GB771890A - Improvements in or relating to electrical ignition systems of gas-turbine engines - Google Patents

Abstract

771,890. Ignition systems. ROLLS-ROYCE, Ltd. June 17, 1955 [June 24, 1954], No. 18599/54. Addition to 697,953. Class 7 (4). [Also in Group XXVI] In the ignition means described in the parent Specification the successively actuated igniters 19, Fig. 1, or groups thereof are the igniters of a number of gas-turbine engines. A power plant comprising sixteen continuous-combustion gas-turbine engines 1-16 arranged in four rows may be installed in an aircraft wing, not shown, to create a lift force for assisting take-off; each engine has two igniters 19 associated with its combustion equipment, which igniters are connected, as shown, to provide eight circuits AA-HH, each having four igniters in series, the circuits AA, CC, EE, GG and BB, DD, FF, HH being energized from ignition means 18 and 17 respectively. The means 17, 18 which are described in the parent Specification are caused to operate in unison by a coupling consisting alternatively of a resistance, a transformer with single-turn oppositely-wound coils or as shown in Fig. 4, a condenser 50 between points intermediate the spark gaps 36 and the ratchet-operated distributor arms 39 ; each igniter 19, Fig. 1, is energized once during each rotation of the distributor rotor arms 17a, 18a. In a modification, the power plant comprises four engines 20-23, Fig. 2, each with two igniters 20a-23a and 20b-23b connected as shown with ignition means 26 and 28, respectively. This arrangement may be applied to a power plant consisting of more than four engines and also to an arrangement as in Fig. 1, wherein the igniters are disposed in sets to be energized simultaneously. Each ignition device may embody a resistor having one end connected to earth and the other end connected to a point intermediate the spark gap and distributor rotor arm.