INTERNAL COOLING OF GAS TURBINE ENGINE COMPONENTS

A gas turbine engine component (2), especially an aerofoil-sectioned nozzle guide vane (NGV), having at least one internal cooling chamber (130F) for passage therethrough of cooling air, the said chamber (103F) including a leading edge portion (80) and at least one inlet portion (90) via which cooli...

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Bibliographische Detailangaben
Hauptverfasser:	IRELAND, PETER, TIBBOTT, IAN, CRESCI, IRENE, RAWLINSON, ANTHONY
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION ENGINE PLANTS IN GENERAL GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS 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 TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine component (2), especially an aerofoil-sectioned nozzle guide vane (NGV), having at least one internal cooling chamber (130F) for passage therethrough of cooling air, the said chamber (103F) including a leading edge portion (80) and at least one inlet portion (90) via which cooling air may enter the chamber (103F) from a feed source (130a, 130b), wherein the component (2) comprises a partitioning element (100), e.g. a curved or scoop-shaped partitioning plate or wall, provided in at least the chamber inlet portion (90) and defining within at least the inlet portion (90) a sub-chamber (150) adjacent the leading edge portion (80), and wherein the partitioning element (100) is configured such that the cooling air velocity in the sub-chamber (150) is less than the cooling air velocity in the remainder (160) of the inlet portion (90). The reduction in velocity of the cooling air in the sub-chamber (150) adjacent the leading edge serves to increase the pressure therein, thereby maintaining a desired backflow pressure margin between the feed pressure of the cooling air delivered to the showerhead holes (20) and the gas-path from the combustor. Thus ingestion of hot gas into the component (NGV) can be better assured, leading e.g. to improved engine performance.