Gas Turbine Inlet Temperature Estimation via Dual Physical Models
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Solution Overview
Problem
Existing methods for estimating turbine inlet temperature in gas turbines face challenges in accuracy and responsiveness, particularly during transition periods, which affects the control accuracy of gas turbines.
Innovation Solution
A gas turbine control device that includes a first estimation unit using a physical model based on fuel flow rate, a second estimation unit using a physical model based on exhaust gas temperature, and a correction unit to calculate a turbine inlet temperature estimation value by correcting the first temperature using a correction coefficient determined from the ratio of the first and second temperatures.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a single physical model using fuel flow rate is used to estimate turbine inlet temperature, then responsiveness in transition period is ensured, but estimation accuracy is insufficient
Solution Approach 1:
The patent merges two different physical models: a fuel flow rate-based model (first model) that provides responsiveness, and an exhaust gas temperature-based model (second model) that provides accuracy. The correction unit combines these models by using the second model to correct the first model's output, achieving both responsiveness and estimation accuracy simultaneously.
2Measurement precision
If a single physical model using exhaust gas temperature is used to estimate turbine inlet temperature, then estimation accuracy is improved, but responsiveness in transition period deteriorates
Solution Approach 1:
The patent merges two different physical models: a fuel flow rate-based model (first model) that provides responsiveness, and an exhaust gas temperature-based model (second model) that provides accuracy. The correction unit combines these models by using the second model to correct the first model's output, achieving both responsiveness and estimation accuracy simultaneously.
3Measurement precision
If turbine inlet temperature is measured directly, then measurement accuracy would be high, but measurement becomes difficult due to high temperature at inlet
Solution Approach 1:
The patent uses exhaust gas temperature as an intermediary parameter to indirectly estimate turbine inlet temperature. Instead of directly measuring the difficult-to-access inlet temperature, the system measures exhaust gas temperature (which is easier to access) and uses it to correct the fuel flow rate-based estimation, thereby achieving accurate inlet temperature estimation without direct high-temperature measurement.
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
This approach ensures responsiveness and enhances the estimation accuracy of turbine inlet temperature, improving the control accuracy of gas turbines by combining fuel flow rate and exhaust gas temperature models for more precise temperature estimation.
Implementation Method 1
a first estimation unit configured to estimate a first temperature which is a turbine inlet temperature estimation value based on a first model which is a physical model using a fuel flow rate to a gas turbine
Implementation Method 2
a second estimation unit configured to estimate a second temperature which is a turbine inlet temperature estimation value based on a second model which is a physical model using an exhaust gas temperature of the gas turbine
Data Source
AI summary
A gas turbine control device includes a first estimation unit configured to estimate a first temperature which is a first turbine inlet temperature estimation value based on a first model which is a physical model using a fuel flow rate to a gas turbine; a second estimation unit configured to estimate a second temperature which is a second turbine inlet temperature estimation value based on a second model which is a physical model using an exhaust gas temperature of the gas turbine; and a correction unit configured to correct the first temperature based on the second temperature to calculate a third turbine inlet temperature estimation value.