wilhelm R. Ramon
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL 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:	An apparatus and method of cooling a hot portion of a gas turbine engine within a nozzle segment (100) comprising an outer and inner band (116) and at least one vane (72) extending between the outer and inner band (116). The outer band (118) includes a forward and aft cavity (136). The apparatus comprises a forward impingement baffle (138) located within the forward cavity (134) comprising a forward cooling chamber (148) and an aft impingement baffle (140) located within the aft cavity (136) comprising an aft cooling air chamber (152). Cooling air (A) introduced into the forward cooling air chamber (148) passes through impingement holes (146) of the forward impingement baffle (138) into a forward impingement chamber (150) then passes through an aperture to the aft cooling air chamber (152), and then passes through the impingement holes (146) of the aft impingement baffle (140) into an aft impingement chamber (143).