| 摘要 |
947,808. Gas turbine combustion chambers. ROLLS-ROYCE Ltd. July 27, 1962 [Aug. 3, 1961], No. 28322/61. Heading F1L. A combustion chamber for a gas turbine engine comprises a fuel injection nozzle mounted within the chamber and a fuel impingement member extending longitudinally therein such that the fuel from the nozzle is directed on to the upstream portion of the member, and means for directing combustion air to urge fuel downstream along the member to effect atomization of the fuel, deflector means being provided at the downstream end of the member for reducing the velocity of the fuel and deflecting it so that it leaves the member transversely. An annular combustion chamber has walls 15, 17 and dilution and cooling air ducts 19, 20 respectively. An annular manifold 24 having a supply pipe 25 feeds fuel to injection nozzles 26 extending into the combustion air duct 22. Each nozzle 26 is associated with a rectangular fuel impingement plate 27 mounted on the duct 22 by a strap 30 and having an open gutter 31 at its downstream end. Angularly spaced apart baffles 34 are mounted on either side of each impingement plate 27 to direct air past the plate 27 and urge the fuel downstream into the gutter 31. Dilution air enters the combustion chamber 13 through angularly spaced apart holes 23. Fuel is also supplied through two auxiliary atomizing nozzles 37 having igniters 40. |
