| 摘要 |
802,703. Electric igniters. BENDIX AVIATION CORPORATION. April 9, 1956 [April 11, 1955], No. 10769/56. Class 75(3) In combustion apparatus comprising a combustion chamber 4, means at one end of the chamber for introducing air and a conical spray of fuel into the chamber, and an electric igniter 12 projecting into the chamber, the igniter extends into the outer part of the conical fuel spray and comprises electrodes 34 and inner and outer spaced open-ended baffles 15, 24 coaxially surrounding and extending beyond the electrodes 34, the inner baffle 15 having a ring of openings 19 near the ends of the electrodes and the outer baffle 24 having a series of openings 29 near the openings 19 of the inner baffle. The openings 29 in the outer baffle are larger than the openings 19 of the inner baffle and are arranged in two staggered rows. The free edge of the outer baffle is inclined to provide a short wall 32 on the side nearer the fuel nozzle 9 and a long wall 31 on the side farther from the fuel nozzle 9. The short wall terminates short of and the long wall terminates beyond the free edge of the inner baffle. The inner baffle has a large hole 21 near the long wall of the outer baffle. The electrodes are mounted on a plug 35 screwed into the upper part of the inner baffle. The igniter is secured in a collar 37 in an aperture in the conical wall 5 of the combustion chamber by a nut 39 received in the collar 37 and threaded on to the upper part of the inner baffle. A flange 18 on the inner baffle clamps a flange 25 on the upper end of the outer baffle against the. collar 37 and splines on the inner baffle engage in splineways in the flange 25 and in the collar 37. The fuel nozzle 9 is mounted on a plate 7 closing the narrow end of the combustion chamber and projects axially thereinto. A plurality of air openings 8 are provided in the plate 7 around the fuel nozzle. The wider end of the combustion chamber is closed by a head 3 having nozzles 2 for directing combustion gases on to the blades of an axial flow type turbine 1 for operating the starter mechanism of a jet aircraft engine.
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