Method and device for generating real characteristics of high-pressure turbine of aero-engine

Abstract

The invention discloses a method and device for generating real characteristics of a high-pressure turbine of an aero-engine. In one embodiment, a design characteristic diagram of the high-pressure turbine can be obtained, and performance data of at least two test points with different expansion ratios of the high-pressure turbine at a conversion rotating speed in a performance test can be obtained. A design point corresponding to the performance data of the test point under the conversion rotating speed in the design characteristic diagram can be determined. A plurality of performance data at a plurality of converted speeds may be generated based on differences between the performance data of the design points and the performance data of the corresponding test points, and true characteristic maps of the high pressure turbine at the plurality of converted speeds are generated based on the plurality of performance data. According to the method, the actual characteristic diagram of the turbine component can be quickly generated through parameters such as deviation or convergence coefficients based on the design characteristic diagram and two (or more) actual performance test results.

Description

Technical Field

[0001] The present invention relates to the field of aircraft engines, and in particular to a method and a device for generating true characteristics of a high-pressure turbine of an aircraft engine. Background Art

[0002] Aircraft engines are sophisticated and complex turbine machinery products, and their internal airflow channels have a significant impact on engine performance. Therefore, the geometric dimensions of rotating parts are usually carefully designed and strictly controlled during the manufacturing process. In the actual manufacturing process, due to the combined influence of multiple manufacturing uncertainties, such as processing equipment errors, thermal deformation errors, force deformation errors, positioning errors, etc., the dimensions of parts will have certain deviations. This geometric deviation inevitably changes the flow of air in the internal flow channel of the engine, causing it to deviate from the ideal design state, thereby affecting engine performance.

[0003] As the aviation industry pays more attention to digital twin technology, how to build a high-fidelity digital twin of each engine determines the benefits of product operation and maintenance. Affected by manufacturing uncertainty, both key geometric parameters and overall performance parameters show scattered characteristics within a certain range, and this scattered characteristic is random, which poses a challenge to building a high-fidelity digital twin of the product.

[0004] Current research focuses on the impact of key parameters of turbine blades on performance, such as tip radius and tip clearance, blade surface roughness, throat area, etc. Most studies use CFD simulation methods to study the influence of a single factor on turbine aerodynamic performance. However, in actual engineering applications, obtaining the actual characteristics of components often requires a large number of tests, which imposes a serious burden on generating the true characteristics of aircraft engine high-pressure turbines. In addition, if the performance obtained through the test deviates too much from the design performance, rework is required, which affects the efficiency of engine design and production. There is currently no method to correct component characteristics for geometric parameter uncertainty.

[0005] Therefore, there is a need in the art for an improved method and apparatus for generating realistic characteristics of an aircraft engine high pressure turbine. Summary of the invention

[0006] The present invention proposes an improved method and device for generating the real characteristics of an aircraft engine high-pressure turbine. Based on the design characteristic diagram of the turbine and the results of two (or more) performance tests of the actual turbine, the present invention generates the actual characteristic diagram of the turbine within a certain geometric deviation range according to similarity theory, and provides real model information for the digital twin. In addition, by calculating the deviation between the actual characteristic diagram and the design characteristic diagram, it is determined whether the turbine performance meets the standard, which can simplify the test process of the turbine performance and quickly complete the evaluation of the turbine performance deviation.

[0007] In one embodiment of the present invention, a method for generating true characteristics of a high-pressure turbine of an aircraft engine is provided, comprising: obtaining a design characteristic diagram of the high-pressure turbine; obtaining performance data of at least two test points of the high-pressure turbine having different expansion ratios at a converted speed in a performance test; determining at least two design points in the design characteristic diagram having the different expansion ratios at the converted speed; generating a plurality of performance data at a plurality of converted speeds based on differences between the at least two design points and the corresponding performance data of the at least two test points; and generating a true characteristic diagram of the high-pressure turbine at the plurality of converted speeds based on the at least two test point performance data and the generated plurality of performance data.

[0008] In one aspect, generating multiple performance data at multiple converted speeds further includes: determining a deviation vector based on the difference between one or more design points of the at least two design points and the corresponding test point performance data; determining a deviation matrix at the multiple converted speeds based on the deviation vector; and generating multiple performance data at the multiple converted speeds based on the design characteristic diagram and the deviation matrix.

[0009] In one aspect, determining the deviation matrix at the multiple converted speeds according to the deviation vector further includes: generating a corresponding deviation vector at each converted speed in the multiple converted speeds according to the deviation vector based on an empirical function of deviations between different converted speeds, the deviation matrix including the corresponding deviation vector at each converted speed in the multiple converted speeds.

[0010] In one aspect, generating multiple performance data at multiple converted speeds further includes: determining a convergence coefficient of the difference as the difference changes with the expansion ratio based on the difference between the performance data of the at least two design points and the corresponding at least two test points, and generating multiple performance data based on the convergence coefficient changing with the expansion ratio at each of the multiple converted speeds based on the design characteristic diagram and the deviation matrix.

[0011] In one aspect, the at least two test point performance data and each of the plurality of performance data include a scaled flow rate and / or an efficiency.

[0012] In one aspect, the at least two design points are determined by interpolating in the design characteristic map.

[0013] In one aspect, a deviation between the design characteristic map and the actual characteristic map is determined to determine whether the performance of the high-pressure turbine meets the requirements.

[0014] In one aspect, the deviation between the designed characteristic map and the actual characteristic map comprises an average value, a weighted value, or a maximum value of the deviations at a plurality of performance points.

[0015] In one embodiment of the present invention, a device for generating real characteristics of a high-pressure turbine of an aircraft engine is provided, comprising: a memory for storing processor-executable instructions; and a processor coupled to the memory, wherein the processor is configured to implement a method for generating real characteristics of a high-pressure turbine of an aircraft engine as described in any one of the above when executing the processor-executable instructions.

[0016] In one embodiment of the present invention, there is provided an apparatus for generating the real characteristics of a high-pressure turbine of an aircraft engine, comprising: a data acquisition module, configured to acquire a design characteristic diagram of the high-pressure turbine, and to acquire performance data of at least two test points of the high-pressure turbine having different expansion ratios at a converted speed in a performance test; an interpolation module, configured to determine at least two design points in the design characteristic diagram having the different expansion ratios at the converted speed; a performance data generation module, configured to generate a plurality of performance data at a plurality of converted speeds according to differences between the at least two design points and the corresponding performance data of the at least two test points; and a characteristic diagram generation module, configured to generate the real characteristic diagram of the high-pressure turbine at the plurality of converted speeds based on the at least two test point performance data and the generated plurality of performance data.

[0017] The present invention is based on the design characteristic diagram and two (or more) actual performance test results, and quickly generates the actual characteristic diagram of the turbine component through parameters such as deviation and convergence coefficient. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 The present invention is a flowchart of a method for generating real characteristics of a high-pressure turbine of an aircraft engine according to an embodiment of the present invention.

[0019] Figure 2 1 is a diagram showing the relationship between the converted flow rate and the expansion ratio according to a high-pressure turbine design characteristic diagram according to an embodiment of the present invention.

[0020] Figure 3 1 is a diagram illustrating the relationship between efficiency and expansion ratio of a high-pressure turbine design characteristic according to an embodiment of the present invention.

[0021] Figure 4 This is the relationship between the converted flow rate and the expansion ratio in the actual generated characteristic diagram according to one embodiment of the present invention.

[0022] Figure 5 This is the relationship between efficiency and expansion ratio in a characteristic diagram actually generated according to an embodiment of the present invention.

[0023] Figure 6 The invention is a block diagram of an apparatus for generating real characteristics of a high-pressure turbine of an aircraft engine according to an embodiment of the present invention. DETAILED DESCRIPTION

[0024] The present invention will be further described below in conjunction with specific embodiments and drawings, but the protection scope of the present invention shall not be limited thereto.

[0025] The present invention proposes a characteristic generation algorithm based on the turbine design characteristic map and two (or more) performance test results of the actual turbine, which can quickly generate the actual characteristic map of the turbine. The characteristic map is a curve used to describe the relationship between the converted flow rate and efficiency and the expansion ratio under a series of equal converted speed lines for turbine performance.

[0026] Compared with the existing technology that requires a large number of tests to obtain performance parameters, the present invention can generate the real complete characteristics of the components through a small amount of test data, provide real model information for the digital twin, and improve the accuracy of the whole machine performance evaluation. Preferably, during the performance test after the engine is assembled, due to the influence of various manufacturing uncertainties, the overall performance will have a certain dispersion. The deviation between the actual characteristic diagram and the design characteristic diagram can be used to determine whether its performance meets the standard, effectively reducing the time for component performance evaluation.

[0027] Figure 1 1 is a flow chart of a method 100 for generating real characteristics of a high-pressure turbine of an aircraft engine according to an embodiment of the present invention. The method 100 may be executed by a computer, a processor, a server, a controller, a cloud service, etc. The characteristics of the high-pressure turbine may be described by a characteristic diagram, wherein the characteristic diagram may show, for example, the converted speed π k , converted flow rate ρ k , efficiency ε k , expansion ratio θ k Although the present invention describes a characteristic diagram, it should be understood that the characteristic diagram may also be non-graphical, but may be expressed by corresponding data.

[0028] In step 101, a design characteristic map of a high pressure turbine may be obtained. The design characteristic map may describe the desired / designed converted speed π k , converted flow rate ρ k , efficiency ε k , expansion ratio θ k For example, the design characteristic diagram can be composed of M design performance points P k (π k ,ρ k ,ε k ,θ k)(k=1,…,M) is drawn, and the specific form is as follows Figure 2 and Figure 3 shown. Specifically, Figure 2 The relationship between the expansion ratio and the converted flow rate at different conversion speeds n is shown, with the horizontal axis being the expansion ratio and the vertical axis being the converted flow rate. Each curve shows the change of the converted flow rate with the expansion ratio at different conversion speeds n. Figure 3 The relationship between the expansion ratio and the efficiency at different conversion speeds n is shown, with the horizontal axis being the expansion ratio and the vertical axis being the efficiency. Each curve shows the change of the efficiency with the expansion ratio at different conversion speeds n.

[0029] In step 102, the actual test performance point parameters may be obtained. For example, the high pressure turbine may be tested multiple times to obtain test results. In one embodiment, the test results of two (or more) tests of the high pressure turbine at the same converted speed in the actual performance test may be obtained. For example, the high pressure turbine performance point Q may be obtained for each test. i (π i ,ρ i ,ε i ,θ i )(i=1,2…). As an example but not a limitation, test data of at least two tests of the high-pressure turbine with different expansion ratios θ at a certain conversion speed π may be obtained, such as performance data of a first test point with a first expansion ratio and performance data of a second test point with a second expansion ratio (see Figure 4 , Figure 5 The test point performance data may represent the flow rate ρ and / or efficiency ε at the corresponding converted speed π and expansion ratio θ.

[0030] In step 103, a design performance point on the design performance diagram corresponding to the test performance point may be determined. As described above, the design performance diagram may show the relationship between the expansion ratio and the converted flow rate / efficiency at different converted speeds n. Accordingly, a corresponding design performance point on the design performance diagram having the same converted speed and expansion ratio as the test performance point may be found, such as a first design point having a first expansion ratio and a second design point having a second expansion ratio at a converted speed π.

[0031] In one embodiment, a linear interpolation method can be used to find the point Q corresponding to the test performance point on the design characteristic diagram. i The corresponding design performance point Q i (π i ,ρ i ,ε i ,θ i )(i=1,2…). Taking two test points as an example, according to the test requirements, the conversion speed of the two test points is π 1 =π 2 , corresponding to Q iThe conversion speed π i =π 1 , find all the converted speeds π in the design characteristic diagram 1 Performance point P k (π k =π 1 ), linear interpolation is performed based on the expansion ratio to satisfy θ i =θ i , at performance point P k (π k =π 1 ) to find the expansion ratio that satisfies θ m ≤θ i ≤θ n Design performance point P m (π m ,ρ m ,ε m ,θ m ) and P n (π n ,ρ n ,ε n ,θ n ), then the interpolation calculation formula for the converted flow is:

[0032]

[0033] The interpolation formula for efficiency is:

[0034]

[0035] According to the above formula, the design performance point Q can be determined i (π i ,ρ i ,ε i ,θ i )(i=1,2…).

[0036] In step 104 , a plurality of performance data at a plurality of converted speeds may be generated according to the difference between the design performance point and the performance data of the corresponding test point.

[0037] Based on the non-deterministic analysis of the performance of high-pressure turbine components of aircraft engines, when the geometric parameters of turbine components are dispersed within a certain range (such as the deviation of the tip clearance of the moving blades ±0.2mm, the deviation of the torsion angle of the guide vanes ±2°), according to the similarity theory, its real characteristics have a similar variation trend to the design characteristics. For example, the difference between the design performance point and the corresponding test point performance data at the experimental conversion speed can be extended to the difference between the design performance point and the corresponding test point performance data at different conversion speeds.

[0038] As an example but not limitation, in sub-step 105, the deviation vector may be determined according to the difference between the performance data of the design point and the corresponding test point at the experimental conversion speed.

[0039] For example, taking the test point Q 1 As the conversion speed π 1 The reference point under the deviation vector can be (π 1 ,α π1 ,β π1 ,θ 1 )=(π 1 ,(ρ 1 -ρ 1 ),(ε 1 -ε 1 ),θ 1 ). Similarly, for each performance test point at the test conversion speed, the corresponding deviation vector can be obtained.

[0040] In sub-step 106, a deviation matrix under multiple converted speeds may be determined according to the deviation vector. In one embodiment, according to the deviation empirical function between different converted speeds, a corresponding deviation vector under each of the multiple converted speeds may be generated based on the deviation vector between the design point and the test point under the experimental converted speed, and these deviation vectors may constitute a deviation matrix.

[0041] For example, based on historical knowledge or expert experience, the deviation vector at different conversion speeds can be generated according to the deviation vector at the experimental conversion speed, such as the conversion flow deviation Deviation from efficiency As an example and not a limitation, the conversion speed π k The calculation formula for the converted flow deviation is:

[0042]

[0043] Conversion speed π k The calculation formula for the lower efficiency deviation is:

[0044]

[0045] In the formula, For the conversion between different conversion speeds, (ρ 1 -ρ 1 ) and (ε 1 -ε 1 ) are the flow deviation and efficiency deviation under the test conversion speed, f(π k -π 1 ) and g(π k -π 1) is a historical knowledge or expert experience function with the conversion speed difference as a variable, which is used to correct the deviation between different conversion speeds. According to experience, as an example and not a limitation, in the present invention, f(π k -π 1 )=rand1, rand1 is a normal distribution N(0,0.1·|π k -π 1 |) random number; g(π k -π 1 )=rand2, rand2 is a normal distribution N(0,0.15·|π k -π 1 |) random number. Based on the A different converted speeds in the characteristic diagram, according to the above formula, Q 1 As the conversion speed π 1 By taking the reference point under the multiple conversion speeds, the corresponding deviation vector under each conversion speed is generated, and the deviation matrix under the multiple conversion speeds can be obtained:

[0046]

[0047] The matrix represents the 1 Under different conversion speeds, the conversion flow deviation and efficiency deviation. Similarly, with other test points Q i As the conversion speed π 1 The reference points under other expansion ratios θ can be generated i The deviation matrix under multiple converted speeds.

[0048] In sub-step 107, multiple performance data at multiple converted speeds are generated based on the design characteristic diagram and the deviation matrix. Since the deviation matrix provides deviations from the design characteristics at multiple converted speeds, the design characteristic diagram and the deviation matrix are added to obtain multiple performance data at multiple converted speeds.

[0049] In one embodiment, according to the design characteristic diagram and the multiple deviation matrices generated based on the multiple test points, multiple performance data can be generated at each converted speed. Figure 1 One-to-one generation of actual characteristic graph P k (π k ,ρ k ,ε k ,θ k )(k=1,…,M), where the correspondence between the actual characteristic diagram and the design characteristic diagram is determined by the conversion speed and the expansion ratio, that is, for all actual performance points:

[0050]

[0051] Therefore, the subsequent calculation only needs to obtain the converted flow and efficiency of each performance point based on the deviation matrix. The calculation formula for the converted flow of the actual performance point is:

[0052]

[0053] The efficiency calculation formula for the actual performance point is:

[0054]

[0055] where ρ k is the converted flow rate at the design performance point, is the flow deviation, ε k is the efficiency of the design performance point, is the efficiency deviation.

[0056] Then, in step 110, a real characteristic diagram of the high pressure turbine at multiple converted speeds may be generated based on the test point performance data and the generated multiple performance data. For example, the actual characteristic diagram P may be calculated for all points in the design characteristic diagram. k (π k ,ρ k ,ε k ,θ k )(k=1,…,M).

[0057] In another embodiment of step 104, as shown in optional sub-step 108, a convergence coefficient of the difference as the expansion ratio changes may be determined based on the difference between the plurality of design points and the corresponding test points. The convergence coefficient may represent a trend of the difference (deviation) between the design point and the corresponding test point as the expansion ratio changes. In this case, step 107 may include adjusting a plurality of performance data at a plurality of converted speeds generated based on one or more test points based on the convergence coefficient.

[0058] As an example and not a limitation, taking two performance points as an example, the design performance point Q i (i=1,2) and test performance point Q i (i=1,2) Calculate the conversion flow convergence coefficient And the efficiency convergence coefficient ω. The calculation formula for the conversion flow convergence coefficient is:

[0059]

[0060] The calculation formula of efficiency convergence coefficient is:

[0061]

[0062] With more test performance points and corresponding design points, a more accurate convergence coefficient can be calculated, where the contribution of each performance point to the convergence coefficient can be adjusted by different parameters (coefficients).

[0063] Subsequently, according to the deviation matrix, the convergence coefficient, and the design characteristics Figure 1 generate the actual characteristic diagram P one-to-one k (π k , ρ k , ε k , θ k )(k = 1, …, M), where the correspondence between the actual characteristic diagram and the design characteristic diagram is determined by the conversion speed and the expansion ratio, that is, for all actual performance points:

[0064]

[0065] Therefore, only need to obtain the conversion flow rate and efficiency of each performance point according to the convergence coefficient and the deviation matrix. The conversion flow rate calculation formula for the actual performance point is:

[0066]

[0067] The efficiency calculation formula for the actual performance point is:

[0068]

[0069] Among them and (θ k - θ 1 )·ω·π k is an adjustment term based on the convergence coefficient, which can vary with the expansion ratio.

[0070] In this case, only need to test or select the parameters of two test performance points and calculate the convergence coefficient, select one of the actual performance points to calculate the deviation matrix, and generate multiple performance data based on the convergence coefficient varying with the expansion ratio at each conversion speed among multiple conversion speeds based on the design characteristic diagram and the deviation matrix, then multiple performance data at each conversion speed among multiple conversion speeds can be generated. The calculation process is simple and convenient, and when the geometric parameters are within a small variation range, the evaluation accuracy is relatively high.

[0071] In the case of having more than two test performance points, it is also possible to adjust the multiple deviation matrices at each conversion speed based on the convergence coefficient, so as to generate more accurate performance data varying with the expansion ratio at the corresponding conversion speed. For example, the expansion ratio can be divided into intervals based on the test performance points, and each expansion ratio interval can have at least two test performance points. Correspondingly, the deviation matrix and the convergence coefficient can be calculated for each expansion ratio interval, and multiple performance data at each conversion speed in this expansion ratio interval among multiple conversion speeds can be generated based on the deviation matrix and the convergence coefficient of each expansion ratio interval. In addition, the convergence coefficients of each expansion ratio interval can be adjusted with reference to each other.

[0072] Then, in step 110, a real characteristic diagram of the high pressure turbine at multiple converted speeds may be generated based on the test point performance data and the generated multiple performance data. The actual characteristic diagram P may be calculated for all points in the design characteristic diagram. k (π k ,ρ k ,ε k ,θ k )(k=1,…,M).

[0073] Figure 4 This is the relationship between the converted flow rate and the expansion ratio in the actual generated characteristic diagram according to one embodiment of the present invention. Figure 5 is the relationship between efficiency and expansion ratio in a characteristic diagram actually generated according to one embodiment of the present invention. Figure 4 and Figure 5 In FIG. 1 , the solid line represents the design characteristics at different conversion speeds, and the dotted line represents the characteristics of the actual characteristic diagram generated according to the present invention at different conversion speeds. It can be seen that the design characteristics and the actual characteristics at the same conversion speed are similar, and their deviations change with the expansion ratio.

[0074] Back to Figure 1 Optionally, in step 112, the actual characteristic map P is calculated k Design characteristics diagram P k For example, in step 114, it can be determined whether the performance of the high-pressure turbine meets the requirements based on the acceptable standard value of the high-pressure turbine.

[0075] Based on the actual characteristic diagram P k From the calculation process, it can be seen that the conversion speed and expansion ratio of the design characteristic diagram performance point and the actual characteristic diagram performance point are the same, so only the deviation of the conversion flow and efficiency needs to be calculated, which simplifies the calculation difficulty. k The deviation consists of two parts, one of which is the conversion flow deviation f k , part of which is the efficiency deviation e k , and its calculation formula is:

[0076]

[0077] In one embodiment, the average value or weighted value of the deviations of multiple performance points may be taken as the deviation value δ of the entire characteristic diagram.

[0078] In another embodiment, considering the different effects of the converted flow rate and efficiency on the overall performance, the point with the largest deviation among all the performance points is taken as the deviation value of the entire characteristic diagram, and the calculation formula of the deviation δ of the entire characteristic diagram is:

[0079]

[0080] Where μf With μ e are the conversion coefficients for flow deviation and efficiency deviation respectively, and their values ​​can be obtained based on the sensitivity analysis of the overall performance design scheme.

[0081] According to the allowable variation range of the geometric parameters of the high-pressure turbine components and the product qualification inspection standards, the acceptable compliance value for the high-pressure turbine is Δ. If δ≤Δ, it means that the performance of the high-pressure turbine meets the requirements. Otherwise, it does not meet the requirements and should be returned for repair.

[0082] As described above, the present invention proposes a solution for evaluating component performance based on characteristic diagram deviation. At present, the main method for evaluating the performance of high-pressure turbine components still requires a large number of tests. The present invention calculates the converted flow deviation and efficiency deviation of each performance point based on the generated actual characteristic diagram and integrates their performance differences, selects the maximum value and compares it with the set standard value, determines whether the component performance meets the standard, and simplifies the test verification process.

[0083] In addition, it should be understood that the various calculation formulas given in the present invention are only examples and not limitations. In specific implementations, reasonable calculation methods and parameters can be selected or designed according to needs or actual conditions, and are not limited to the specific formulas given in this article.

[0084] Figure 6 is a block diagram of an apparatus 600 for generating real characteristics of a high-pressure turbine of an aircraft engine according to an embodiment of the present invention.

[0085] The device 600 may include a data acquisition module 602, which may be configured to acquire a design characteristic diagram of the high-pressure turbine, and acquire at least two test point performance data of the high-pressure turbine with different expansion ratios at a converted speed during a performance test. For example, the test data may include at least first test point performance data of a first expansion ratio and second test point performance data of a second expansion ratio, and so on.

[0086] The apparatus 600 may further include an interpolation module 604, which may be configured to determine a design point in the design characteristic diagram corresponding to the test data. For example, the interpolation module 604 may determine a design point in the design characteristic diagram corresponding to the test expansion ratio at the test scaled speed, such as a first design point having a first expansion ratio and a second design point having a second expansion ratio at the test scaled speed, etc. As an example and not limitation, the interpolation module 604 may determine a design point corresponding to the test point performance data by interpolating in the design characteristic diagram.

[0087] The apparatus 600 may further include a performance data generating module 606 , which may be configured to generate a plurality of performance data at a plurality of converted speeds according to the determined difference between the design point performance data and the test point performance data.

[0088] In one embodiment, the performance data generation module 606 may determine the deviation vector according to the difference between the performance data of at least two design points and the corresponding at least two test points. Further, the performance data generation module 606 may generate a corresponding deviation vector at each of the multiple converted speeds according to the deviation vector based on the deviation empirical function between different converted speeds, and these deviation vectors may form a deviation matrix. The performance data generation module 606 may also generate multiple performance data at each of the multiple converted speeds based on the design characteristic diagram and the deviation matrix.

[0089] In another embodiment, the performance data generation module 606 may determine the convergence coefficient of the difference as the expansion ratio changes based on the difference between the performance data of at least two design points and the corresponding test points. Further, the performance data generation module 606 may select a design point as a reference point, and generate a corresponding deviation vector at each of the multiple conversion speeds based on the reference point according to the deviation empirical function between different conversion speeds. The performance data generation module 606 may also generate multiple performance data for each conversion speed at multiple conversion speeds based on the design characteristic diagram, the deviation vector and the convergence coefficient.

[0090] The apparatus 600 may further include a characteristic diagram generating module 608 , which may be configured to generate a real characteristic diagram of the high pressure turbine at a plurality of converted speeds based on at least the first test point performance data and the second test point performance data and the generated plurality of performance data.

[0091] In a further embodiment, the device 600 may further optionally include a performance evaluation module 610, which may be configured to, for example, determine the deviation between the design characteristic map and the actual characteristic map to determine whether the performance of the high-pressure turbine meets the requirements. For example, the deviation between the design characteristic map and the actual characteristic map may include the mean, weighted value, or maximum value of the deviations at multiple performance points.

[0092] Figure 6 The various modules of the device 600 shown in the figure may be implemented in a processor or a memory. For example, the memory may store processor executable instructions, which are configured to implement the functions implemented by the various modules when executed by the processor.

[0093] The present invention aims at the uncertainty in the high-pressure turbine components of aircraft engines and proposes a method for generating an actual characteristic diagram and a performance evaluation method based on the deviation of the characteristic diagram. The uncertainty in the manufacturing process will lead to deviations in component performance. It takes a lot of time and cost to test the performance of the components. The present invention only needs to test the parameters of two actual performance points. The calculation process is simple and convenient. When the geometric parameters are within a small range of variation, the evaluation method has a high accuracy and can provide high-fidelity digital twin model information for the component, and save a lot of experimental time and cost for evaluating component performance.

[0094] The various steps and modules of the methods and devices described above can be implemented with hardware, software, or a combination thereof. If implemented in hardware, the various illustrative steps, modules, and circuits described in conjunction with the present disclosure can be implemented or executed with a general-purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field programmable gate array (FPGA), or other programmable logic components, hardware components, or any combination thereof. The general-purpose processor can be a processor, a microprocessor, a controller, a microcontroller, or a state machine, etc. If implemented in software, the various illustrative steps and modules described in conjunction with the present disclosure can be stored on a computer-readable medium or transmitted as one or more instructions or codes. The software modules that implement the various operations of the present disclosure can reside in a storage medium, such as RAM, flash memory, ROM, EPROM, EEPROM, registers, hard disks, removable disks, CD-ROMs, cloud storage, etc. The storage medium can be coupled to a processor so that the processor can read and write information from / to the storage medium, and execute corresponding program modules to implement the various steps of the present disclosure. Moreover, the software-based embodiments can be uploaded, downloaded, or remotely accessed by appropriate communication means. Such appropriate communications means include, for example, the Internet, the World Wide Web, an intranet, software applications, cable (including fiber optic cables), magnetic communications, electromagnetic communications (including RF, microwave and infrared communications), electronic communications or other such communications means.

[0095] The numerical values ​​given in each embodiment are only examples and are not intended to limit the scope of the present invention. According to specific practice, the specific parameters of each component can be appropriately set as needed, without being limited to the specific values ​​given as examples in this article. In addition, as an overall technical solution, there are other components or steps that are not listed in the claims or description of the present invention. Moreover, a single name of a component does not exclude other names of the component.

[0096] It should also be noted that these embodiments may be described as a process depicted as a flow chart, flow diagram, structure diagram, or block diagram. Although the flow chart may describe the operations as sequential processes, many of these operations can be performed in parallel or concurrently. In addition, the order of these operations can be rearranged.

[0097] The disclosed methods, devices, and systems should not be limited in any way. On the contrary, the present disclosure covers all novel and non-obvious features and aspects of the various disclosed embodiments (alone and in various combinations and sub-combinations with each other). The disclosed methods, devices, and systems are not limited to any specific aspects or features or combinations thereof, nor do any disclosed embodiments require the existence of any one or more specific advantages or the resolution of specific or all technical problems.

[0098] The present invention is not limited to the above-mentioned specific embodiments, which are merely illustrative and not restrictive. Under the guidance of the present invention, ordinary technicians in this field can make many forms without departing from the scope of protection of the present invention and the claims, all of which belong to the protection scope of the present invention.

Claims

1. A method for generating realistic characteristics of a high pressure turbine of an aero-engine, It is characterized in that include: Obtaining the design characteristic diagram of the high pressure turbine; Acquiring performance data of at least two test points of the high-pressure turbine having different expansion ratios at a converted speed in the performance test; Determining at least two design points in the design characteristic diagram having the different expansion ratios at the converted speed; Generating a plurality of performance data at a plurality of converted speeds according to differences between the at least two design points and the corresponding performance data of the at least two test points; as well as A real characteristic diagram of the high-pressure turbine at the plurality of converted speeds is generated based on the at least two test point performance data and the generated plurality of performance data.

2. The method for generating the real characteristics of the high pressure turbine of an aircraft engine according to claim 1, It is characterized in that Generating a plurality of performance data at a plurality of converted speeds further comprises: determining a deviation vector based on a difference between one or more of the at least two design points and corresponding test point performance data; Determining a deviation matrix at the plurality of converted speeds according to the deviation vector; and A plurality of performance data at the plurality of converted rotation speeds are generated based on the design characteristic map and the deviation matrix.

3. The method for generating the real characteristics of the high pressure turbine of an aircraft engine according to claim 2, It is characterized in that Determining the deviation matrix at the plurality of converted speeds according to the deviation vector further comprises: Based on an empirical function of deviations between different converted speeds, a corresponding deviation vector at each of the multiple converted speeds is generated according to the deviation vector, and the deviation matrix includes a corresponding deviation vector at each of the multiple converted speeds.

4. The method for generating the real characteristics of the high pressure turbine of an aircraft engine according to claim 2, It is characterized in that Generating a plurality of performance data at a plurality of converted speeds further comprises: determining a convergence coefficient of the difference as the expansion ratio changes based on the difference between the performance data of the at least two design points and the corresponding at least two test points, and A plurality of performance data based on a change in the convergence coefficient with the expansion ratio at each of the plurality of converted rotational speeds are generated based on the design characteristic map and the deviation matrix.

5. The method for generating the real characteristics of the high pressure turbine of an aircraft engine according to claim 1, Features: Each of the at least two test point performance data and the plurality of performance data includes a converted flow rate and / or an efficiency.

6. The method for generating the real characteristics of the high pressure turbine of an aircraft engine according to claim 1, Features: The at least two design points are determined by interpolating in the design characteristic map.

7. The method for generating the real characteristics of the high pressure turbine of an aircraft engine according to claim 1, Features: The deviation between the designed characteristic map and the actual characteristic map is determined to determine whether the performance of the high-pressure turbine meets the requirements.

8. The method for generating the real characteristics of the high pressure turbine of an aircraft engine according to claim 7, Features: The deviation between the designed characteristic diagram and the actual characteristic diagram includes an average value, a weighted value, or a maximum value of the deviations at a plurality of performance points.

9. A device for generating the real characteristics of a high pressure turbine of an aircraft engine, include: A memory for storing processor executable instructions; as well as A processor coupled to the memory, wherein the processor is configured to implement the method for generating real characteristics of a high-pressure turbine of an aircraft engine according to any one of claims 1 to 8 when executing the processor-executable instructions.

10. A device for generating the real characteristics of a high pressure turbine of an aircraft engine, include: a data acquisition module configured to acquire a design characteristic diagram of the high-pressure turbine and to acquire performance data of at least two test points of the high-pressure turbine having different expansion ratios at a converted speed during a performance test; an interpolation module configured to determine at least two design points in the design characteristic diagram having the different expansion ratios at the converted rotation speed; A performance data generating module, configured to generate a plurality of performance data at a plurality of converted speeds according to differences between the at least two design points and the corresponding at least two test point performance data; as well as A characteristic map generating module is configured to generate a real characteristic map of the high-pressure turbine at the plurality of converted speeds based on the at least two test point performance data and the generated plurality of performance data.

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