Turboshaft engine ground bench performance tuning method based on turbine guider area
By using the overall performance calculation model of the turbine guide area, the minimum adjustment amount for the performance debugging of the turboshaft engine on the ground test bench was found, which solved the problem of high cost and low efficiency caused by unreasonable adjustment of the turbine guide area, and realized efficient and low-cost turboshaft engine debugging.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- AECC HUNAN AVIATION POWERPLANT RES INST
- Filing Date
- 2023-09-26
- Publication Date
- 2026-06-26
AI Technical Summary
In the current performance testing of turboshaft engines on ground test benches, the unreasonable adjustment of the guide area of the gas turbine and power turbine leads to high testing costs, low efficiency, and frequent replacement of turbine parts.
By configuring a general performance calculation model with different guide vane areas for gas turbines and power turbines, the corresponding temperature, power, fuel consumption rate and speed change data are obtained. Two-dimensional linear interpolation is then performed to find the guide vane area that simultaneously satisfies the relevant constraints, and then the minimum adjustment amount is found to achieve ground test bench performance debugging of the turboshaft engine.
It effectively improves the efficiency of ground test bench performance debugging of turboshaft engines, reduces debugging costs, avoids the replacement of turbine parts, and controls the gas generator speed within the limit range.
Smart Images
Figure CN117433795B_ABST
Abstract
Description
Technical Field
[0001] This application relates to the field of turboshaft engine ground test bench performance testing technology, and in particular, to a turboshaft engine ground test bench performance testing method based on turbine guide vane area. Background Technology
[0002] Compared to turboshaft engines with power outputs above 600kW, small turboshaft engines in the 200-600kW range are characterized by higher gas generator speeds and lower gas temperatures, typically using speed as the defining characteristic. During bench testing, the power output is primarily limited by speed, while temperature has a larger margin. The main testing methods for small turboshaft engines on ground benches include adjusting the guide vane area of the gas turbine or power turbine.
[0003] Traditional methods do not take into account the adjustment range of the guide vane area for both gas turbines and power turbines. When the gas turbine or power turbine needs to be enlarged, if the control is not good, the turbine guide vane shape adjustment will be too large and will not meet the requirements. It cannot be reduced again, resulting in the need to replace turbine parts. Summary of the Invention
[0004] This application provides a method for ground test bench performance debugging of turboshaft engines based on turbine guide vane area, in order to solve the technical problems of high debugging cost and low efficiency caused by the adjustment amount in existing ground test bench performance debugging of turboshaft engines based on turbine guide vane area.
[0005] The technical solution adopted in this application is as follows:
[0006] A method for ground-based performance testing of a turboshaft engine based on turbine guide vane area includes the following steps:
[0007] By configuring overall performance calculation models with different gas turbine and power turbine guide vane areas, the results of different gas turbine guide vane areas A under the same gas generator physical speed are obtained. GT and the area A of the power turbine guide PT Corresponding gas temperature change data △T t4.5 The power change data ΔP is used to generate tables for gas temperature change and power change, respectively.
[0008] By configuring overall performance calculation models with different gas turbine and power turbine guide vane areas, the different gas turbine guide vane areas A under the same takeoff power conditions are obtained. GT and the area A of the power turbine guide PT The corresponding fuel consumption rate change data △sfc and speed change data △n g And separate tables were generated for fuel consumption rate changes and engine speed changes;
[0009] The gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed change data that simultaneously satisfy the relevant constraints can be obtained by two-dimensional linear interpolation from the gas temperature change table, power change table, fuel consumption rate, and speed change table. GT and the area A of the power turbine guide PT As candidate A GT and A PT ;
[0010] From candidate A GT and A PT In the process of optimization, the area A of the gas turbine guide vane is found. GT and the area A of the power turbine guide PT The minimum adjustment amount is used for performance testing of turboshaft engines on ground test benches.
[0011] Furthermore, the different gas turbine guide areas A GT and the area A of the power turbine guide PT The interval between changes is 1%.
[0012] Furthermore, the gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed variation data that simultaneously satisfy the relevant constraints is obtained by two-dimensional linear interpolation from the gas temperature variation table, power variation table, fuel consumption rate variation table, and speed variation table. GT and the area A of the power turbine guide PT As candidate A GT and A PT The specific steps include:
[0013] Based on the initial performance values and relevant constraints of the turboshaft engine, the temperature margin, power margin, fuel consumption rate margin, and speed margin of the turboshaft engine are calculated. The relevant constraints include: at 1.0 speed, the power output is greater than or equal to the target value P_. limit T t4.5 Less than or equal to temperature value T t4.5_limit Under the specified power conditions, the fuel consumption rate is less than or equal to the specified value sfc_ limit The relevant initial performance values include: initial power value P. _0 Initial gas temperature T t4.5_0 Initial fuel consumption rate (sfc_0), engine speed (n) g_0 ;
[0014] Based on the temperature margin, power margin, fuel consumption rate margin, speed margin, and set magnitude relationships, the gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed change data that simultaneously satisfy the set magnitude relationships is obtained through two-dimensional linear interpolation from the temperature, power, fuel consumption rate, and speed change data tables. GTand the area A of the power turbine guide PT As candidate A GT and A PT .
[0015] Furthermore, the calculation of the temperature margin, power margin, fuel consumption margin, and speed margin of the turboshaft engine based on the initial values of its relevant performance and related constraints specifically includes:
[0016] Calculate the power margin: ΔP _m =P _0 / P_ limit -1;
[0017] Calculate the gas temperature margin: △T t4.5_m =T t4.5_0 / T t4.5_limit -1;
[0018] Calculate the fuel consumption margin △sfc _m =sfc _0 / sfc_ limit -1;
[0019] Calculate the speed margin Δn g_m =n g_0 / n g _ limit -1.
[0020] Furthermore, the gas turbine guide vane area A corresponding to the temperature, power, fuel consumption rate, and speed change data that simultaneously satisfy the set magnitude relationship is obtained by two-dimensional linear interpolation from the temperature, power, fuel consumption rate, and speed change data tables based on temperature margin, power margin, fuel consumption rate margin, speed margin, and set magnitude relationship. GT and the area A of the power turbine guide PT The specific steps include:
[0021] If there exists a ΔP in the power change table that satisfies: ΔP + ΔP _m If ≥0, then the two-dimensional linear interpolation in the power change table yields A that satisfies the condition. GT A PT ;
[0022] If the gas temperature change table contains T t4.5 Satisfy: T t4.5 +△T t4.5_m If ≤0, then the two-dimensional linear interpolation in the gas temperature change table will yield A that satisfies the condition. GT A PT ;
[0023] If the fuel consumption rate change table contains a Δsfc that satisfies: Δsfc + Δsfc_m If ≤0, then A is obtained by two-dimensional linear interpolation in the fuel consumption rate change table, which satisfies the condition. GT A PT ;
[0024] If the fuel consumption rate change table contains Δn g Satisfy: △n g +△n g_m If ≤0, then the two-dimensional linear interpolation in the speed variation table yields A that satisfies the condition. GT A PT ;
[0025] A that simultaneously meets the above conditions GT A PT As candidate A GT and A PT .
[0026] Furthermore, the statement from candidate A GT and A PT In the process of optimization, the area A of the gas turbine guide vane is found. GT and the area A of the power turbine guide PT The minimum adjustment amount is used for the performance testing of turboshaft engines on ground test benches, and the specific steps include:
[0027] From candidate A GT and A PT Selected from The minimum value corresponds to A GT and A PT As the area A of the gas turbine guide vane GT and the area A of the power turbine guide PT The minimum adjustment amount is used for performance testing of turboshaft engines on ground test benches.
[0028] Another preferred embodiment of this application also provides a ground-based performance testing device for a turboshaft engine based on the area of the turbine guide vane, comprising:
[0029] The temperature and power variation data acquisition module is used to obtain the gas turbine guide area A under the same gas generator physical speed by configuring an overall performance calculation model with different gas turbine and power turbine guide areas. GT and the area A of the power turbine guide PT Corresponding gas temperature change data △T t4.5 The power change data ΔP is used to generate tables for gas temperature change and power change, respectively.
[0030] The fuel consumption rate and engine speed variation data acquisition module is used to obtain the gas turbine guide area A under the same takeoff power conditions by configuring an overall performance calculation model with different gas turbine and power turbine guide areas. GT and the area A of the power turbine guide PT The corresponding fuel consumption rate change data △sfc and speed change data △n g And separate tables were generated for fuel consumption rate changes and engine speed changes;
[0031] The filtering module is used to obtain the gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed change data that simultaneously meet the relevant constraints from the gas temperature change table, power change table, fuel consumption rate change table, and speed change table using two-dimensional linear interpolation. GT and the area A of the power turbine guide PT As candidate A GT and A PT ;
[0032] The minimum value optimization module is used to find the minimum value from the candidate A. GT and A PT In the process of optimization, the area A of the gas turbine guide vane is found. GT and the area A of the power turbine guide PT The minimum adjustment amount is used as the performance debugging parameter for the turboshaft engine on the ground test bench.
[0033] Another preferred embodiment of this application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the steps of the turboshaft engine ground test bench performance debugging method based on turbine guide area.
[0034] Another preferred embodiment of this application also provides a storage medium including a stored program that, when the program is executed, controls the device where the storage medium is located to perform the steps of the turboshaft engine ground test bench performance debugging method based on turbine guide area.
[0035] Compared with the prior art, this application has the following advantages:
[0036] This application provides a method for ground-based performance testing of a turboshaft engine based on the area of the turbine guide vane. This method improves the power of a small turboshaft engine by determining the minimum adjustment amount of the gas turbine guide vane and the power turbine guide vane. At the same time, when testing according to the minimum adjustment amount, the speed of the gas generator can be controlled within the limit range. This avoids the problem in the prior art where unreasonable adjustment amounts of the gas turbine guide vane and the power turbine guide vane lead to a large adjustment of the turbine guide vane blade shape, causing the speed of the gas generator to exceed the limit range and fail to meet the requirements, and it cannot be reduced further. If further testing is desired, turbine parts need to be replaced. This method avoids the need to replace turbine parts during the testing process, effectively improves the efficiency of ground-based performance testing of turboshaft engines, and reduces testing costs.
[0037] In addition to the purposes, features, and advantages described above, this application provides other purposes, features, and advantages. The application will now be described in further detail with reference to the accompanying drawings. Attached Figure Description
[0038] The accompanying drawings, which form part of this application, are used to provide a further understanding of this application. The illustrative embodiments and descriptions of this application are used to explain this application and do not constitute an undue limitation of this application. In the drawings:
[0039] Figure 1 This is a schematic flowchart of a preferred embodiment of the performance debugging method for a turboshaft engine on a ground test bench based on the area of the turbine guide vane.
[0040] Figure 2 This is a schematic diagram of a sub-process of step S3 in a preferred embodiment of this application.
[0041] Figure 3 This is a schematic diagram of a sub-process of step S32 in a preferred embodiment of this application.
[0042] Figure 4 This is a schematic diagram of the hydroelectric series dynamometer system device module according to a preferred embodiment of this application.
[0043] Figure 5 This is a schematic block diagram of an electronic device according to a preferred embodiment of this application.
[0044] Figure 6 This is an internal structural diagram of a computer device according to a preferred embodiment of this application. Detailed Implementation
[0045] It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other. This application will now be described in detail with reference to the accompanying drawings and embodiments.
[0046] Reference Figure 1A preferred embodiment of this application provides a method for ground-based performance testing of a turboshaft engine based on the area of the turbine guide vane, comprising the following steps:
[0047] S1. By configuring a comprehensive performance calculation model with different gas turbine and power turbine guide vane areas, the guide vane areas A of different gas turbines under the same gas generator physical speed are obtained. GT and the area A of the power turbine guide PT Corresponding gas temperature change data △T t4.5 The power change data ΔP were collected and converted into a gas temperature change table (Table 2) and a power change table (Table 1), respectively.
[0048] Table 1: Effect of different guide area on power ΔP
[0049]
[0050] Table 2: Effect of different guide area on temperature T t4.5 Impact △T t4.5
[0051]
[0052]
[0053] S2. By configuring a comprehensive performance calculation model with different gas turbine and power turbine guide vane areas, the different gas turbine guide vane areas A under the same takeoff power conditions are obtained. GT and the area A of the power turbine guide PT The corresponding fuel consumption rate change data △sfc and speed change data △n g And separate tables were generated for fuel consumption rate changes and engine speed changes;
[0054] Table 3: Effect of turbine guide vane area on fuel consumption rate at takeoff power Δsfc
[0055]
[0056] Table 4: Influence of turbine guide vane area on gas generator speed at takeoff power Δn g
[0057]
[0058] S3. Obtain the gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed change data that simultaneously satisfy the relevant constraints from the gas temperature change table, power change table, fuel consumption rate change table, and speed change table using two-dimensional linear interpolation. GT and the area A of the power turbine guide PT As candidate A GTand A PT ;
[0059] S4, from candidate A GT and A PT In the process of optimization, the area A of the gas turbine guide vane is found. GT and the area A of the power turbine guide PT The minimum adjustment amount is used for performance testing of turboshaft engines on ground test benches.
[0060] Wherein, the different gas turbine guide area A GT and the area A of the power turbine guide PT The interval variation step size is 1%. This embodiment can simultaneously meet the requirements of efficiency and accuracy by using a reasonable interval variation step size.
[0061] This embodiment provides a ground test bench performance debugging method for turboshaft engines based on turbine guide vane area. This method improves the power of a small turboshaft engine by determining the minimum adjustment amount of the gas turbine guide vane and the power turbine guide vane. At the same time, when debugging according to the minimum adjustment amount, the speed of the gas generator can be controlled within the limit range. This avoids the problem in the prior art where unreasonable adjustment amounts of the gas turbine guide vane and the power turbine guide vane lead to a large adjustment of the turbine guide vane blade shape, causing the speed of the gas generator to exceed the limit range and fail to meet the requirements, and it cannot be reduced further. If you want to continue debugging, you need to replace the turbine parts. This method avoids the need to replace turbine parts during the debugging process, effectively improves the efficiency of ground test bench performance debugging of turboshaft engines, and reduces debugging costs.
[0062] Preferably, such as Figure 2 As shown, the gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed variation data that simultaneously satisfy the relevant constraints can be obtained by two-dimensional linear interpolation from the gas temperature variation table, power variation table, fuel consumption rate variation table, and speed variation table. GT and the area A of the power turbine guide PT As candidate A GT and A PT The specific steps include:
[0063] S31. Calculate the temperature margin, power margin, fuel consumption rate margin, and speed margin of the turboshaft engine based on the initial values and relevant constraints. The relevant constraints include: at 1.0 speed, the power output is greater than or equal to the target value P_ limit T t4.5 Less than or equal to temperature value T t4.5_limit Under the specified power conditions, the fuel consumption rate is less than or equal to the specified value sfc_ limit The relevant initial performance values include: initial power value P. _0 Initial gas temperature Tt4.5_0 Initial fuel consumption rate (sfc_0), engine speed (n) g_0 ;
[0064] S32. Based on the temperature margin, power margin, fuel consumption rate margin, speed margin, and set magnitude relationships, the gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed change data that simultaneously satisfy the set magnitude relationships is obtained through two-dimensional linear interpolation from the temperature, power, fuel consumption rate, and speed change data tables. GT and the area A of the power turbine guide PT As candidate A GT and A PT .
[0065] In this embodiment, after calculating the temperature margin, power margin, fuel consumption rate margin, and speed margin of the turboshaft engine based on the initial performance values and relevant constraints, the temperature margin, power margin, fuel consumption rate margin, and speed margin are then compared with the combustion gas temperature change data T. t4.5 Power change data △P, fuel consumption rate change data △sfc, speed change data △n g The size relationship is set to filter and obtain the candidate A that meets the requirements. GT and A PT Its advantage lies in obtaining the adjustment amount of the gas turbine and power turbine guide vanes that meet the constraints through screening.
[0066] Preferably, the calculation of the temperature margin, power margin, fuel consumption margin, and speed margin of the turboshaft engine based on the initial values of relevant performance characteristics and relevant constraints specifically includes:
[0067] Calculate the power margin: ΔP _m =P _0 / P_ limit -1;
[0068] Calculate the gas temperature margin: △T t4.5_m =T t4.5_0 / T t4.5_limit -1;
[0069] Calculate the fuel consumption margin △sfc _m =sfc _0 / sfc_ limit -1;
[0070] Calculate the speed margin Δn g_m =n g_0 / n g _ limit -1.
[0071] Preferably, such as Figure 3As shown, the gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed change data that simultaneously satisfy the set magnitude relationship is obtained by two-dimensional linear interpolation from the temperature, power, fuel consumption rate, and speed change data tables based on temperature margin, power margin, fuel consumption rate margin, speed margin, and set magnitude relationship. GT and the area A of the power turbine guide PT As candidate A GT and A PT The specific steps include:
[0072] S321. If there exists a ΔP in the power change table that satisfies: ΔP + ΔP _m If ≥0, then the two-dimensional linear interpolation in the power change table yields A that satisfies the condition. GT A PT ;
[0073] S322, If the gas temperature change table contains T t4.5 Satisfy: T t4.5 +△T t4.5_m If ≤0, then the two-dimensional linear interpolation in the gas temperature change table will yield A that satisfies the condition. GT A PT ;
[0074] S323. If the fuel consumption rate change table contains a Δsfc that satisfies: Δsfc + Δsfc _m If ≤0, then A is obtained by two-dimensional linear interpolation in the fuel consumption rate change table, which satisfies the condition. GT A PT ;
[0075] S324. If the fuel consumption rate change table contains Δn g Satisfy: △n g +△n g_m If ≤0, then the two-dimensional linear interpolation in the speed variation table yields A that satisfies the condition. GT A PT ;
[0076] S325. A that simultaneously meets the above conditions... GT A PT As candidate A GT and A PT .
[0077] This embodiment provides a method for selecting candidate A from the table of temperature, power, fuel consumption rate, and speed variation data. GT and A PT The specific process, in which candidate A GT and A PTThe turbine must meet the relevant requirements for power change, gas temperature change, fuel consumption rate change, and speed change. Its purpose and benefit is to ensure that the performance of the turbine guide is up to standard after adjustment.
[0078] Preferably, the selection from candidate A GT and A PT In the process of optimization, the area A of the gas turbine guide vane is found. GT and the area A of the power turbine guide PT The minimum adjustment amount is used for the performance testing of turboshaft engines on ground test benches, and the specific steps include:
[0079] From candidate A GT and A PT Selected from The minimum value corresponds to A GT and A PT As the area A of the gas turbine guide vane GT and the area A of the power turbine guide PT The minimum adjustment amount is used for performance testing of turboshaft engines on ground test benches.
[0080] This embodiment is illustrated by... Minimum value to select the corresponding A GT and A PT The purpose and benefit of using the minimum adjustment amount for ground test bench performance debugging of turboshaft engines is to obtain the minimum adjustment amount that comprehensively considers the gas turbine and power turbine guide vanes by screening the areas of the gas turbine and power turbine guide vanes.
[0081] For example, during the ground test bench performance debugging of a 400kW turboshaft engine, ΔP = -7%, ΔT t4.5 =-7%, △sfc=-5%, △n g =0.
[0082] When using the turboshaft engine ground test bench performance debugging method based on turbine guide area provided in the above embodiments, the data in Tables 1 to 4 above are first calculated using the existing overall performance calculation model of the project. Finally, according to the tables, the minimum adjustment amount of the gas turbine guide area and the power turbine guide area can be obtained as: A GT =+2%, A PT =-2%, Table 5 shows the actual parameters of the engine after assembling the gas turbine guide and power turbine guide according to the minimum adjustment amount. It can be seen that this method improves the power of the small turboshaft engine by calculating the minimum adjustment amount of the gas turbine guide and power turbine guide, and at the same time, when debugging according to the minimum adjustment amount, the speed of the gas generator can be controlled within the limit range. Table 5
[0083] Parameter name deviation Gas turbine guide vane area 2％ Power turbine guide area -2％ power +7％ temperature +4％ rotational speed constant fuel consumption rate +0.4％
[0084] like Figure 4 As shown, another preferred embodiment of this application also provides a ground-based performance testing device for a turboshaft engine based on the area of the turbine guide vane, comprising:
[0085] The temperature and power variation data acquisition module is used to obtain the gas turbine guide area A under the same gas generator physical speed by configuring an overall performance calculation model with different gas turbine and power turbine guide areas. GT and the area A of the power turbine guide PT Corresponding gas temperature change data △T t4.5 The power change data ΔP is used to generate tables for gas temperature change and power change, respectively.
[0086] The fuel consumption rate and engine speed variation data acquisition module is used to obtain the gas turbine guide area A under the same takeoff power conditions by configuring an overall performance calculation model with different gas turbine and power turbine guide areas. GT and the area A of the power turbine guide PT The corresponding fuel consumption rate change data △sfc and speed change data △n g And separate tables were generated for fuel consumption rate changes and engine speed changes;
[0087] The filtering module is used to obtain the gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed change data that simultaneously meet the relevant constraints from the gas temperature change table, power change table, fuel consumption rate change table, and speed change table using two-dimensional linear interpolation. GT and the area A of the power turbine guide PT As candidate A GT and A PT ;
[0088] The minimum value optimization module is used to find the minimum value from the candidate A. GT and A PT In the process of optimization, the area A of the gas turbine guide vane is found. GT and the area A of the power turbine guide PT The minimum adjustment amount is used as the performance debugging parameter for the turboshaft engine on the ground test bench.
[0089] like Figure 5 As shown, a preferred embodiment of this application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the program, it implements the steps of the turboshaft engine ground test bench performance debugging method based on turbine guide area in the above embodiments.
[0090] like Figure 6As shown, a preferred embodiment of this application also provides a computer device, which may be a terminal or a liveness detection server, and its internal structure diagram may be as follows. Figure 6 As shown, the computer device includes a processor, memory, and a network interface connected via a system bus. The processor provides computing and control capabilities. The memory includes a non-volatile storage medium and internal memory. The non-volatile storage medium stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs stored in the non-volatile storage medium. The network interface is used to communicate with other external computer devices via a network connection. When the computer program is executed by the processor, it implements the steps of the aforementioned method for performance debugging of a turboshaft engine on a ground test bench based on the turbine guide vane area.
[0091] Those skilled in the art will understand that Figure 6 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the computer device to which the present application is applied. Specific computer devices may include more or fewer components than those shown in the figure, or combine certain components, or have different component arrangements.
[0092] A preferred embodiment of this application also provides a storage medium, the storage medium including a stored program, which, when the program is executed, controls the device where the storage medium is located to perform the steps of the turboshaft engine ground test bench performance debugging method based on turbine guide area in the above embodiments.
[0093] It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions, and although a logical order is shown in the flowchart, in some cases the steps shown or described may be executed in a different order than that shown here.
[0094] If the functions described in this embodiment are implemented as software functional units and sold or used as independent products, they can be stored in one or more computing device-readable storage media. Based on this understanding, the parts of this application's embodiments that contribute to the prior art or the technical solutions can be embodied in the form of a software product. This software product is stored in a storage medium and includes several instructions to cause a computing device (which may be a personal computer, server, mobile computing device, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage media include: USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, optical disks, and other media capable of storing program code.
[0095] Those skilled in the art will understand that embodiments of this application can be provided as methods, systems, or computer program products. Therefore, this application can take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, this application can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code. The solutions in the embodiments of this application can be implemented in various computer languages, such as the object-oriented programming language Java and the interpreted scripting language JavaScript.
[0096] This application is described with reference to flowchart illustrations and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of this application. It will be understood that each block of the flowchart illustrations and / or block diagrams, and combinations of blocks in the flowchart illustrations and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, generate instructions for implementing the flowchart... Figure 1 One or more processes and / or boxes Figure 1 A device that provides the functions specified in one or more boxes.
[0097] These computer program instructions may also be stored in a computer-readable storage medium that can direct a computer or other programmable data processing device to function in a particular manner, such that the instructions stored in the computer-readable storage medium produce an article of manufacture including instruction means, which are implemented in a process Figure 1 One or more processes and / or boxes Figure 1 The function specified in one or more boxes.
[0098] These computer program instructions may also be loaded onto a computer or other programmable data processing equipment to cause a series of operational steps to be performed on the computer or other programmable equipment to produce a computer-implemented process, thereby providing instructions that execute on the computer or other programmable equipment for implementing the process. Figure 1 One or more processes and / or boxes Figure 1 The steps of the function specified in one or more boxes.
[0099] Although preferred embodiments of this application have been described, those skilled in the art, upon learning the basic inventive concept, can make other changes and modifications to these embodiments. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments as well as all changes and modifications falling within the scope of this application.
[0100] Obviously, those skilled in the art can make various modifications and variations to this application without departing from the spirit and scope of this application. Therefore, if such modifications and variations fall within the scope of the claims of this application and their equivalents, this application also intends to include such modifications and variations.
Claims
1. A method for ground-based performance testing of a turboshaft engine based on the area of the turbine guide vane, characterized in that, Including the following steps: By configuring overall performance calculation models with different gas turbine and power turbine guide vane areas, the results of different gas turbine guide vane areas A under the same gas generator physical speed are obtained. GT and the area A of the power turbine guide PT Corresponding gas temperature change data △T t4.5 The power change data ΔP is used to generate tables for gas temperature change and power change, respectively. By configuring overall performance calculation models with different gas turbine and power turbine guide vane areas, the different gas turbine guide vane areas A under the same takeoff power conditions are obtained. GT and the area A of the power turbine guide PT The corresponding fuel consumption rate change data △sfc and speed change data △n g And separate tables were generated for fuel consumption rate changes and engine speed changes; The gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed change data that simultaneously satisfy the relevant constraints can be obtained by two-dimensional linear interpolation from the gas temperature change table, power change table, fuel consumption rate, and speed change table. GT and the area A of the power turbine guide PT As candidate A GT and A PT ; From candidate A GT and A PT In the process of optimization, the area A of the gas turbine guide vane is found. GT and the area A of the power turbine guide PT The minimum adjustment amount is used for performance testing of turboshaft engines on ground test benches.
2. The method for ground-based performance testing of a turboshaft engine based on turbine guide vane area according to claim 1, characterized in that, The different gas turbine guide area A GT and the area A of the power turbine guide PT The interval between changes is 1%.
3. The method for ground-based performance testing of a turboshaft engine based on turbine guide vane area according to claim 1, characterized in that, The gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed change data that simultaneously satisfy the relevant constraints can be obtained by two-dimensional linear interpolation from the gas temperature change table, power change table, fuel consumption rate, and speed change table. GT and the area A of the power turbine guide PT As candidate A GT and A PT The specific steps include: Based on the initial performance values and relevant constraints of the turboshaft engine, the temperature margin, power margin, fuel consumption rate margin, and speed margin of the turboshaft engine are calculated. The relevant constraints include: at 1.0 speed, the power output is greater than or equal to the target value P_. limit T t4.5 Less than or equal to temperature value T t4.5_limit Under the specified power conditions, the fuel consumption rate is less than or equal to the specified value sfc_ limit The relevant initial performance values include: initial power value P. _0 Initial gas temperature T t4.5_0 Initial fuel consumption rate (sfc_0), engine speed (n) g _0 ; Based on the temperature margin, power margin, fuel consumption rate margin, speed margin, and set magnitude relationships, the gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed change data that simultaneously satisfy the set magnitude relationships is obtained through two-dimensional linear interpolation from the temperature, power, fuel consumption rate, and speed change data tables. GT and the area A of the power turbine guide PT As candidate A GT and A PT .
4. The method for ground-based performance testing of a turboshaft engine based on turbine guide vane area according to claim 3, characterized in that, The calculation of the temperature margin, power margin, fuel consumption margin, and speed margin of the turboshaft engine based on the initial values of its relevant performance and constraints specifically includes: Calculate the power margin: ΔP _m = P _0 / P_ limit -1; Calculate the gas temperature margin: △T t4.5_m =T t4.5_0 / T t4.5_limit -1; Calculate the fuel consumption margin △sfc _m =sfc _0 / sfc limit -1; Calculate the speed margin Δn g_m =n g _0 / n g limit -1.
5. The method for ground-based performance testing of a turboshaft engine based on turbine guide vane area according to claim 4, characterized in that, The gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed variation data that simultaneously satisfy the set magnitude relationship is obtained by two-dimensional linear interpolation from the temperature, power, fuel consumption rate, and speed variation data tables, based on temperature margin, power margin, fuel consumption rate, and speed margin, respectively. GT and the area A of the power turbine guide PT As candidate A GT and A PT The specific steps include: If there exists a ΔP in the power change table that satisfies: ΔP + ΔP _m If ≥ 0, then the two-dimensional linear interpolation in the power change table will yield A that satisfies the condition. GT A PT ; If the gas temperature change table contains ΔT t4.5 Satisfy: T t4.5 +△T t4.5_m If ≤0, then the two-dimensional linear interpolation in the gas temperature change table will yield A that satisfies the condition. GT A PT ; If the fuel consumption rate change table contains a Δsfc that satisfies: Δsfc + Δsfc _m If ≤0, then A is obtained by two-dimensional linear interpolation in the fuel consumption rate change table, which satisfies the condition. GT A PT ; If the fuel consumption rate change table contains Δn g Satisfy: △n g +△n g_m If ≤0, then the two-dimensional linear interpolation in the speed variation table will yield A that satisfies the condition. GT A PT ; A that simultaneously meets the above conditions GT A PT As candidate A GT and A PT .
6. The method for ground-based performance testing of a turboshaft engine based on turbine guide vane area according to claim 1, characterized in that, The candidate A GT and A PT In the process of optimization, the area A of the gas turbine guide vane is found. GT and the area A of the power turbine guide PT The minimum adjustment amount is used for the performance testing of turboshaft engines on ground test benches, and the specific steps include: From candidate A GT and A PT Selected from The minimum value corresponds to A GT and A PT As the area A of the gas turbine guide vane GT and the area A of the power turbine guide PT The minimum adjustment amount is used for performance testing of turboshaft engines on ground test benches.
7. A ground-based performance testing device for a turboshaft engine based on the area of a turbine guide vane, characterized in that, include: The temperature and power variation data acquisition module is used to obtain the gas turbine guide area A under the same gas generator physical speed by configuring an overall performance calculation model with different gas turbine and power turbine guide areas. GT and the area A of the power turbine guide PT Corresponding gas temperature change data △T t4.5 The power change data ΔP is used to generate tables for gas temperature change and power change, respectively. The fuel consumption rate and engine speed variation data acquisition module is used to obtain the gas turbine guide area A under the same takeoff power conditions by configuring an overall performance calculation model with different gas turbine and power turbine guide areas. GT and the area A of the power turbine guide PT The corresponding fuel consumption rate change data △sfc and speed change data △n g And separate tables were generated for fuel consumption rate changes and engine speed changes; The filtering module is used to obtain the gas turbine guide area A corresponding to the temperature, power, fuel consumption rate, and speed change data that simultaneously meet the relevant constraints from the gas temperature change table, power change table, fuel consumption rate change table, and speed change table using two-dimensional linear interpolation. GT and the area A of the power turbine guide PT As candidate A GT and A PT ; The minimum value optimization module is used to find the minimum value from the candidate A. GT and A PT In the process of optimization, the area A of the gas turbine guide vane is found. GT and the area A of the power turbine guide PT The minimum adjustment amount is used as the performance debugging parameter for the turboshaft engine on the ground test bench.
8. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, characterized in that, When the processor executes the program, it implements the steps of the ground test bench performance debugging method for turboshaft engines based on turbine guide area as described in any one of claims 1 to 6.
9. A storage medium comprising a stored program, characterized in that, When the program is running, it controls the device containing the storage medium to perform the steps of the ground test bench performance debugging method for turboshaft engines based on turbine guide area as described in any one of claims 1 to 6.