Method for determining the fuel supply quantity during the start-up of a gas turbine
By dividing the fuel supply into two segments and introducing temperature and speed correction coefficients, the problem of poor adaptability between fuel supply and ambient temperature during gas turbine startup was solved, thereby improving combustion stability and startup reliability.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- WUXI BRACH 703TH RES INST OF CHINA SHIPBUILDING IND CORP
- Filing Date
- 2026-06-05
- Publication Date
- 2026-07-17
AI Technical Summary
During the startup process of existing gas turbines, the fuel supply is poorly adapted to the unit's thermal state and ambient temperature, leading to risks such as ignition failure, unstable combustion, overheating, and component damage.
The fuel supply is divided into two segments: a fixed ignition fuel supply segment and a speed-following fuel supply segment. The relationship between fuel flow and turbine back temperature is calibrated through incremental ignition tests. The unit's initial static temperature and atmospheric temperature correction coefficients are introduced for dynamic compensation. The high-pressure speed range is evenly divided into segments to establish a mapping relationship between equivalent speed and fuel flow. High-pressure speed closed-loop control is adopted.
It achieves precise matching of fuel supply with unit thermal state and ambient temperature, suppresses the risk of overheating, improves start-up reliability and operational safety, has good combustion stability, and reduces engineering implementation costs.
Smart Images
Figure CN122407376A_ABST