Gas Turbine Control Device Transient Temperature Calculation
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Solution Overview
Problem
Existing gas turbine control methods face challenges in accurately calculating turbine inlet temperature during transient responses, leading to potential combustion oscillations and instability, especially when the output fluctuates.
Innovation Solution
A gas turbine control device and method that includes units for calculating fuel and air flow rates, turbine inlet temperature, and fuel distribution ratios using a physical model formula, with correction mechanisms based on exhaust gas temperatures, to ensure accurate and stable combustion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If turbine inlet temperature is calculated based on generator output and fuel command value, then calculation is simplified, but accuracy is degraded particularly during transient response
Solution Approach 1:
The patent segments the temperature calculation into multiple components: a first temperature calculated from heat balance data and a second temperature calculated from physical model formulas using measured values. These segmented calculations are then combined through weighted averaging, where the weight dynamically adjusts based on operating conditions. This segmentation allows each component to be optimized independently while maintaining overall accuracy.
Solution Approach 2:
The patent changes the calculation parameters dynamically based on operating conditions. During transient response, the system switches to using measured values (fuel flow rate, air flow rate) in physical model formulas with higher weight. During steady-state operation, it uses design-based heat balance data with higher weight. This parameter change strategy optimizes accuracy for each operational phase.
2Measurement precision
If corrected value is used to match gas turbine characteristics, then calculation accuracy improves, but device complexity and adjustment difficulty increase
Solution Approach 1:
The system performs self-adjustment by automatically determining the appropriate weight for measured values based on the relationship between calculated and measured exhaust gas temperatures. The correction mechanism uses feedback from temperature comparisons to dynamically adjust calculation parameters without requiring manual intervention or complex external correction systems.
Solution Approach 2:
The patent implements a feedback mechanism where the calculated exhaust gas temperature is compared with the measured exhaust gas temperature. Based on this comparison, the system adjusts the weight of measured values in the turbine inlet temperature calculation. This closed-loop feedback ensures continuous optimization of calculation accuracy without increasing structural complexity.
3Use of energy by moving object
If fuel distribution ratio is determined based on turbine inlet temperature from heat balance data, then combustion efficiency is maintained, but combustion oscillation risk increases
Solution Approach 1:
The patent applies dynamic calculation methods that adapt to changing operating conditions. Instead of using static heat balance data, the system dynamically calculates turbine inlet temperature using physical model formulas with measured values, particularly during transient response. This dynamic approach maintains both combustion efficiency and stability across varying operating conditions by continuously adjusting to current system state.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution enables precise calculation of turbine inlet temperature and fuel distribution ratios, even during transient responses, effectively suppressing combustion oscillations and ensuring stable combustion.
Implementation Method 1
a turbine inlet temperature calculation unit configured to calculate a turbine inlet temperature by inputting, in a physical model formula expressing a relationship of balance of thermal energy relating to a combustor of the gas turbine, the flow rate per unit time of the fuel, the flow rate per unit time of the air, a fuel temperature, and an air temperature
Implementation Method 2
The gas turbine control device described above may further include a correction unit configured to correct the turbine inlet temperature, based on a ratio of an exhaust gas temperature at the gas turbine and an exhaust gas temperature at the gas turbine calculated from the turbine inlet temperature
Data Source
AI summary
A flow rate per unit time of fuel fed to a gas turbine is calculated. A flow rate per unit time of air fed to the gas turbine is calculated. A turbine inlet temperature is calculated through use of a physical model formula expressing a relationship of input and output of thermal energy relating to a combustor of the gas turbine. A fuel distribution ratio for each of a plurality of fuel supply systems connected to the combustor is calculated based on the turbine inlet temperature.