Wall elements for gas turbine engine combustors

The invention relates to a wall element (60A-G) for a wall structure of a gas turbine engine combustor (15). The wall element has an inner, in use, hot surface (32), and an outer, in use, cooler surface (41). A plurality of projections (40) is provided on the outer surface (41) to facilitate heat tr...

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Bibliographische Detailangaben
Hauptverfasser:	MILLS, STEPHEN JOHN, WOOLFORD, JAMES RICHARD, WHITE, KEVIN ANDREW
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION APPARATUS COMBUSTION PROCESSES GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING 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:	The invention relates to a wall element (60A-G) for a wall structure of a gas turbine engine combustor (15). The wall element has an inner, in use, hot surface (32), and an outer, in use, cooler surface (41). A plurality of projections (40) is provided on the outer surface (41) to facilitate heat transfer to a coolant flow. The wall element (60A-G) comprises a means (64-64G) to direct more coolant flow at a hot-spot on an adjacent tile (60B) than the remainder of the adjacent tile (60B) and thereby reducing the thermal gradient across the adjacent tile (60B).