GB1174694A - Improvements in or relating to Rotary Engines - Google Patents

Abstract

1,174,694. Gas turbine plant; turbines. T.W. ANDREW and J.D. YANDLE. Nov.5, 1968 [Jan.24, 1968], No.3777/68. Addition to 1,156,441. Headings F1G and F1T. In a modification of the rotary engine claimed in Specification 1,156,441, the combustion chamber 1 is offset laterally from the vertical plane through the axis of the rotor disc 3 and the disc is provided with axially spaced depressions 13, 17 forming first and second expansion stages, respectively. Ignition of the fuel/air mixture in the combustion chamber 1 is effected when a depression 12 in the disc 3 moves into alignment with the outlet port 10 of the chamber so that the disc 3 receives a driving pulse in the anti-clockwise direction. As the disc 3 rotates, the depression 13 moves into communication with port 10 to receive a further driving pulse. The leading edge of depression 13 then moves into communication with a port 14 in the stator casing 2 so that some of the gas leaves depression 13 and flows through port 14 and a passage 15 to enter the second stage depression 17 in the disc 3 through a port 16. When depression 13 moves out of alignment with port 10 a further depression 18 moves into communication with the latter and connects same with port 14 so that a blast of scavenging air supplied to the combustion chamber 1 flows through port 10 and depression 18 to scavenge both depressions 13 and 17 before leaving through an exhaust port 19 to complete the cycle. Depression 17 may be provided with a series of curved vanes 21 to assist impingement of the driving gases. The sealing ring 9 at the periphery of disc 3 and the remainder of the engine are substantially as described in the parent Specification.