Virtual sensing method for radial flow type turbine of supercharger of marine internal combustion engine

Abstract

The invention provides a marine internal combustion engine supercharger radial flow type turbine virtual sensing method which comprises the steps that turbine working state information is received, and the turbine working state information comprises working medium mass flow; calling a turbine inlet section simulation sensing sub-model, judging whether the blockage flow is greater than the first preset value, if so, calling a volute simulation sensing sub-model, a nozzle ring simulation sensing sub-model and an impeller simulation sensing sub-model in sequence, and judging whether the surge flow is greater than the second preset value; if yes, the operation is finished, and the first preset value and the second preset value are the working medium mass flow. The working medium mass flow is updated through the turbine working state information, the blocking flow and the surge flow are conducted, and the technical problem that in the prior art, flow sensing for the radial flow type turbine of the supercharger is lacked is solved.

Description

Technical fields:

[0001] This invention relates to the field of virtual sensing technology, and in particular to a virtual sensing method for a radial turbine of a marine internal combustion engine turbocharger. Background technology:

[0002] In the field of marine diesel engine turbocharger fault diagnosis, Jia Baozhu et al. collected bearing vibration signals through coarse-grained sampling and diagnosed turbocharger bearing faults using vibration-based fault diagnosis, employing a data-driven approach for marine diesel engine turbocharger fault diagnosis. This technology requires continuous acquisition of test data (turbocharger bearing vibration signals) to determine the turbocharger's operational health status, thereby achieving fault prediction. Yang Jianguo et al. detected marine diesel engine turbocharger vibration signals through online monitoring, obtaining turbocharger fault characteristic parameters by reconstructing the vibration signals during fault identification, and using this as a turbocharger fault diagnosis method. This method judges the turbocharger's operational status based on whether its vibration state is normal. Du Lei et al. optimized the one-dimensional simulation model of the diesel engine turbocharger, adding modeling and calculation of components such as pistons, bearings, turbochargers, and shock absorbers to improve the simulation accuracy of the turbocharger system. Zhou Chengyao et al. determined whether the turbocharger speed was abnormal by establishing a relationship between engine speed and turbocharger speed. Du Yang et al. defined the abnormal range of turbocharger speed by establishing a relationship between diesel engine main unit load, scavenging pressure, and turbocharger speed, thereby determining turbocharger speed-related faults. Zeng Hong et al. observed abnormalities in the frequency and amplitude of pressure vibrations by detecting signals such as compressor outlet pressure changes, thereby determining compressor faults. Jiang Zenghui et al. determined whether turbocharger pressure was abnormal based on MAP charts.

[0003] Research on one-dimensional virtual sensing models began earlier abroad. In the 1850s, scholars studied one-dimensional loss models for radial centrifugal compressors. In 1965, Krylov et al. studied the influence of centrifugal compressor tip clearance on compressor operating parameters. In 1975, Whitfield et al. studied the influence of slip loss coefficient on flow conditions within a centrifugal compressor. In 1980, Conrad et al. predicted the maximum MAP (measurand ratio) of centrifugal compressors with bladed diffusers using one-dimensional performance prediction. In 2008, Costal et al. studied the propagation and evolution of unsteady waves in turbochargers using a one-dimensional model. In 2017, Ding et al. studied the performance variation of radial turbines under pulsed flow conditions using a one-dimensional model.

[0004] There is an urgent need for a virtual sensing method for radial turbines of marine internal combustion engine turbochargers, which would help solve the technical problem of lacking flow sensing for radial turbines of turbochargers in the existing technology. Summary of the Invention:

[0005] In one embodiment, the present invention provides a virtual sensing method for radial turbines of marine internal combustion engine turbochargers, which updates the working fluid mass flow rate through turbine operating status information, and measures blockage flow rate and surge flow rate, thereby helping to solve the technical problem of lacking flow sensing for radial turbines of turbochargers in the prior art.

[0006] The virtual sensing method for the radial turbine of the marine internal combustion engine turbocharger includes:

[0007] Receive turbine operating status information, wherein the turbine operating status information includes working fluid mass flow rate;

[0008] The turbine inlet section simulation sensing sub-model is invoked to determine whether the blockage flow rate is greater than the first predetermined value. If so, the volute simulation sensing sub-model, nozzle ring simulation sensing sub-model, and impeller simulation sensing sub-model are invoked in sequence to determine whether the surge flow rate is greater than the second predetermined value.

[0009] If so, then the process ends, wherein the first predetermined value and the second predetermined value are the mass flow rates of the working fluid.

[0010] In one embodiment, after the step of determining whether the congestion flow rate is greater than the first predetermined value, the method further includes:

[0011] If not, then after updating the first predetermined value, return to the step of receiving turbine operating status information and repeat the calculation.

[0012] In one embodiment, after the step of determining whether the surge flow rate is greater than the second predetermined value, the method further includes:

[0013] If not, then after updating the second predetermined value, return to the step of receiving turbine operating status information and repeat the calculation.

[0014] In one embodiment, the marine internal combustion engine turbocharger radial turbine has a radial turbine inlet to volute inlet section, a volute inlet to nozzle ring inlet section, a nozzle ring inlet to impeller inlet section, and an impeller inlet to radial turbine outlet section;

[0015] The above sub-models correspond in sequence.

[0016] In one embodiment, the marine internal combustion engine turbocharger radial turbine has a radial turbine inlet, a volute inlet, a nozzle ring inlet, an impeller inlet, and a radial turbine outlet.

[0017] In one embodiment, the turbine operating status information further includes turbine geometry parameters, inlet total temperature, total pressure, and impeller speed.

[0018] In one embodiment, loss calculation is performed on the invoked volute-simulated perception sub-model.

[0019] In one embodiment, an early warning is provided when the turbine operating state parameters are within a predetermined range.

[0020] In one embodiment, the working fluid mass flow rate gradient is reduced by 0.1 each time it is updated.

[0021] In one embodiment, the loss calculation includes an isobaric loss model and a NASA loss model. Attached image description:

[0022] Figure 1 This is a schematic diagram of a radial turbine structure for a marine internal combustion engine turbocharger in one embodiment of the present invention;

[0023] Figure 2 This is a schematic diagram of a virtual sensing method for a radial turbine of a marine internal combustion engine turbocharger, according to another embodiment of the present invention. Detailed implementation method:

[0024] To enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0025] Various embodiments and features of this application are described herein with reference to the accompanying drawings.

[0026] These and other features of this application will become apparent from the following description of preferred forms of embodiments given as non-limiting examples, with reference to the accompanying drawings.

[0027] It should also be understood that although this application has been described with reference to some specific examples, those skilled in the art can certainly implement many other equivalent forms of this application, which have the features described in the claims and are therefore all within the scope of protection defined herein.

[0028] The above and other aspects, features and advantages of this application will become more apparent when taken in conjunction with the accompanying drawings and in view of the following detailed description.

[0029] Specific embodiments of this application are described below with reference to the accompanying drawings; however, it should be understood that the claimed embodiments are merely examples of this application, which can be implemented in various ways. Well-known and / or repeated functions and structures are not described in detail to ascertain the true intent based on the user's historical operations, and to avoid unnecessary or redundant details that would obscure this application. Therefore, the specific structural and functional details claimed herein are not intended to be limiting, but merely serve as the basis and representative basis for the claims to teach those skilled in the art to use this application in various ways with substantially any suitable detailed structure.

[0030] This specification may use the phrases “in one embodiment,” “in another embodiment,” “in yet another embodiment,” or “in other embodiments,” all of which may refer to one or more of the same or different embodiments according to this application.

[0031] To enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0032] Various embodiments and features of this application are described herein with reference to the accompanying drawings.

[0033] These and other features of this application will become apparent from the following description of preferred forms of embodiments given as non-limiting examples, with reference to the accompanying drawings.

[0034] It should also be understood that although this application has been described with reference to some specific examples, those skilled in the art can certainly implement many other equivalent forms of this application, which have the features described in the claims and are therefore all within the scope of protection defined herein.

[0035] The above and other aspects, features and advantages of this application will become more apparent when taken in conjunction with the accompanying drawings and in view of the following detailed description.

[0036] Specific embodiments of this application are described below with reference to the accompanying drawings; however, it should be understood that the claimed embodiments are merely examples of this application, which can be implemented in various ways. Well-known and / or repeated functions and structures are not described in detail to ascertain the true intent based on the user's historical operations, and to avoid unnecessary or redundant details that would obscure this application. Therefore, the specific structural and functional details claimed herein are not intended to be limiting, but merely serve as the basis and representative basis for the claims to teach those skilled in the art to use this application in various ways with substantially any suitable detailed structure.

[0037] This specification may use the phrases “in one embodiment,” “in another embodiment,” “in yet another embodiment,” or “in other embodiments,” all of which may refer to one or more of the same or different embodiments according to this application.

[0038] This invention proposes a virtual sensing method for radial turbines of marine diesel engine turbochargers based on the fusion of mechanism and geometric parameters. Based on the characteristics of marine turbocharger geometric parameters, the calculation formulas for turbine internal volute loss, angle of attack loss, and impeller flow loss are modified. The internal working fluid parameters of the turbine are solved iteratively through the thermodynamic and aerodynamic equations of the radial turbine. Under the premise of known radial turbine geometric parameters, the performance parameters of the radial turbine can be obtained online. Real-time virtual sensing and fault warning of radial turbine performance can be performed, which can replace some physical sensors.

[0039] Figure 1 This is a schematic diagram of a radial turbine structure for a marine internal combustion engine turbocharger in one embodiment of the present invention; Figure 2 This is a schematic diagram of a virtual sensing method for a radial turbine of a marine internal combustion engine turbocharger, according to another embodiment of the present invention. Figures 1 to 2 As shown, in one embodiment, the present invention provides a virtual sensing method for a radial turbine of a marine internal combustion engine turbocharger, the virtual sensing method for a radial turbine of a marine internal combustion engine turbocharger comprising:

[0040] S101, Receive turbine operating status information, wherein the turbine operating status information includes working fluid mass flow rate;

[0041] S102, call the turbine inlet section simulation sensing sub-model to determine whether the blockage flow rate is greater than the first predetermined value. If so, call the volute simulation sensing sub-model, nozzle ring simulation sensing sub-model, and impeller simulation sensing model in sequence to determine whether the surge flow rate is greater than the second predetermined value.

[0042] S103, if yes, then end, wherein the first predetermined value and the second predetermined value are the mass flow rate of the working fluid.

[0043] This embodiment provides a specific implementation of a virtual sensing method for a radial turbine of a marine internal combustion engine turbocharger. The method utilizes four sub-models for calculation. It should be noted that these sub-models are all existing technologies; the innovation lies in the overall algorithm logic. Furthermore, the first predetermined value and the second predetermined value both correspond to the working fluid mass flow rate in a single calculation loop.

[0044] In one embodiment, after the step of determining whether the congestion flow rate is greater than the first predetermined value, the method further includes:

[0045] If not, then after updating the first predetermined value, return to the step of receiving turbine operating status information and repeat the calculation.

[0046] In one embodiment, after the step of determining whether the surge flow rate is greater than the second predetermined value, the method further includes:

[0047] If not, then after updating the second predetermined value, return to the step of receiving turbine operating status information and repeat the calculation.

[0048] In one embodiment, the marine internal combustion engine turbocharger radial turbine has a radial turbine inlet to volute inlet section, a volute inlet to nozzle ring inlet section, a nozzle ring inlet to impeller inlet section, and an impeller inlet to radial turbine outlet section;

[0049] The above sub-models correspond in sequence.

[0050] This embodiment provides a structural basis for calculating the aforementioned sensed parameters such as flow rate.

[0051] In one embodiment, the marine internal combustion engine turbocharger radial turbine has a radial turbine inlet 0, a volute inlet 1, a nozzle ring inlet 2, an impeller inlet 3, and a radial turbine outlet 4.

[0052] In one embodiment, the turbine operating status information further includes turbine geometry parameters, inlet total temperature, total pressure, and impeller speed.

[0053] In one embodiment, loss calculation is performed on the invoked volute-simulated perception sub-model.

[0054] In one embodiment, an early warning is provided when the turbine operating state parameters are within a predetermined range.

[0055] During the overall calculation process, each parameter is generally given a range. If the range of a single parameter in this loop is exceeded, a warning will be issued.

[0056] In one embodiment, the working fluid mass flow rate gradient is reduced by 0.1 each time it is updated.

[0057] In one embodiment, the loss calculation includes an isobaric loss model and a NASA loss model.

[0058] The radial-flow turbine of a marine diesel engine turbocharger has three important components: the impeller, the nozzle ring, and the volute. These three physical structures divide the flow structure of the radial-flow turbine into four parts: the section from the turbine inlet to the volute inlet, the section from the volute inlet to the nozzle ring inlet, the section from the nozzle ring inlet to the impeller inlet, and the section from the impeller inlet to the turbine outlet. The thermodynamic and aerodynamic equations for the radial-flow turbine are then solved.

[0059] The parameters and formulas are as follows:

[0060]

[0061]

[0062] The equations for solving the radial flow turbine inlet to volute inlet are shown below:

[0063]

[0064] P 00 -P 01 =K 01 (P 01 -P1) (1-2);

[0065]

[0066] The equations for solving the problem from the volute inlet to the nozzle ring inlet are shown below:

[0067] ρ1C m1 A1=ρ 2-0 C m2 A2 (2-1);

[0068]

[0069] The equations for solving the problem from the nozzle ring inlet to the impeller inlet are shown below:

[0070]

[0071] The equations for solving the problem from the impeller inlet to the radial turbine outlet are shown below:

[0072] C sllip =(1-σ)U4 (4-1);

[0073] C θ4 =U4-C m4-0 tan(β 4b )-C slip (4-2);

[0074] Δh0=U4C θ4 -U3C θ3 +W vol +W ine +W rot (4-3);

[0075] C m4 =m / (ρ4A4) (4-4);

[0076] Key innovations of the technical solution:

[0077] Current virtual sensing methods for radial turbines in diesel engine turbochargers are mostly based on big data, which lacks clarity regarding fault mechanisms and their locations, making them difficult to replace physical sensors. Furthermore, current virtual sensing models for turbochargers are primarily based on small-volume turbochargers. This patent modifies the calculation formulas for turbine internal volute losses, angle-of-attack losses, and impeller flow losses based on the geometric characteristics of marine turbochargers. It employs a mathematical-physical model based on mechanism and data fusion to perform virtual sensing and online fault warning for radial turbines, potentially replacing some physical sensors. Based on existing radial turbine geometric parameters (flow area of ​​four parts, blade angle, radius, etc.) and environmental parameters (inlet pressure and temperature), it obtains the state parameters of the radial turbine under complete operating conditions.

[0078] As the turbocharger volume increases, the assumption given in the NASA volute loss model that "the volute loss is proportional to the average kinetic energy at the volute inlet and outlet, and the kinetic energy loss coefficient remains unchanged" is unreasonable. This patent corrects this by using marine turbocharger test data to modify the volute loss coefficient and volute speed coefficient.

[0079] Similarly, the angle-of-attack loss is corrected. Traditional loss models mainly include the isobaric loss model and the NASA loss model. The isobaric loss model assumes that the static pressure remains constant when the airflow angle deviates from the design condition and ignores blade thickness. The NASA loss model considers the impact of blade thickness on the angle-of-attack loss by considering the number of blades, thus calculating the optimal angle of attack. However, as the size and weight of marine turbochargers gradually increase, the blade thickness also increases. Simply considering the impact of blade thickness based on the number of blades leads to a large deviation between virtual sensing results and experimental values. Therefore, blade thickness is incorporated into the calculation of the optimal angle of attack to correct the angle-of-attack loss.

[0080] Impeller flow losses consist of two parts: channel loss and tip clearance loss. Channel loss can be expressed as a function of the average kinetic energy at the turbine inlet and outlet, and is less affected by the turbocharger volume. However, tip clearance loss requires consideration of leakage. Marine turbochargers are larger, and the tip clearance length is even greater, rendering the empirical loss parameters commonly used in automotive turbochargers inapplicable. Therefore, experimental data is used to correct the empirical loss parameters, thereby revising the calculation of tip clearance loss (impeller flow loss).

[0081] By replacing corresponding position sensors with geometric parameters and mechanistic calculations, the number of sensors used can be effectively reduced, lowering operating costs and further saving space in the diesel engine. Furthermore, the model in this invention determines the location of abnormal radial turbine state parameters through partitioning, pinpointing the fault location and type, enabling more precise and rapid fault localization.

[0082] The exhaust gas flows through the turbocharger turbine of a marine diesel engine as shown in the diagram above, passing through the volute, nozzle ring, and impeller before finally exiting the turbine. In the radial-flow turbine virtual sensing model described in this patent, the turbine is divided into four sub-models: turbine inlet section, volute, nozzle ring, and impeller. Each sub-model is solved in the order indicated by the numbers above. The output of the upstream sub-model serves as the input parameters for the downstream sub-model, ultimately resulting in the calculation of the entire radial-flow turbine.

[0083] Describe in detail the best way and process to achieve this intellectual achievement.

[0084] Intellectual achievements in software programs

[0085] Software identification materials, namely source code and / or object code, as well as user manuals or operating instructions.

[0086] The three key components of a marine diesel engine turbocharger's radial-flow turbine are the impeller, nozzle ring, and volute. These three physical structures divide the flow structure of the radial-flow turbine into four parts: the section from the turbine inlet to the volute inlet, the section from the volute inlet to the nozzle ring inlet, the section from the nozzle ring inlet to the impeller inlet, and the section from the impeller inlet to the turbine outlet. By solving the thermodynamic and aerodynamic equations for the radial-flow turbine, the aerodynamic and thermodynamic parameters can be obtained, thus enabling virtual sensing, fault warning, and replacement of physical sensors. As shown in the flowchart, the input parameters are turbine geometry parameters and inlet environment parameters. The first to fourth sub-models represent the turbine inlet section, volute, nozzle ring, and impeller, respectively. When the inlet mass flow rate is between the blockage flow rate and the surge flow rate, the model has a solution. The above four sub-models can be solved sequentially to obtain the turbine aerodynamic and thermodynamic parameters.

[0087] The above embodiments are merely exemplary embodiments of the present invention and are not intended to limit the present invention. The scope of protection of the present invention is defined by the claims. Those skilled in the art can make various modifications or equivalent substitutions to the present invention within its spirit and scope of protection, and such modifications or equivalent substitutions should also be considered to fall within the scope of protection of the present invention.

Claims

1. A virtual sensing method for a radial turbine of a marine internal combustion engine turbocharger, characterized in that, The virtual sensing method for the radial turbine of the marine internal combustion engine turbocharger includes: Receive turbine operating status information, wherein the turbine operating status information includes working fluid mass flow rate; The turbine inlet section simulation sensing sub-model is invoked to determine whether the blockage flow rate is greater than the first predetermined value. If so, the volute simulation sensing sub-model, nozzle ring simulation sensing sub-model, and impeller simulation sensing sub-model are invoked in sequence to determine whether the surge flow rate is greater than the second predetermined value. If so, then the process ends, wherein the first predetermined value and the second predetermined value are the mass flow rates of the working fluid.

2. The virtual sensing method for radial turbines of marine internal combustion engine turbochargers according to claim 1, characterized in that, After the step of determining whether the congestion flow rate is greater than the first predetermined value, the method further includes: If not, then after updating the first predetermined value, return to the step of receiving turbine operating status information and repeat the calculation.

3. The virtual sensing method for radial turbines of marine internal combustion engine turbochargers according to claim 2, characterized in that, After the step of determining whether the surge flow rate is greater than the second predetermined value, the method further includes: If not, then after updating the second predetermined value, return to the step of receiving turbine operating status information and repeat the calculation.

4. The virtual sensing method for radial turbines of marine internal combustion engine turbochargers according to claim 3, characterized in that, The marine internal combustion engine turbocharger radial turbine has a radial turbine inlet to volute inlet section, a volute inlet to nozzle ring inlet section, a nozzle ring inlet to impeller inlet section, and an impeller inlet to radial turbine outlet section; The above sub-models correspond in sequence.

5. The virtual sensing method for radial turbines of marine internal combustion engine turbochargers according to claim 4, characterized in that, The marine internal combustion engine turbocharger radial turbine has a radial turbine inlet, a volute inlet, a nozzle ring inlet, an impeller inlet, and a radial turbine outlet.

6. The virtual sensing method for radial turbines of marine internal combustion engine turbochargers according to claim 5, characterized in that, The turbine operating status information also includes turbine geometric parameters, inlet total temperature, total pressure, and impeller speed.

7. The virtual sensing method for radial turbines of marine internal combustion engine turbochargers according to claim 6, characterized in that, Loss calculation is performed on the aforementioned invocation of the volute-simulated perception sub-model.

8. The virtual sensing method for radial turbines of marine internal combustion engine turbochargers according to claim 7, characterized in that, When the turbine operating parameters are within a predetermined range, an early warning is issued.

9. The virtual sensing method for radial turbines of marine internal combustion engine turbochargers according to claim 8, characterized in that, The gradient of the working fluid mass flow rate is reduced by 0.1 each time it is updated.

10. The virtual sensing method for radial turbines of marine internal combustion engine turbochargers according to claim 9, characterized in that, Loss calculations include the isobaric loss model and the NASA loss model.

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