GB624273A - Improvements in or relating to compressor systems - Google Patents

Abstract

624,273. Axial-flow compressors; elasticfluid turbines. FLETCHER, A. H. June 24, 1947, No. 16698. [Classes 110(i) and 110(iii)] A compressor and one or more aircoolers are incorporated in a unitary structure which includes a chamber surrounding the compressor, whence air passes to the cooler at low velocity, and a diffuser connecting the compressor outlet and the surrounding chamber. The arrangement is particularly suitable for the low-pressure compressor in gas turbine plant, and the structure may incorporate combustion chambers for reheating the exhaust gases from the high-pressure unit before they enter the turbine driving the compressor in question. In the embodiment shown, a diffuser 20 is arranged as an extension of an axial-flow compressor 10 driven by a turbine 12, and discharges into a chamber 36 formed by an additional casing 21 surrounding the compressor and the outer wall of the diffuser, this chamber communicating at 26 with an intercooler 14 at each side; guide vanes 37 are placed in the diffuser outlet. Combustion chambers 15 for heating the gas entering the turbine 12 are located between and above the intercoolers, and all the members are connected by a structure 24 which incorporates the turbine inlet and carries end doors for the intercoolers and combustion chambers, the doors for the latter serving to locate the nozzles 32 of the flame tubes by means of spigots 33 thereon. The casing 21 is slidably mounted on the inlet end of the compressor, to allow for differential expansion, and the air in the chamber 36 is insulated from that in the compressor inlet 16 by lagging the compressor casing or forming the latter as a double-walled structure through which coolant is circulated, differential expansion between the compressor casing and rotor being thus minimised.