Improvements in or relating to Gas Turbine Engines

1,194,684. Gas turbine combustion chambers. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. June 30, 1967 [July 8, 1966], No.30388/67. Heading F1L. The air delivered by a compressor 1 to a flame tube 2 is divided adjacent the upstream end of the flame tube into two streams...

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Bibliographische Detailangaben
Hauptverfasser:	JACQUES EMILE JULES CARUEL, HARVE ALAIN QUILLEVERE
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 USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINSTCLIMATE CHANGE WEAPONS
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Zusammenfassung:	1,194,684. Gas turbine combustion chambers. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. June 30, 1967 [July 8, 1966], No.30388/67. Heading F1L. The air delivered by a compressor 1 to a flame tube 2 is divided adjacent the upstream end of the flame tube into two streams, a first stream providing combustion and dilution air and a second stream providing cooling and insulating air films. The first air stream is supplied to the flame tube 2 through nozzles 7, 71 at a higher pressure than the second air stream passing through openings 8, 9, 91 by passing the first air stream through a supplementary compressor stage 5 or by passing the second air stream through a throttling plate (10), Fig. 2 (not shown), or plates (10a, 10b), Fig. 3 (not shown).