A ship gas turbine overall performance model modeling method based on a sysblock platform

Abstract

The purpose of this invention is to provide a modeling method for the overall performance of marine gas turbines based on the Sysblock platform, belonging to the field of gas turbines. The method includes the following steps: modular decomposition of the gas turbine system; construction of low-pressure and high-pressure compressor models based on Sysblock according to compressor performance calculation principles and similarity theory; establishment of a combustion chamber model based on Sysblock according to combustion chamber thermodynamic performance calculation principles; construction of high-pressure, low-pressure, and power turbine models based on Sysblock according to turbine performance calculation principles and similarity theory; construction of cavity and rotor models based on Sysblock respectively; and connection of the constructed models according to the actual topology to achieve integration of the overall performance model of the gas turbine. This invention fundamentally solves the problem of efficient and high-precision integration of heterogeneous models from multiple fields on a unified platform. Simultaneously, it is compatible with existing model migration paths and provides a lossless conversion tool for SLX models, which can automatically migrate historical Simulink models to the Sysblock platform.

Description

Technical Field

[0001] The present invention relates to a gas turbine simulation method, specifically a marine gas turbine simulation method. Background Technology

[0002] The overall performance model of a gas turbine is a crucial foundation for the design of marine propulsion systems. Its modeling accuracy and co-simulation capabilities directly determine the feasibility and optimization potential of the overall system design. Currently, the main methods for overall performance modeling of gas turbines face technical bottlenecks: Traditional overall performance models are often built using a single tool (such as Simulink), and their accuracy is limited by simplification assumptions. For example, the flow efficiency characteristics of components such as compressors and turbines in Simulink are often interpolated using empirical characteristics, which makes it difficult to reflect the actual aerodynamic parameters and their dynamic coupling effects.

[0003] Furthermore, if detailed modeling of the various components and system models of a gas turbine is performed, a highly heterogeneous development platform and language problem arises. For example, the compressor aerodynamic performance model is built using Fortran; the turbine aerodynamic performance model is built using Python; the fuel system simulation platform is Amesim software; and the air system calculation program is written in Fortran. These heterogeneous models are difficult to integrate on a unified platform due to incompatibility in data formats, solution step sizes, and dimensional systems. Moreover, Simulink models lack the ability to collaboratively solve multi-physics fields, and have limited capabilities for unified modeling and collaborative solving of physical phenomena and their strong coupling relationships across multiple fields such as mechanics, thermodynamics, fluid dynamics, and control, making it difficult to achieve high-precision dynamic coupling simulation at the system level. Summary of the Invention

[0004] The purpose of this invention is to provide a modeling method for the overall performance model of a ship gas turbine based on the Sysblock platform, which can solve the problem of collaborative simulation of multi-source heterogeneous models.

[0005] The objective of this invention is achieved as follows: This invention discloses a method for modeling the overall performance of a marine gas turbine based on the Sysblock platform, characterized by the following steps: (1) Modular decomposition of the gas turbine system: The gas turbine body is decomposed into a low-pressure compressor model, a high-pressure compressor model, a combustion chamber model, a high-pressure turbine model, a low-pressure turbine model, a power turbine model, a cavity model, and a rotor model; (2) Based on the compressor performance calculation principle and similarity theory, construct low-pressure compressor and high-pressure compressor models based on Sysblock; (3) Based on the calculation principle of combustion chamber thermodynamic performance, establish a combustion chamber model based on Sysblock; (4) Based on the turbine performance calculation principle and similarity theory, construct high-pressure turbine, low-pressure turbine and power turbine models based on Sysblock; (5) Construct cavity and rotor models based on Sysblock respectively; (6) Based on the actual topology, connect the constructed low-pressure compressor model, high-pressure compressor model, combustion chamber model, high-pressure turbine model, low-pressure turbine model, power turbine model, cavity model, and rotor model to realize the integration of the overall performance model of the gas turbine.

[0006] The present invention may also include: 1. The overall performance model of the gas turbine is constructed in the Simulink environment. The .slx model is converted into a Sysblock model using the Slx model import tool and opened in the Sysplorer visual modeling environment. It supports importing Slx model data and block diagram component information and generates a report.

[0007] 2. Configure model boundary conditions and conduct integrated testing and functional verification of the overall performance model of the gas turbine.

[0008] 3. The specific process of step (2) includes: Based on the known rotor speed and import / export pressure Using the converted speed and pressure ratio Calculate the corresponding reduced flow rate. and efficiency After determining the compressor flow rate and efficiency, based on the compressor inlet total temperature... Obtain the total outlet temperature of the compressor and the power consumed by the compressor The calculation method is as follows: First, based on the inlet temperature... With pressure ratio Calculate the isentropic temperature at the outlet. The corresponding isentropic enthalpy at the outlet is calculated based on the gas law. Then, based on the obtained compressor efficiency Calculate the specific enthalpy of the outlet Obtain the outlet temperature The compressor power was calculated using enthalpy drop. .

[0009] 4. Step (3) specifically includes: treating the combustion chamber model as a volumetric module with the same thermal state throughout, while considering energy input, and based on airflow... Fuel flow Calculate the combustion chamber outlet pressure ,temperature .

[0010] 5. Step (4) specifically includes: the rotor speed during the turbine performance calculation process. and import / export pressure Given that the speed is known, use the reduced rotational speed. Calculate the corresponding reduced flow rate based on the expansion ratio. and efficiency According to the total temperature of the turbine inlet Calculate the total outlet temperature of the turbine. and the power generated by the turbine .

[0011] 6. The compressor model consists of two parts: characteristic calculation equations and performance calculation equations; The characteristic calculation equations are as follows: In the formula For import flow, Due to import pressure, For pressure ratio, For efficiency; The performance calculation equations are as follows: In the formula , For the import / export enthalpy, For the import specific entropy, The isentropic temperature at the outlet. For the outlet temperature, This is for the power consumption of the compressor.

[0012] 7. The combustion chamber model is considered a uniform field, meaning that the entire module has the same thermodynamic state and is not adiabatic. Considering the energy input, its mathematical model is expressed as: In the formula, k is the adiabatic index of the combustion chamber. For the specific heat capacity of the exported gas, Due to export pressure, This refers to the outlet temperature.

[0013] 8. The calculation equations for the turbine model characteristics are as follows: In the formula To convert the turbine's converted flow rate, This is the converted rotational speed; The main calculation equations for the turbine's power operation process are as follows: In the formula To generate power for the turbine, Specific enthalpy before mixing at the turbine outlet.

[0014] The advantages of this invention are: 1. This invention provides a fast and effective way to realize the forward design technology of gas turbines; the overall performance model obtained by this invention has an independent intellectual property rights simulation compilation and solution underlying algorithm, which provides technical support for the digital realization of marine gas turbines.

[0015] 2. The Sysblock platform proposed in this invention uses Modelica for unified modeling and performs simulation calculations through a unified solver. Modelica is an object-oriented, multi-domain modeling language specifically designed for modeling complex dynamic systems. It supports expressing different types of models (such as physical models, control system modules, and their interactions) in a unified manner. In this environment, physical models and control strategies can be modeled and simulated using the same language and solver. Model simulation is based on model-generated code, thus ensuring consistent results without the need for back-to-back testing and verification.

[0016] 3. This invention, based on the Modelica unified modeling language and unified solver architecture, fundamentally solves the challenge of efficiently and accurately integrating heterogeneous models (such as Fortran, Python, and Amesim) from multiple fields (mechanical, thermodynamic, fluid, and control) on a unified platform. Simultaneously, this invention is compatible with existing model migration paths, providing a lossless SLX model conversion tool that can automatically migrate historical Simulink models (such as component characteristic line libraries and control logic) to the Sysblock platform, preserving existing accumulation while achieving model inheritance upgrades. Attached Figure Description

[0017] Figure 1 This is a flowchart of the present invention; Figure 2This is a breakdown diagram of the overall performance model of the gas turbine. Detailed Implementation

[0018] The invention will now be described in more detail with reference to the accompanying drawings: Combination Figure 1-2 The present invention specifically includes the following steps: Step 1: Modular Decomposition of the Gas Turbine System. The gas turbine used in this embodiment is a three-shaft gas turbine (the gas generator has two shafts: a low-pressure shaft and a high-pressure shaft, and a separate shaft that drives the propeller). As shown in Figure 2, the three-shaft gas turbine adopts a modular modeling and decomposition method. Based on the actual topology, the gas turbine model is decomposed into mathematical and simulation models of various modules, including the low-pressure compressor, high-pressure compressor, combustion chamber, combustion chamber, high-pressure turbine, low-pressure turbine, and power turbine.

[0019] Step 2: Compressor Model Construction. Based on the compressor performance calculation principles and similarity theory, low-pressure and high-pressure compressor models are constructed using Sysblock. The compressor model inputs are compressor inlet pressure, compressor outlet temperature, compressor outlet pressure, and compressor speed; the outputs are compressor inlet flow rate, compressor power consumption, compressor outlet temperature, and compressor outlet flow rate.

[0020] Based on the known rotor speed and import / export pressure Using the converted speed and pressure ratio Calculate the corresponding reduced flow rate. and efficiency The calculation method is as follows: Given the compressor characteristics, the above information regarding the reduced flow rate... and efficiency The calculation can be constructed using the characteristic data interpolation module.

[0021] After determining the compressor flow rate and efficiency, based on the compressor inlet total temperature... Obtain the total outlet temperature of the compressor and the power consumed by the compressor The calculation method is as follows: First, based on the inlet temperature... With pressure ratio Calculate the isentropic temperature at the outlet. : The corresponding isentropic enthalpy at the outlet is calculated based on the gas law. Then, based on the obtained compressor efficiency Calculate the specific enthalpy of the outlet Finally, the outlet temperature is obtained. The compressor power was calculated using enthalpy drop. .

[0022] Step 3: Combustion chamber model construction. The inputs to the combustion chamber model are combustion chamber inlet flow rate, combustion chamber inlet temperature, combustion chamber outlet flow rate, and combustion chamber air-fuel ratio. The outputs are combustion chamber outlet temperature, combustion chamber inlet pressure, and combustion chamber outlet pressure.

[0023] The combustion chamber module is considered as a non-adiabatic cavity model with the same thermal state throughout, taking energy input into account. The flow rate at the combustion chamber inlet is then considered. Fuel flow rate Calculate the outlet temperature ,pressure The calculation formula is as follows: Step 4: Based on the turbine performance calculation principles and similarity theory, construct models of the high-pressure turbine, low-pressure turbine, and power turbine. The model inputs are inlet total pressure, outlet total pressure, inlet total temperature, and rotational speed; the outputs are outlet total temperature, equivalent flow rate, and output power.

[0024] First, the equivalent flow rate and equivalent speed are calculated based on the turbine characteristic equation: Given the turbine characteristics, the turbine efficiency under the current operating conditions is obtained using a characteristic data interpolation module: Finally, based on the obtained converted flow rate and efficiency, combined with the turbine inlet total temperature... Calculate the total outlet temperature of the turbine. and the power generated by the turbine : Step 5: Constructing the cavity and rotor model. The cavity model is constructed using the ideal gas law: The rotor model is constructed using dynamic equations: Step Six: Model Integration and Topology Connection. Connect the components according to the actual gas turbine gas path topology. The cavity module is placed between components to transmit dynamic pressure / temperature, and the rotor module is associated with the compressor and turbine power balance.

[0025] Step 7: Boundary Condition Configuration and Simulation Testing Verification. Given the boundary conditions of the overall performance model of the gas turbine, such as inlet pressure and load power, perform operating condition testing and functional verification on the overall performance model built on the Sysblock platform.

[0026] If you already have a Simulink model (.slx) of the overall performance of the gas turbine, import the model using the Sysplorer SLX conversion tool. The following conversions will be completed automatically: Simulink algebraic loop → Modelica differential-algebraic equations (DAE); dimensional system unification (SI units); generation of a conversion report, marking interfaces that require manual verification (such as custom S-functions and dynamic interpolation modules).

[0027] This invention effectively solves key bottleneck problems in traditional modeling, such as difficulties in integrating multi-source heterogeneous models (e.g., Fortran, Python, Amesim), loss of accuracy in data conversion, and limited co-simulation step size. This method achieves unified expression and high-precision co-solution of the physical models and system block diagram models of core components such as the compressor, combustion chamber, and turbine by modularly decomposing the gas turbine system and using the Sysblock environment of MWORKS.Sysplorer and the Modelica unified modeling language.

[0028] This invention ensures the accuracy of the model and its real-time simulation capabilities. Through unified platform integration, it avoids accuracy loss during data conversion and meets the real-time simulation requirements of highly dynamic processes.

[0029] Meanwhile, the SLX model conversion tool provided by this invention supports the lossless migration of existing Simulink gas turbine models (.slx files) to the Sysblock platform, achieving smooth inheritance and upgrading of historical model resources. This significantly reduces model migration costs and provides efficient and reliable technical support for the digital forward design, performance optimization, and virtual-physical integrated control of marine gas turbines.

Claims

1. A modeling method for the overall performance of marine gas turbines based on the Sysblock platform, characterized by: Includes the following steps: (1) Modular decomposition of the gas turbine system: The gas turbine body is decomposed into a low-pressure compressor model, a high-pressure compressor model, a combustion chamber model, a high-pressure turbine model, a low-pressure turbine model, a power turbine model, a cavity model, and a rotor model; (2) Based on the compressor performance calculation principle and similarity theory, construct low-pressure compressor and high-pressure compressor models based on Sysblock; (3) Based on the calculation principle of combustion chamber thermodynamic performance, establish a combustion chamber model based on Sysblock; (4) Based on the turbine performance calculation principle and similarity theory, construct high-pressure turbine, low-pressure turbine and power turbine models based on Sysblock; (5) Construct cavity and rotor models based on Sysblock respectively; (6) Based on the actual topology, connect the constructed low-pressure compressor model, high-pressure compressor model, combustion chamber model, high-pressure turbine model, low-pressure turbine model, power turbine model, cavity model, and rotor model to realize the integration of the overall performance model of the gas turbine.

2. The method for modeling the overall performance of a marine gas turbine based on the Sysblock platform according to claim 1, characterized in that: The overall performance model of the gas turbine was built in the Simulink environment. The .slx model was converted into a Sysblock model using the Slx model import tool and opened in the Sysplorer visual modeling environment. It supports importing Slx model data and block diagram component information and generates a report.

3. The method for modeling the overall performance of a marine gas turbine based on the Sysblock platform according to claim 2, characterized in that: Configure the model boundary conditions and conduct integrated testing and functional verification of the overall performance model of the gas turbine.

4. The method for modeling the overall performance of a marine gas turbine based on the Sysblock platform according to claim 1, characterized in that: Step (2) includes the following specific processes: Based on the known rotor speed and import / export pressure Using the converted speed and pressure ratio Calculate the corresponding reduced flow rate. and efficiency After determining the compressor flow rate and efficiency, based on the compressor inlet total temperature... Obtain the total outlet temperature of the compressor and the power consumed by the compressor The calculation method is as follows: First, based on the inlet temperature... With pressure ratio Calculate the isentropic temperature at the outlet. The corresponding isentropic enthalpy at the outlet is calculated based on the gas law. Then, based on the obtained compressor efficiency Calculate the specific enthalpy of the outlet Obtain the outlet temperature The compressor power was calculated using enthalpy drop. .

5. The method for modeling the overall performance of a marine gas turbine based on the Sysblock platform according to claim 1, characterized in that: Step (3) specifically includes: treating the combustion chamber model as a volumetric module with the same thermal state throughout, while considering energy input and based on airflow. Fuel flow Calculate the combustion chamber outlet pressure ,temperature .

6. The method for modeling the overall performance of a marine gas turbine based on the Sysblock platform according to claim 1, characterized in that: Step (4) specifically includes: the rotor speed during turbine performance calculation. and import / export pressure Given that the speed is known, use the reduced rotational speed. Calculate the corresponding reduced flow rate based on the expansion ratio. and efficiency According to the total temperature at the turbine inlet Calculate the total outlet temperature of the turbine. and the power generated by the turbine .

7. The method for modeling the overall performance of a marine gas turbine based on the Sysblock platform according to claim 1, characterized in that: The compressor model consists of two parts: characteristic calculation equations and performance calculation equations; The characteristic calculation equations are as follows: In the formula For import flow, Due to import pressure, For pressure ratio, For efficiency; The performance calculation equations are as follows: In the formula , For the import / export enthalpy, For the import specific entropy, The isentropic temperature at the outlet. For the outlet temperature, This is for the power consumption of the compressor.

8. The method for modeling the overall performance of a marine gas turbine based on the Sysblock platform according to claim 1, characterized in that: The combustion chamber model is considered a uniform field, meaning that the entire module has the same thermodynamic state and is not adiabatic. Considering the energy input, its mathematical model is expressed as: In the formula, k is the adiabatic index of the combustion chamber. For the specific heat capacity of the exported gas, Due to export pressure, This refers to the outlet temperature.

9. The method for modeling the overall performance of a marine gas turbine based on the Sysblock platform according to claim 1, characterized in that: The equations for calculating the characteristics of the turbine model are as follows: In the formula To convert the turbine's converted flow rate, This is the converted rotational speed; The main calculation equations for the turbine's power operation process are as follows: In the formula To generate power for the turbine, Specific enthalpy before mixing at the turbine outlet.

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