GB469180A - Improvements in or relating to turbines - Google Patents

Abstract

469,180. Gas turbines. OFFEN, A. Jan. 20, 1936, Nos. 1756 and 10015. [Class 110 (iii)] In a gas turbine of the type described in Specification 445,550, spherical combustion chambers, with inlet and exhaust openings on opposite sides thereof, are spaced angularly, around a rotor, which is driven by combustion products impinging on fixed reaction blading. The spherical chambers 32 are built up of two portions 36, 37 keyed to the shaft 26. Scavening air and explosion mixture are supplied to these chambers by ducts 29, 30, separated by a rib 28. A fuel atomizer 67 enters passage 30. As the rotor rotates, the chambers 32 come into line with the air duct 29 and exhaust 64, Figs. 10, 14, and scavenging takes place. Then the exhaust is closed by the stationary valve 34 and the chambers are charged with a mixture of air and fuel from duct 30. This is fired by a quantity of hot gases, regulated by rod 81, taken through flame tube 69 from the previously fired charge. The hot gases leave the chamber 32 by means of nozzles 60, impinge on fixed blading 63, then pass through moving blades 66 on to the exhaust 62. Scavenging is then again carried out and the cycle repeated. For starting purposes a plug 84 is used, a spark passing between electrode 90 and earthed cap 92. The clearances between the rotor and casing are maintained by placing around heated parts a liner 61 and inserts 85, 93, 94 capable of taking up differences ! of expansion. Heat from the rotor is prevented from reaching the bearings by the oil-cooled glands 106, 109. The cooling jackets fitted with an air release tank 53 are supplied through pipes 56, 57 (behind) with cooling water from a circulating pump.