GB432652A - Improved constant pressure gas turbine plant - Google Patents

Abstract

432,652. Gas turbines. AKTIEBOLAGET MILO, 32, Kungsgatan, Stockholm. Feb. 9, 1934, No. 4365. Convention date, Feb. 10, 1933. [Class 110 (iii)] A constant-pressure gas turbine for use with gases having an inlet temperature of at least 800‹ C., is formed as an axial-flow turbine with full admission, the blades of the turbine being fastened to a conical drum or to discs the diameter of which increases, from the turbine inlet towards the outlet and the length of the blades also increasing towards the outlet, the blade length on the inlet amounting to at least 10 per cent, preferably 15 per cent to 20 per cent of the average blade diameter. The turbine casing 25, which is stepped and undivided, is surrounded by an air-jacketed combustion chamber 8, and has arms 32 which are connected to the casing of the direct-driven air compressor A by bolts 54. The charge air on its way to the combustion chamber 8 passes around all sides of the chamber and cooling and preheating effects are thereby secured. Compressed air passes also to the main bearing 5 and prevents leakage of combustion products thereto. A modified arrangement of turbine is described. The shaft is hollow and may be heated by leakage gases passing through channels at the bases of the discs, or by introducing leakage gases into the centre by holes 98, Fig. 6. The blades are fixed by welding, as at 40<1>, 40<11>, and blade tip shrouding such as 105, 119, is provided. The blade-carrying discs 140, Fig. 9 may be welded together at 142 to form the rotor. The exhaust of the turbine may be used to exert a propulsive effect. An arrangement in which water is injected into the compressed air and into the combustion chamber is described.