| 摘要 |
PROBLEM TO BE SOLVED: To change a target fuel flow by comparison of a rotor shaft speed with a pre-fill rotor speed of a gas turbine and detection of a filled status of fuel in a fuel line, in starting of the gas turbine. SOLUTION: A fuel control system for a gas turbine engine having a staged combustor includes apparatus and methods to operate the combustor during pilot operation, staged operation, and transition between the two modes of operation. A fuel control has a switch built in the hysteresis for determining a transition point between operating modes. The combustor is switched from pilot to staged operation at a thrust level greater than the thrust level at which the combustor is switched from pilot operation to staged operation. During transitions between operating modes, the changes in fuel flows are limited by a plurality of rate limits to prevent combustor fuel spikes and blow-outs from occurring. During engine starts, the fuel lines to the main combustor are pre-filled to provide responsiveness during the transition from the pilot operation to staged operation. COPYRIGHT: (C)2005,JPO&NCIPI
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