COMBUSTION DEVICE AND GAS TURBINE ENGINE SYSTEM
FIG1 is a block diagram showing an overall constitution of a gas turbine engine system according to an embodiment of the present disclosure
FIG1 is a block diagram showing an overall constitution of a gas turbine engine system 1 according to the embodiment. As shown in the drawing, the gas turbine engine system 1 according to the embodiment includes a gas turbine engine 2, a fuel ammonia supply system 3, a natural gas supply system 4, a reduction catalyst chamber 5 (a denitration device), an intercooler 6 (a combustion air cooling unit), and a cooling water supply system 7. Further, in the embodiment, a compressor 2a of the gas turbine engine 2 which will be described later, the fuel ammonia supply system 3, the natural gas supply system 4, the intercooler 6 (the combustion air cooling unit), and the cooling water supply system 7 constitute a combustion device of the present disclosure. The gas turbine engine system 1 is a drive source of a generator G and generates rotational power by burning fuel ammonia using compressed combustion air. As shown in FIG1, the pipe 3b of the fuel ammonia supply system 3 is connected to the ammonia supply unit 3a and the combustor 2b, and includes a first path which guides the fuel ammonia to the combustor 2b via the vaporizer 3d, and a second path which guides the fuel ammonia to the combustor 2b via the intercooler 6 without passing through the vaporizer 3d. Further, the pipe 3b also includes a third path which branches from the first path which guides the fuel ammonia to the combustor 2b via the vaporizer 3d, and guides the fuel ammonia to an exhaust gas pipe located on the upstream side of the reduction catalyst chamber 5.
block diagram
8
heat exchanger
3
fuel ammonia supply system
1
gas turbine engine system
['7. A gas turbine engine system comprising the combustion device according to any one of claims 1 to']