Unified Gas Path Performance Analysis Method for Multiple Models of Gas Turbines Based on Modular Model

Abstract

The present invention discloses a unified gas path performance analysis method for multi - model gas turbines based on a modular model, including a modular model of gas turbine components, a unit and component type identification component, and a gas path iterative calculation component for gas turbines. The modular model of gas turbine components is provided with a compressor module, a turbine module, and a combustion chamber module, and the modular model of gas turbine components includes the definition of input and output interfaces for components such as compressors, turbines, and combustion chambers. The modular model of gas turbine components has built - in component performance calculation methods. This unified gas path performance analysis method for multi - model gas turbines based on a modular model can select different component coupling methods for gas path calculation according to different types of measurement points, so as to realize the evaluation of gas path states. In addition, this system can perform real - time monitoring and detection, evaluation, and provide corresponding basis for the control system, and can also carry out off - line monitoring management and the formulation of maintenance plans.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and specifically to a unified gas path performance analysis method for multiple models of gas turbines based on a modular model. Background Technique

[0002] As a widely used energy conversion device, a gas turbine plays an increasingly important role in fields such as aviation, power generation, and ground drive due to its low emissions, high reliability, and wide fuel adaptability. Its reliable, stable, and economical operation is very important for production and life. Achieving effective monitoring of the gas path state is an important issue in gas turbine management. With the continuous advancement of the informatization process, realizing the intelligent monitoring of the gas path state of gas turbines is of great significance for improving the management level of gas turbines.

[0003] However, there are various models of gas turbines, and there are problems such as different structures and different monitoring measurement points between different models of gas turbines. Traditional monitoring methods usually establish gas path calculation models for each type of gas turbine separately. As the number and types of gas turbines to be monitored increase, the types of gas path monitoring models will also continue to increase, making it difficult to simultaneously monitor the states of all gas turbines in a single computing environment, which is not conducive to the realization of the intelligent monitoring of gas turbines.

[0004] Through retrieval, it is found that Patent CN106525442B [P]: provides a method and device for detecting the gas path performance of a gas turbine, with insufficient compatibility, and can only perform performance analysis on a single type of gas turbine, which is not conducive to the promotion of intelligence. Summary of the Invention

[0005] The purpose of the present invention is to provide a unified gas path performance analysis method for multiple models of gas turbines based on a modular model to solve the problems of insufficient compatibility, only being able to perform performance analysis on a single type of gas turbine, and not being conducive to the promotion of intelligence proposed in the above background technique.

[0006] To achieve the above purpose, the present invention provides the following technical solution: A unified gas path performance analysis method for multiple models of gas turbines based on a modular model, including a modular model of gas turbine components, a unit and component type identification component, and a gas path iterative calculation component for gas turbines. The modular model of gas turbine components is provided with a compressor module, a turbine module, and a combustion chamber module, and the modular model of gas turbine components includes the definition of input and output interfaces for components such as compressors, turbines, and combustion chambers. The modular model of gas turbine components has built-in component performance calculation methods.

[0007] Furthermore, the unit and component type identification component realizes the identification of the gas turbine type and component type according to the input conditions of each module of multiple gas turbines of the same type, and then establishes the connection relationship between components according to the component coupling relationship.

[0008] Furthermore, on the basis of realizing component connection, the gas path iterative calculation component of the gas turbine establishes degradation factors for the compressor and turbine, and iteratively calculates the degradation factors through the conservation relationships of mass and energy during the operation of the gas turbine, effectively characterizing the health state of the gas path and providing a basis for the adjustability and convenience of the overall analysis method.

[0009] The unified gas path performance analysis method for multiple models of gas turbines based on modular models comprises the following steps:

[0010] S1: Establish a modular performance analysis model for the gas-driven compressor unit. According to the different types of units and available calculation parameters, select the coupling methods of the multi-stage compressor, turbine, and combustion chamber modules, and perform gas path performance analysis calculations for different models of units under a unified model, thereby effectively monitoring the gas path state;

[0011] S2: The modular models of the gas turbine components establish unified modules and their interfaces for the compressor, turbine, and combustion chamber. Based on different monitoring data, the unit and component type recognition method automatically selects different module coupling methods, and the gas path iterative calculation method of the gas turbine realizes the performance matching calculation of gas turbines with different coupling methods;

[0012] S3: Determine the input parameters and output parameters of each module in the component module model. The input parameters of the compressor module include inlet temperature, inlet pressure, outlet temperature, outlet pressure, and rotational speed, and the output parameters include compressor efficiency, flow rate, and power. The input parameters of the combustion chamber module include fuel flow rate, working medium flow rate, fuel enthalpy, fuel calorific value, and total pressure recovery coefficient, and the output parameters include combustion chamber outlet temperature and combustion chamber outlet pressure. The input parameters of the turbine module include inlet temperature, inlet pressure, outlet temperature, outlet pressure, and rotational speed, and the output parameters include turbine efficiency, flow rate, and power. The inlet temperature and pressure of the turbine module can be defaulted depending on the specific actual situation;

[0013] S4: Perform gas path performance analysis operations according to the input parameters and output parameters of each module in the component module model.

[0014] S5: Considering the actual situation of gas turbine monitoring, when monitoring the gas path state, consider the actual problem that it is difficult to perform calculations for different types of units under a unified model. Establish a unified gas path calculation model through a modular modeling method, which can intelligently identify the unit and component types according to the input data situation, and then establish the connection relationship between components according to the coupling relationship between components to perform corresponding performance calculations, realizing the intelligent monitoring of the gas turbine performance.

[0015] Compared with the prior art, the beneficial effects of the present invention are as follows: The unified gas path performance analysis method for multi-model gas turbines based on a modular model can select different component coupling methods for gas path calculation according to different types of measurement points, so as to realize the evaluation of the gas path state. Considering the actual situation of gas turbine monitoring, when performing gas path state monitoring, it takes into account the actual problem that different types of units are difficult to calculate under a unified model. By using a modular modeling method, a unified gas path calculation model is established, which can intelligently identify the unit and component types according to the input data situation, and then establish the connection relationship between components according to the coupling relationship between components for corresponding performance calculations. It can realize the intelligent monitoring of the performance of gas turbines, and is applicable to the gas path performance calculation and analysis of multi-type gas turbines equipped with sensors. For gas turbines in different fields and models, only the characteristics of modular components need to be changed to be embedded in the system calculation. For gas turbines in power fields such as transportation, aerospace, aviation, and navigation, this system can perform real-time monitoring and detection, evaluation, and provide corresponding basis for the control system, and can also carry out offline monitoring management and maintenance plan formulation. Specific Embodiments

[0016] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0017] The present invention provides a technical solution: A unified gas path performance analysis method for multi-model gas turbines based on a modular model, including a modular model of gas turbine components, a unit and component type identification component, and a gas path iterative calculation component of a gas turbine. The modular model of gas turbine components is provided with a compressor module, a turbine module, and a combustion chamber module, and the modular model of gas turbine components includes the input and output interface definitions of components such as compressors, turbines, and combustion chambers. The modular model of gas turbine components is built-in with component performance calculation methods.

[0018] Implementation process: First, establish a modular performance analysis model for the gas turbine-driven compressor unit. According to the different types of the unit and available calculation parameters, select the coupling method of multi-stage compressors, turbines, and combustion chamber modules to conduct gas path performance analysis and calculation for different models of the unit under a unified model, thereby effectively monitoring the gas path state. The modular model of the gas turbine components establishes unified modules and their interfaces for the compressor, turbine, and combustion chamber. The unit and component type identification method automatically selects different module coupling methods based on different monitoring data. The gas path iterative calculation method for the gas turbine realizes the performance matching calculation of gas turbines with different coupling methods. On the basis of realizing component connection, the gas path iterative calculation component of the gas turbine establishes the degradation factors for the compressor and turbine, and iteratively calculates the degradation factors through the conservation relationships of mass and energy during the operation of the gas turbine, effectively characterizing the health state of the gas path. Then, determine the input parameters and output parameters of each module in the component module model. Among them, the input parameters of the compressor module include inlet temperature, inlet pressure, outlet temperature, outlet pressure, and rotational speed, and the output parameters include compressor efficiency, flow rate, and power. The input parameters of the combustion chamber module include fuel flow rate, working medium flow rate, fuel enthalpy, fuel calorific value, and total pressure recovery coefficient, and the output parameters include the combustion chamber outlet temperature and combustion chamber outlet pressure. The input parameters of the turbine module include inlet temperature, inlet pressure, outlet temperature, outlet pressure, and rotational speed, and the output parameters include turbine efficiency, flow rate, and power. The inlet temperature and pressure of the turbine module can be defaulted according to the specific actual situation. According to the input parameters and output parameters of each module in the component module model, conduct gas path performance analysis operations. Finally, considering the actual situation of gas turbine monitoring, when conducting gas path state monitoring, consider the actual problem that it is difficult to calculate different types of units under a unified model. Through the modular modeling method, establish a unified gas path calculation model, which can intelligently identify the unit and component types according to the input data situation, and then establish the connection relationship between components according to the coupling relationship between components for corresponding performance calculations, realizing the intelligent monitoring of the gas turbine performance. The unit and component type identification component realizes the identification of the gas turbine type and component type according to the input conditions of each module of multiple same gas turbines, and then establishes the connection relationship between components according to the component coupling relationship.

[0019] Finally, it should be noted that the above content is only used to illustrate the technical solution of the present invention, rather than limiting the protection scope of the present invention. Any simple modification or equivalent replacement made by those of ordinary skill in the art to the technical solution of the present invention shall not depart from the essence and scope of the technical solution of the present invention.

Claims

1. A unified gas path performance analysis method for multi - model gas turbines based on a modular model, including a modular model of gas turbine components, a unit and component type identification component, and a gas path iterative calculation component for gas turbines. In the modular model of gas turbine components, there are a compressor module, a turbine module, and a combustion chamber module. The modular model of gas turbine components includes the definition of input and output interfaces for compressors, turbines, and combustion chamber components. The modular model of gas turbine components has built - in component performance calculation methods; The unit and component type identification component realizes the identification of gas turbine types and component types according to the input conditions of each module of multiple same gas turbines, and then establishes the connection relationship between components according to the component coupling relationship; Based on the realization of component connection, the gas path iterative calculation component for gas turbines establishes the degradation factors of the compressor and the turbine, and iteratively calculates the degradation factors through the conservation relationships of mass and energy during the operation of the gas turbine, effectively characterizing the health state of the gas path.

2. The unified gas path performance analysis method for multi - model gas turbines based on a modular model according to claim 1, and its steps are as follows: S1: Establish a modular performance analysis model for a gas - driven compressor unit. According to the different unit types and available calculation parameters, select the coupling methods of multi - stage compressors, turbines, and combustion chamber modules, and conduct gas path performance analysis and calculation for different - model units under a unified model, thereby effectively monitoring the gas path state; S2: The modular model of gas turbine components establishes unified modules and their interfaces for compressors, turbines, and combustion chambers. The unit and component type identification method automatically selects different module coupling methods based on different monitoring data. The gas path iterative calculation method for gas turbines realizes the performance matching calculation of gas turbines with different coupling methods; S3: Determine the input parameters and output parameters of each module in the component module model. The input parameters of the compressor module include inlet temperature, inlet pressure, outlet temperature, outlet pressure, and rotational speed. The output parameters include compressor efficiency, flow rate, and power. The input parameters of the combustion chamber module include fuel flow rate, working medium flow rate, fuel enthalpy, fuel calorific value, and total pressure recovery coefficient. The output parameters include combustion chamber outlet temperature and combustion chamber outlet pressure. The input parameters of the turbine module include inlet temperature, inlet pressure, outlet temperature, outlet pressure, and rotational speed. The output parameters include turbine efficiency, flow rate, and power. The inlet temperature and pressure of the turbine module can be defaulted depending on the specific actual situation; S4: Conduct gas path performance analysis operations according to the input parameters and output parameters of each module in the component module model; S5: Considering the actual situation of gas turbine monitoring, when conducting gas path state monitoring, consider the actual problem that different - type units are difficult to calculate under a unified model. Establish a unified gas path calculation model through a modular modeling method, which can intelligently identify the unit and component types according to the input data situation, and then establish the connection relationship between components according to the component coupling relationship for corresponding performance calculations, realizing the intelligent monitoring of gas turbine performance.