| 摘要 |
<p>A fuel supply system for a gas turbine having a combustor comprises a first heat exchanger 200A, receiving fuel, suitably a gaseous fuel, from a source at a first temperature through a first fuel line 4 and providing fuel to the combustor at a second, preferably higher, temperature. A control valve 27A is provided in first fuel line 4 upstream of heat exchanger 200A to regulate the flow rate of fuel through first heat exchanger 200A, and a shut-off valve 28 is provided in first fuel line 4 upstream of control valve 27A to selectively stop fuel flow through first fuel line 4 to the combustor. Suitably, a second heat exchanger 200B and control valve 27B may be provided in parallel with first heat exchanger 200A, which may heat fuel to a third, different temperature. Suitably, the fuel system may be discharged without using pressure relief valves.</p> |
