Torque calibration method, device, equipment and medium for aero-gas turbine shaft engines based on torque meter

Abstract

This application discloses a method, apparatus, equipment, and medium for calibrating the torque of an aero-gas turbine shaft engine based on a torque meter. The method includes the following steps: S1, engine steady-state performance testing: starting the engine to idle, then slowly increasing the engine to several takeoff torque states, recording the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter at each takeoff torque state; S2, torque calibration: selecting N=2 takeoff torque states for the engine, the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter, and obtaining the calibration function relationship through linear fitting; S3, post-calibration check: calculating the calibrated torque values ​​of the power turbine shaft torque sensor at several takeoff torque states based on the calibration function relationship. If the differences between each calibrated torque value and the torque value corresponding to the torque meter all meet the requirements, then the torque calibration meets the requirements. This application improves the accuracy of engine torque calibration.

Description

Technical Field

[0001] This application relates to the field of aero-engine technology, and in particular to a method, apparatus, equipment and medium for torque calibration of aero-gas turbine shaft engines based on a torque meter. Background Technology

[0002] The torque of the power turbine shaft is a very important monitoring parameter during the installation and use of aero gas turbine shaft engines. If the measurement is inaccurate, it may cause the engine's power turbine shaft to operate under conditions exceeding its torque limit, leading to fatigue fracture of the power turbine shaft, and ultimately causing engine shutdown in flight or even dangerous consequences, seriously affecting flight safety.

[0003] The main body of an aero gas turbine engine is generally equipped with a torque sensor for the power turbine shaft, but its measurement accuracy is not high (±4%). Therefore, the torque measured by a hydraulic dynamometer is generally used for calibration. However, due to the measurement accuracy of the hydraulic dynamometer itself and the influence of its own flywheel torque loss, the torque accuracy after calibration is ±2%. When the engine is under high torque output, the measurement error is still too large, which may cause fatigue fracture of the power turbine shaft after long-term operation. Summary of the Invention

[0004] This application provides a torque calibration method for aero-gas turbine shaft engines based on a torque meter, in order to solve the technical problem that existing power turbine shaft torque sensors still have large errors after calibration by a hydraulic dynamometer.

[0005] The technical solution adopted in this application is as follows:

[0006] A torque calibration method for an aero-gas turbine shaft engine based on a torque meter, wherein a torque meter is installed between the engine and a hydraulic dynamometer before calibration, and the torque meter, hydraulic dynamometer and engine are connected by a coupling, and the engine torque is directly measured by the torque meter, including the following steps:

[0007] S1. Engine steady-state performance test: Start the engine to idle state, then slowly push the engine up to several takeoff torque states. Stabilize each takeoff torque state for 4 to 8 minutes and record the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under each takeoff torque state.

[0008] S2. Torque calibration: Select the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under the engine N=2 takeoff torque conditions, and obtain the calibration function relationship based on the corresponding torque values ​​through linear fitting.

[0009] S3. After calibration, check the torque value of the power turbine shaft torque sensor after calibration according to the calibration function relationship. If the difference between the torque value of the power turbine shaft torque sensor after calibration and the torque value corresponding to the torque meter under each takeoff torque condition meets the setting requirements, then the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements.

[0010] Furthermore, in step S1, the step of slowly pushing the engine up to a certain takeoff torque state specifically refers to:

[0011] Slowly push the engine up to 50% to 100% of takeoff torque, and then to several takeoff torque states.

[0012] Furthermore, step S2 specifically includes the following steps:

[0013] S21. Select the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter under the conditions of 50% takeoff torque and 100% takeoff torque, respectively. Qe1 T Qt1 ), (T Qe3 T Qt3 ),

[0014] S22. Obtain the calibration function relationship under the selected takeoff torque state through linear fitting:

[0015] T Qt =x1×T Qe +y1;

[0016] Where x1 and y1 are calibration coefficients, T Qe The torque value of the power turbine shaft torque sensor, T Qt For the torque value corresponding to the torque meter, x1 = (T Qt1 -T Qt3 ) / (T Qe1 -T Qe3 ), y1=T Qt1 -((T Qt1 -T Qt3 ) / (T Qe1 -T Qe3 ))×T Qe1 .

[0017] Furthermore, step S3 specifically includes the following steps:

[0018] S31. Engine steady-state performance test: Start the engine to idle, then slowly increase the engine speed to several takeoff torque states from 50% to 100% takeoff torque. Stabilize each takeoff torque state for 4-8 minutes, and record the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter at each takeoff torque state.Qe T Qt );

[0019] S32. Calculate the torque value T of the power turbine shaft torque sensor after calibration under each takeoff torque condition of the engine, based on the calibration function formula. Q ;

[0020] S33. If the difference between the torque value calibrated by the power turbine shaft torque sensor and the torque value corresponding to the torque meter under each takeoff torque condition meets all the setting requirements: |T Q -T Qt If |≤3N·m, the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements.

[0021] Furthermore, it also includes the following steps:

[0022] S4. Recalibrate the torque. If the torque calibration does not meet the requirements, return to step S1. Select the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under N+1 takeoff torque states. Then, by linear fitting, obtain the corresponding two calibration function relationships based on the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under two adjacent takeoff torque states in the selected N+1 takeoff torque states.

[0023] S5. After recalibration, check the torque value of the power turbine shaft torque sensor after calibration based on the two calibration function relationships. If the difference between the torque value of the power turbine shaft torque sensor after calibration and the torque value corresponding to the torque meter under each takeoff torque condition meets the setting requirements, then the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements.

[0024] Furthermore, step S4 specifically includes the following steps:

[0025] S41. Select the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter under the conditions of 50% takeoff torque and 75% takeoff torque, respectively. Qe1 T Qt1 ), (T Qe2 T Qt2 );

[0026] S42. Obtain the calibration function relationship corresponding to the selected takeoff torque state range through linear fitting:

[0027] T Qt =x2*T Qe +y2;

[0028] Where x2 and y2 are calibration coefficients, T Qe The torque value of the power turbine shaft torque sensor, T QtFor the torque value corresponding to the torque meter, x2 = (T Qt1 -T Qt2 ) / (T Qe1 -T Qe2 ), y2=T Qt1 -((T Qt1 -T Qt2 ) / (T Qe1 -T Qe2 ))×T Qe1 ;

[0029] S43. Select the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter under the conditions of 75% and 100% takeoff torque, respectively. Qe2 T Qt2 ), (T Qe3 T Qt3 );

[0030] S44. Obtain the calibration function relationship corresponding to the selected takeoff torque state range through linear fitting:

[0031] T Qt =x3*T Qe +y3;

[0032] Where x3 and y3 are calibration coefficients, T Qe The torque value of the power turbine shaft torque sensor, T Qt For the torque value corresponding to the torque meter, x3 = (T Qt2 -T Qt3 ) / (T Qe2 -T Qe3 ), y3=T Qt1 -((T Qt2 -T Qt3 ) / (T Qe2 -T Qe3 ))×T Qe2 .

[0033] Furthermore, step S5 specifically includes the following steps:

[0034] S51. Engine steady-state performance test: Start the engine to idle, then slowly increase the engine speed to several takeoff torque states from 50% to 100% takeoff torque. Stabilize each takeoff torque state for 4-8 minutes, and record the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter at each takeoff torque state. Qe T Qt );

[0035] S52. Based on the interval where the engine takeoff torque state is located, select the corresponding calibration function formula to calculate the torque value T after calibration by the power turbine shaft torque sensor for each engine takeoff torque state. Q ;

[0036] S53. If the difference between the torque value calibrated by the power turbine shaft torque sensor and the torque value corresponding to the torque meter under each takeoff torque condition meets all the setting requirements: |T Q -T Qt If |≤3N·m, the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements.

[0037] This application also provides a torque calibration device for an aero-gas turbine shaft engine based on a torque meter. Before calibration, a torque meter is installed between the engine and a hydraulic dynamometer. The torque meter, hydraulic dynamometer, and engine are connected via a coupling. The torque of the engine is directly measured using the torque meter, including:

[0038] The engine steady-state performance test module is used to start the engine to idle state, and then slowly push the engine to several take-off torque states. Each take-off torque state is stabilized for 4 to 8 minutes, and the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter are recorded at each take-off torque state.

[0039] The torque calibration module is used to select the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under the engine N=2 takeoff torque conditions, and obtain the calibration function relationship based on the corresponding torque values ​​through linear fitting.

[0040] The calibration check module is used to calculate the calibrated torque value of the power turbine shaft torque sensor under several takeoff torque conditions of the engine according to the calibration function relationship. If the difference between the calibrated torque value of the power turbine shaft torque sensor and the torque value corresponding to the torque meter under each takeoff torque condition meets the setting requirements, then the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements.

[0041] 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 computer program to implement the steps of the torque calibration method for an aero-gas turbine shaft engine based on a torque meter.

[0042] This application also provides a storage medium including a stored program that, when the program is executed, controls the device containing the storage medium to perform the steps of the torque calibration method for an aero-gas turbine shaft engine based on a torque meter.

[0043] This application has the following beneficial effects:

[0044] This application provides, for the first time, a torque calibration method for aero-gas turbine shaft engines based on a torque meter. This method offers several advantages: firstly, the torque meter provides higher torque measurement accuracy (±0.1%), while avoiding the torque loss caused by the flywheel of a hydraulic dynamometer, significantly improving the accuracy of engine power turbine shaft torque measurement; secondly, calibration using this method typically requires only one set of torque calibration coefficients, simplifying operation for maintenance personnel. Compared to conventional multi-point (more than 10 points) calibration methods, this method effectively reduces the workload of data recording and torque calibration during engine steady-state performance testing, and avoids the confusion and errors caused by multiple sets of calibration coefficients. The torque accuracy calibrated using this method can reach ±0.5%, a significant improvement over conventional torque calibration accuracy.

[0045] In addition to the purposes, features, and advantages described above, this application has other purposes, features, and advantages. A further detailed description of this application will be provided below with reference to the figures. Attached Figure Description

[0046] 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:

[0047] Figure 1 This is a schematic flowchart of a preferred embodiment of the torque calibration method for an aero-gas turbine shaft engine based on a torque meter.

[0048] Figure 2 This is a schematic diagram of the device architecture for the torque calibration method for aero-gas turbine shaft engines based on a torque meter as described in this application;

[0049] Figure 3 This is a schematic diagram showing the connection of the engine, torque meter, and hydraulic sensor according to a preferred embodiment of this application;

[0050] Figure 4 This is a schematic block diagram of an electronic device according to a preferred embodiment of this application;

[0051] Figure 5 This is an internal structural diagram of a computer device according to a preferred embodiment of this application.

[0052] In the diagram: 1. Hydraulic dynamometer; 2. Torque meter; 3. Engine. Detailed Implementation

[0053] The embodiments of this application are described in detail below with reference to the accompanying drawings; however, this application may be implemented in a variety of different ways as defined and covered below.

[0054] like Figure 1As shown, a preferred embodiment of this application provides a torque calibration method for an aero-gas turbine shaft engine based on a torque meter. Before calibration, a torque meter 2 is installed between the engine 3 and the hydraulic dynamometer 1. The torque meter 2, the hydraulic dynamometer 1, and the engine 3 are connected by a coupling. The torque of the engine 3 is directly measured by the torque meter 2 (see...). Figure 2 ), including the following steps:

[0055] S1. Engine steady-state performance test: Start the engine to idle state, then slowly push the engine up to several takeoff torque states. Stabilize each takeoff torque state for 4 to 8 minutes and record the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under each takeoff torque state.

[0056] S2. Torque calibration: Select the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under the engine N=2 takeoff torque conditions, and obtain the calibration function relationship based on the corresponding torque values ​​through linear fitting.

[0057] S3. After calibration, check the torque value of the power turbine shaft torque sensor after calibration according to the calibration function relationship. If the difference between the torque value of the power turbine shaft torque sensor after calibration and the torque value corresponding to the torque meter under each takeoff torque condition meets the setting requirements, then the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements.

[0058] This embodiment provides, for the first time, a torque calibration method for aero-gas turbine shaft engines based on a torque meter. This method offers several advantages: firstly, the torque meter provides higher torque measurement accuracy (±0.1%), while avoiding the torque loss caused by the flywheel of a hydraulic dynamometer, significantly improving the accuracy of engine power turbine shaft torque measurement; secondly, calibration using this method typically requires only one set of torque calibration coefficients, simplifying operation for maintenance personnel. Compared to conventional multi-point (more than 10 points) calibration methods, this method effectively reduces the workload of data recording and torque calibration during engine steady-state performance testing, and avoids the confusion and calibration errors caused by multiple sets of calibration coefficients. The torque accuracy calibrated using this method can reach ±0.5%, a significant improvement over conventional torque calibration accuracy.

[0059] Preferably, in step S1, the step of slowly pushing the engine up to a certain takeoff torque state specifically means:

[0060] Slowly push the engine up to several takeoff torque states, such as 50% takeoff torque state, 75% takeoff torque state, and 100% takeoff torque state.

[0061] Preferably, step S2 specifically includes the following steps:

[0062] S21. Select the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter under the conditions of 50% takeoff torque and 100% takeoff torque, respectively. Qe1 T Qt1 ), (T Qe3 T Qt3 ),

[0063] S22. Obtain the calibration function relationship under the selected takeoff torque state through linear fitting:

[0064] T Qt =x1×T Qe +y1;

[0065] Where x1 and y1 are calibration coefficients, T Qe The torque value of the power turbine shaft torque sensor, T Qt For the torque value corresponding to the torque meter, x1 = (T Qt1 -T Qt3 ) / (T Qe1 -T Qe3 ), y1=T Qt1 -((T Qt1 -T Qt3 ) / (T Qe1 -T Qe3 ))×T Qe1 .

[0066] Preferably, step S3 specifically includes the following steps:

[0067] S31. Engine steady-state performance test: Start the engine to idle, then slowly increase the engine speed to several takeoff torque states from 50% to 100% takeoff torque. Stabilize each takeoff torque state for 4-8 minutes, and record the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter at each takeoff torque state. Qe T Qt );

[0068] S32. Calculate the torque value T of the power turbine shaft torque sensor after calibration under each takeoff torque condition of the engine, based on the calibration function formula. Q ;

[0069] S33. If the difference between the torque value calibrated by the power turbine shaft torque sensor and the torque value corresponding to the torque meter under each takeoff torque condition meets all the setting requirements: |T Q -T Qt If |≤3N·m, the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements.

[0070] Preferably, the torque calibration method for aero-gas turbine shaft engines based on a torque meter further includes the following steps:

[0071] S4. Recalibrate the torque. If the torque calibration does not meet the requirements, return to step S1. Select the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under N+1 takeoff torque states. Then, by linear fitting, obtain the corresponding two calibration function relationships based on the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under two adjacent takeoff torque states in the selected N+1 takeoff torque states.

[0072] S5. After recalibration, check the torque value of the power turbine shaft torque sensor after calibration based on the two calibration function relationships. If the difference between the torque value of the power turbine shaft torque sensor after calibration and the torque value corresponding to the torque meter under each takeoff torque condition meets the setting requirements, then the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements.

[0073] In this embodiment, if the torque calibration still does not meet the requirements, the process returns to step S1 to record more torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter under engine operating conditions. Qe T Qt (e.g., 50% takeoff torque, 60% takeoff torque, 75% takeoff torque, 80% takeoff torque, 100% takeoff torque states); generally, only step S3 is needed to meet the calibration requirements, and steps S4 and S5 are unnecessary. During engine operation, one set of torque calibration coefficients is ideal, as it is simple and convenient to operate. Multiple sets of torque calibration coefficients are complex to operate, easily cause confusion, and lead to calibration errors.

[0074] Specifically, step S4 includes the following steps:

[0075] S41. Select the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter under the conditions of 50% takeoff torque and 75% takeoff torque, respectively. Qe1 T Qt1 ), (T Qe2 T Qt2 );

[0076] S42. Obtain the calibration function relationship corresponding to the selected takeoff torque state range through linear fitting:

[0077] T Qt =x2*T Qe +y2;

[0078] Where x2 and y2 are calibration coefficients, T Qe The torque value of the power turbine shaft torque sensor, T Qt For the torque value corresponding to the torque meter, x2 = (T Qt1 -T Qt2) / (T Qe1 -T Qe2 ), y2=T Qt1 -((T Qt1 -T Qt2 ) / (T Qe1 -T Qe2 ))×T Qe1 ;

[0079] S43. Select the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter under the conditions of 75% and 100% takeoff torque, respectively. Qe2 T Qt2 ), (T Qe3 T Qt3 );

[0080] S44. Obtain the calibration function relationship corresponding to the selected takeoff torque state range through linear fitting:

[0081] T Qt =x3*T Qe +y3;

[0082] Where x3 and y3 are calibration coefficients, T Qe The torque value of the power turbine shaft torque sensor, T Qt For the torque value corresponding to the torque meter, x3 = (T Qt2 -T Qt3 ) / (T Qe2 -T Qe3 ), y3=T Qt1 -((T Qt2 -T Qt3 ) / (T Qe2 -T Qe3 ))×T Qe2 .

[0083] In this embodiment, during recalibration, different calibration function relationships are set for different takeoff torque state ranges. The purpose and benefit of this is to effectively improve the torque calibration accuracy of different ranges, so that the torque values ​​after calibration of all ranges meet the setting requirements.

[0084] Specifically, step S5 includes the following steps:

[0085] S51. Engine steady-state performance test: Start the engine to idle, then slowly increase the engine speed to several takeoff torque states from 50% to 100% takeoff torque. Stabilize each takeoff torque state for 4-8 minutes, and record the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter at each takeoff torque state. Qe T Qt );

[0086] S52. Based on the interval where the engine takeoff torque state is located, select the corresponding calibration function formula to calculate the torque value T after calibration by the power turbine shaft torque sensor for each engine takeoff torque state. Q ;

[0087] S53. If the difference between the torque value calibrated by the power turbine shaft torque sensor and the torque value corresponding to the torque meter under each takeoff torque condition meets all the setting requirements: |T Q -T Qt If |≤3N·m, the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements.

[0088] In this embodiment, during the recalibration and inspection, different calibration function relationships are first selected for the takeoff torque states in different intervals to calculate the torque value of the power turbine shaft torque sensor after calibration for each takeoff torque state of the engine. Then, the difference between the calibrated torque value and the torque value corresponding to the torque meter is used to evaluate whether the torque calibration meets the requirements. The purpose and benefit are: to effectively improve the accuracy of the torque value after calibration in different intervals, so that the torque value after calibration in all intervals meets the setting requirements.

[0089] like Figure 3 As shown, this application also provides a torque calibration device for an aero-gas turbine shaft engine based on a torque meter. Before calibration, a torque meter is installed between the engine and a hydraulic dynamometer. The torque meter, hydraulic dynamometer, and engine are connected via a coupling. The torque of the engine is directly measured using the torque meter. The device includes:

[0090] The engine steady-state performance test module is used to start the engine to idle state, and then slowly push the engine to several take-off torque states. Each take-off torque state is stabilized for 4 to 8 minutes, and the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter are recorded at each take-off torque state.

[0091] The torque calibration module is used to select the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under the engine N=2 takeoff torque conditions, and obtain the calibration function relationship based on the corresponding torque values ​​through linear fitting.

[0092] The calibration check module is used to calculate the calibrated torque value of the power turbine shaft torque sensor under several takeoff torque conditions of the engine according to the calibration function relationship. If the difference between the calibrated torque value of the power turbine shaft torque sensor and the torque value corresponding to the torque meter under each takeoff torque condition meets the setting requirements, then the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements.

[0093] like Figure 4As 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 computer program, it implements the steps of the torque calibration method for an aero-gas turbine shaft engine based on a torque meter as described in the above embodiments.

[0094] like Figure 5 As 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 5 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 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 torque calibration method for aero-gas turbine shaft engines based on a torque meter.

[0095] Those skilled in the art will understand that Figure 5 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.

[0096] A preferred embodiment of this application also provides a storage medium including a stored program that, when the program is executed, controls the device containing the storage medium to perform the steps of the torque calibration method for an aero-gas turbine shaft engine based on a torque meter as described in the above embodiments.

[0097] 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.

[0098] 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.

[0099] 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.

[0100] 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.

[0101] 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 1The function specified in one or more boxes.

[0102] 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.

[0103] 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.

[0104] 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 calibrating the torque of an aero-gas turbine shaft engine based on a torque meter, wherein a torque meter is installed between the engine and a hydraulic dynamometer before calibration, the torque meter, the hydraulic dynamometer, and the engine are connected via a coupling, and the engine torque is directly measured using the torque meter, characterized in that... Including the following steps: S1. Engine steady-state performance test: Start the engine to idle state, then slowly push the engine up to several takeoff torque states. Stabilize each takeoff torque state for 4 to 8 minutes and record the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under each takeoff torque state. S2. Torque calibration: Select the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under the engine N=2 takeoff torque conditions, and obtain the calibration function relationship based on the corresponding torque values ​​through linear fitting. S3. After calibration, check the torque value of the power turbine shaft torque sensor after calibration according to the calibration function relationship. If the difference between the torque value of the power turbine shaft torque sensor after calibration and the torque value corresponding to the torque meter under each takeoff torque condition meets the setting requirements, then the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements. S4. Recalibrate the torque. If the torque calibration does not meet the requirements, return to step S1. Select the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under N+1 takeoff torque states. Then, by linear fitting, obtain the corresponding two calibration function relationships based on the torque values ​​corresponding to the power turbine shaft torque sensor and torque meter under two adjacent takeoff torque states in the selected N+1 takeoff torque states. S5. After recalibration, check the torque value of the power turbine shaft torque sensor after calibration based on the two calibration function relationship. If the difference between the torque value of the power turbine shaft torque sensor after calibration and the torque value corresponding to the torque meter under each takeoff torque condition meets the setting requirements, then the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements. Step S4 specifically includes the following steps: S41. Select the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter under the conditions of 50% takeoff torque and 75% takeoff torque, respectively. Qe1 T Qt1 ), (T) Qe2 T Qt2 ); S42. Obtain the calibration function relationship corresponding to the selected takeoff torque state range through linear fitting: T Qt =x2*T Qe +y2; Where x2 and y2 are calibration coefficients, T Qe The torque value of the power turbine shaft torque sensor, T Qt x2 = (T) is the torque value corresponding to the torque meter. Qt1 - T Qt2 ) / ( T Qe1 - T Qe2 ), y2= T Qt1 -(( T Qt1 - T Qt2 ) / ( T Qe1 - T Qe2 )) ×T Qe1 ; S43. Select the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter under the conditions of 75% and 100% takeoff torque, respectively. Qe2 T Qt2 ), (T) Qe3 T Qt3 ); S44. Obtain the calibration function relationship corresponding to the selected takeoff torque state range through linear fitting: T Qt =x3*T Qe +y3; Where x3 and y3 are calibration coefficients, x3 = (T) Qt2 - T Qt3 ) / ( T Qe2 - T Qe3 ), y3= T Qt1 -(( T Qt2 - T Qt3 ) / (T Qe2 - T Qe3 ))×T Qe2 .

2. The method for torque calibration of an aero-gas turbine shaft engine based on a torque meter according to claim 1, characterized in that, In step S1, the step of slowly pushing the engine up to a certain takeoff torque state specifically refers to: Slowly push the engine up to 50% to 100% of takeoff torque, and then to several takeoff torque states.

3. The method for torque calibration of an aero-gas turbine shaft engine based on a torque meter according to claim 1, characterized in that, Step S2 specifically includes the following steps: S21. Select the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter under the conditions of 50% takeoff torque and 100% takeoff torque, respectively. Qe1 T Qt1 ), (T) Qe3 T Qt3 ), S22. Obtain the calibration function relationship under the selected takeoff torque state through linear fitting: T Qt =x1×T Qe +y1; Where x1 and y1 are calibration coefficients, T Qe The torque value of the power turbine shaft torque sensor, T Qt For the torque value corresponding to the torque meter, x1 = (T) Qt1 - T Qt3 ) / ( T Qe1 - T Qe3 ), y1 = T Qt1 -(( T Qt1 - T Qt3 ) / ( T Qe1 - T Qe3 )) ×T Qe1 .

4. The method for torque calibration of an aero-gas turbine shaft engine based on a torque meter according to claim 3, characterized in that, Step S3 specifically includes the following steps: S31. Engine steady-state performance test: Start the engine to idle, then slowly increase the engine speed to several takeoff torque states from 50% to 100% takeoff torque. Stabilize each takeoff torque state for 4-8 minutes, and record the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter at each takeoff torque state. Qe T Qt ); S32. Calculate the torque value T of the power turbine shaft torque sensor after calibration under each takeoff torque condition of the engine, based on the calibration function formula. Q ; S33. If the difference between the torque value calibrated by the power turbine shaft torque sensor and the torque value corresponding to the torque meter under each takeoff torque condition meets all the setting requirements: |T Q -T Qt If |≤3N•m, the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements.

5. The method for torque calibration of an aero-gas turbine shaft engine based on a torque meter according to claim 1, characterized in that, Step S5 specifically includes the following steps: S51. Engine steady-state performance test: Start the engine to idle, then slowly increase the engine speed to several takeoff torque states from 50% to 100% takeoff torque. Stabilize each takeoff torque state for 4-8 minutes, and record the torque values ​​(T) corresponding to the power turbine shaft torque sensor and torque meter at each takeoff torque state. Qe T Qt ); S52. Based on the interval where the engine takeoff torque state is located, select the corresponding calibration function formula to calculate the torque value T after calibration by the power turbine shaft torque sensor for each engine takeoff torque state. Q ; S53. If the difference between the torque value calibrated by the power turbine shaft torque sensor and the torque value corresponding to the torque meter under each takeoff torque condition meets all the setting requirements: |T Q -T Qt If |≤3N•m, the torque calibration meets the requirements; otherwise, the torque calibration does not meet the requirements.

6. An electronic device comprising a memory, a processor, and a computer program stored in the memory and running on the processor, characterized in that, When the processor executes the computer program, it implements the steps of the torque calibration method for an aero-gas turbine shaft engine based on a torque meter as described in any one of claims 1 to 5.

7. 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 torque calibration method for an aero-gas turbine shaft engine based on a torque meter as described in any one of claims 1 to 5.

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