GB1059876A - Combustion equipment - Google Patents

Abstract

1,059,876. Pressure exchangers; gas turbine engines. ROLLS-ROYCE Ltd. Dec. 31, 1965 [Jan. 13, 1965], No. 1587/65. Headings F1G and F1N. Combustion equipment, Fig. 2 (not shown) for a gas turbine comprises an annular combustion chamber 22 or an annular array of combustion chambers which communicate through circumferentially spaced inlet and outlet ports 24, 25 with the cells 28 of a pressure exchanger having inlet ports 32 and outlet ports 33. The inlet ports 32 are connected by ducts 40 to the outlet of the highpressure air compressor of the turbine and the outlet ports 33 are connected by ducts 41 to the intake of a high pressure turbine. The turbine is arranged to drive the pressure exchanger cell ring and the high pressure compressor. In operation the air from the compressor enters the cells 28 and is compressed by high pressure gas admitted through the outlet ports 25 from the combustion chamber or chambers. Some of the resulting high pressure gas in the cells 28 returns to the chamber(s) 22 through inlet ports 24 while much of the remaining gas moves on and is discharged through the ports 33 The chamber inlet and outlet ports 24, 25 may be formed in the radially inner or outer walls of the combustion chamber(s). In a modification, Fig. 2a (not shown) ducts 45, 46 provide communications between the chamber(s) 22 and inlet and outlet ducts 24, 25 in the end walls of the pressure exchanger. Part of the gas which passes to the chamber(s) from the cells 28 may flow around the combustion chamber(s) 22 to mix and thereby dilute the combustion gases, which return to the cells 28. Instead of driving a turbine the exhausted gases may be directed through a propelling nozzle or alternatively the pressure exchanger may be driven by the gases.