COMBUSTOR LINER AND GAS TURBINE ENGINE ASSEMBLY

PROBLEM TO BE SOLVED: To provide a combustor liner excellent in efficacy of a cooling film, and to provide a gas turbine engine assembly.SOLUTION: The combustor liners (12, 14) include: a liner having an upstream end (60) a downstream end (62) having a longitudinal axis (11)extending therethrough; a...

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Bibliographische Detailangaben
Hauptverfasser:	SULEIMAN BAHA, VISE STEVEN CLAYTON, BROWN DANIEL DALE
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TOTRANSPORTATION COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS 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 HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION TECHNICAL SUBJECTS COVERED BY FORMER USPC 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:	PROBLEM TO BE SOLVED: To provide a combustor liner excellent in efficacy of a cooling film, and to provide a gas turbine engine assembly.SOLUTION: The combustor liners (12, 14) include: a liner having an upstream end (60) a downstream end (62) having a longitudinal axis (11)extending therethrough; and a plurality of cooling holes (44) formed in the liners, the cooling holes are arranged along the longitudinal axis into a plurality of circumferentially extending rows (46) that are variably spaced apart along the longitudinal axis. Moreover, the gas turbine assembly includes the combustion liners (12, 14).