| 摘要 |
940,195. Gas turbines etc; combustion chambers. ROLLS-ROYCE Ltd. March 14, 1962. No. 9891/62. Heading F1L. A gas turbine engine has an engine casing in which the upstream end of a single annular flame tube is supported from the casing solely by a plurality of radially extending burner devices through which fuel may be supplied to the flame tube. An annular flame tube 17 having a frusto-conical portion 21 and an internal wall 22 is supported from the engine casing 11 at its upstream end solely by burners 32 passing freely through openings 33 in the portion 21, openings 34 in the wall 25, and holes in brackets 35 secured to the wall 22. Each burner 32 has main and pilot fuel paths leading to a discharge orifice 40 whose axis is at right angles to the longitudinal axis of the burner. The nozzle guide vanes 23 have apertures 24 through which air passes to passages 30, 31 for cabin pressurisation as described in Specification 932,000, |
