Method of supplying fuel into gas turbine combustor
A method is described for supplying a fuel for a gas turbine combustor of the type which introduces high pressure air and a fuel thereinto and combusts the fuel and air to generate a high temperature turbine operating gas, and which includes a first stage combustion chamber having a first stage fuel supply means and an air supply means each disposed upstream of the combustor, and a second stage combustion chamber having a second stage fuel supply means and an air supply means each disposed downstream of the first stage fuel supply means. The method consists of the steps of supplying the fuel only from the first stage fuel supply means to only operate the first stage combustion chamber from the start of operation of the gas turbine until the gas turbine combustor is in a low output range; and supplying in a step change such that a fuel flow rate changes more rapidly than in normal load control the fuel from the second stage fuel supply means to be at a predetermined flow rate and at the same time, decreasing in the step change substantially the same quantity of the fuel, that is being supplied from the first fuel supply means, when the second stage fuel is to be supplied and wherein the second stage fuel to be supplied in a step change into the second combustion chamber is excessively charged above a predetermined value for a short period of time and, at the same time, the first stage fuel to be decreased in the step change is excessively reduced below a predetermined value.
- Assignee:
- Hitachi, Ltd., Tokyo
- Patent Number(s):
- US 4603548
- OSTI ID:
- 5281005
- Country of Publication:
- United States
- Language:
- English
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