Abstract: A fuel delivery system for delivering fuel to a gas turbine engine includes a fixed critical flow nozzle, a first fuel nozzle and a second fuel nozzle. The fixed critical flow nozzle and the variable critical flow nozzle are connected to a fuel source in parallel. The fixed critical flow nozzle has an orifice throat with a fixed effective cross-sectional area. The variable critical flow nozzle has an orifice throat with a variable effective cross-sectional area. The first fuel nozzle is connected to the fixed critical flow nozzle for delivering fuel to the gas turbine engine, and the second fuel nozzle is connected to the variable critical flow nozzle for delivering fuel to the gas turbine engine.

Abstract: A reheat burner arrangement including a center body, an annular duct with a cross-section area, an intermediate fuel injection plane located along the center body and being actively connected to the cross section area of the annular duct, wherein the center body is located upstream of a combustion chamber, wherein the structure of the reheat burner arrangement is defined by various parameters and the structure of the reheat burner arrangement is defined by various dependencies.

Abstract: A multi-energy system 9 including a gas heat pump type air conditioner 10 in which a compressor 16 equipped in an outdoor unit 11 is driven by a gas engine 25, and a power generating apparatus 30 having a power generator 31 which is driven by the gas engine 25 to output AC power, characterized in that the power generating apparatus 30 further includes an AC/DC converter 32 converter for converting AC power output from the power generator 31 to DC power, and a DC/AC converter 33 for converting the DC power thus obtained in the AC/DC converter 32 to AC power having a specified frequency and then outputting the AC power thus obtained to electric equipment.

Abstract: In a secondary burner for a gas turbine combustion chamber, a fuel feed (2, 3) arranged in a combustion chamber wall (1) is surrounded by an annular air duct (4). The air duct (4) communicates, by means of at least one supply tube (5), with a through-flow Helmholtz resonator (6). The outlet from the Helmholtz resonator damping tube (7), which is configured as an annular duct, is located in the region of the burner mouth (8) in the secondary combustion space (9).