GAS TURBINE ENGINE AND ITS COMBUSTOR

PROBLEM TO BE SOLVED: To provide a combustor 16 for a gas turbine engine 10. SOLUTION: The combustor comprises an outside combustor liner 32 defining at least a part of a combustion chamber 30. The outside combustor liner 32 has a first end 34 radially extended to define a combustion chamber input o...

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Hauptverfasser:	LOHMUELLER STEVEN J, BURRUS DAVID L, MANCINI ALFRED A
Format:	Patent
Sprache:	eng
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 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 16 for a gas turbine engine 10. SOLUTION: The combustor comprises an outside combustor liner 32 defining at least a part of a combustion chamber 30. The outside combustor liner 32 has a first end 34 radially extended to define a combustion chamber input opening, and a second end 38 axially extended to define an output opening of the combustion chamber. The first end shifts to the second end to define the circular arc shaped cross section of the combustor liner. The combustor comprises a dome assembly 50 connected to the first end extending downstream of the dome assembly, and the dome assembly 50 comprises a cyclone 120 having a plurality of cyclone stator blades 122 arranged around the cyclone. The combustor comprises fuel nozzles 64 arranged within a range of the cyclone of radial constitution. COPYRIGHT: (C)2007,JPO&INPIT