| 摘要 |
FIELD: igniting main combustion chambers of aircraft gas-turbine engines. ^ SUBSTANCE: proposed igniter has cylindrical body with air admission hole and inner space with partition and three chambers. First chamber accommodates electrical ignition plug, second one holds fuel injector, and third chamber communicates with two first ones and with radial outlet pipe connection. Air admission hole is made in body wall between injector nozzle and partition. Partition has hole providing communication between first and second chambers; volume of the latter is more than twice as large as that of first chamber and ratio of third chamber volume to total volume of two first chambers is lower than 2 and higher than . In addition oxidant inlet holes are provided in body wall of second chamber. Made in body wall of third chamber around radial pipe connection are holes disposed on same circumference, every next one having different diameter; ratio of total areas of holes of one diameter to those of other diameter is 2 to 2.5 and ratio of flow area of radial outlet pipe connection to total area of these holes is 8 to 9. ^ EFFECT: enlarged reliable ignition range of combustion chamber. ^ 3 cl, 1 dwg |
