Gas turbine engine component

A gas turbine engine component such as a high pressure turbine nozzle guide vane (NGV) or blade includes an external wall which is exposed to hot gas flowing through the engine. The component includes an air inlet arrangement 42 and effusion (film) cooling holes 46 formed in the external wall. Air i...

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Bibliographische Detailangaben
Hauptverfasser:	ANTHONY JOHN RAWLINSON, PETER IRELAND, IAN TIBBOTT
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 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:	A gas turbine engine component such as a high pressure turbine nozzle guide vane (NGV) or blade includes an external wall which is exposed to hot gas flowing through the engine. The component includes an air inlet arrangement 42 and effusion (film) cooling holes 46 formed in the external wall. Air is supplied from the inlet arrangement 42 via metering / impingement holes 45 to supply plena 43, 44. The plena 43, 44 supply air to the film cooling holes 46. Cooling air flowing through metering holes 45 impinges on the inner surface of the outer wall to enhance heat transfer. Each plenum 43, 44 is supplied by only one or two metering holes, and supplies only one or two effusion cooling holes 46. This allows flow rates to be accurately matched to cooling requirements at each point on the blade surface.