A method, device and equipment for measuring temperature drop of a pre-rotation gas supply system

Abstract

The embodiment of the present disclosure provides a kind of pre-rotation gas supply system temperature drop measurement method, device and equipment.It includes: determining the total temperature of the gas flow of nozzle inlet;Determine the static pressure and total pressure of nozzle outlet;According to the total temperature of the gas flow, static pressure and total pressure, determine the gas flow velocity of nozzle outlet;Determine the relevant parameters of nozzle, wherein the relevant parameters include nozzle geometric deflection angle, nozzle outlet center radius and gas supply hole outlet center radius;According to the relevant parameters and the gas flow velocity of nozzle outlet, determine the temperature drop of pre-rotation gas supply system.No need to arrange measuring point on turbine disk, reduce processing cost, simplify design process.Directly through pressure tube, nozzle outlet pressure signal is transmitted to pressure scanning valve, parameter transmission is more convenient and stable.Directly in nozzle outlet, pressure tube can be arranged, and more experimental working condition requirements can be adapted.

Description

Technical Field

[0001] This invention relates to the field of pre-swirl air supply systems for aero engines, and in particular to a method, apparatus, and equipment for measuring the temperature drop of a pre-swirl air supply system. Background Technology

[0002] Increasing the turbine inlet gas temperature can significantly improve engine thermal efficiency, but this temperature increase poses a significant challenge to the temperature resistance limits of existing materials. Currently, turbine blade cooling technologies mainly include film cooling, fin-reinforced heat transfer, and internal impact cooling. The pre-swirl gas supply system is responsible for supplying sufficient high-quality cool air to the turbine blades. Modern aero-engine high-pressure turbine pre-swirl gas supply systems can reduce the relative total temperature of the cool air by up to approximately 100K, demonstrating a significant temperature reduction effect. A well-designed pre-swirl gas supply system can also effectively cool the turbine disk and facilitate rim sealing. The temperature reduction effect of the pre-swirl system is an important indicator for judging the quality of its design.

[0003] The current method for measuring system temperature drop in pre-swirl gas supply system experiments is as follows: a wiring groove is machined on the back of the turbine disk, a thermocouple is fixed in the wiring groove with AB hardening glue, the relative total temperature of the gas flow at the gas supply port outlet is directly measured, and the experimental data is stored in a data logger and then transmitted to a computer for processing after the experiment is completed.

[0004] However, due to the high centrifugal force and wind resistance generated by the high speed of the turbine disk rotation, the thermocouple may fall off, making it difficult to ensure that the thermocouple remains fixed. Furthermore, the potential signal collected by the thermocouple is easily interfered with during transmission, leading to inaccurate measurement results. Summary of the Invention

[0005] The purpose of this invention is to overcome the difficulties caused by directly measuring the temperature drop using thermocouples in the prior art. It provides a method, device and equipment for measuring the temperature drop of a pre-swirl gas supply system. The method can indirectly measure the temperature drop of the pre-swirl system by installing a swirling total pressure probe at the nozzle outlet to measure the total pressure of the gas flow and arranging static pressure measuring points to measure the static pressure of the gas flow.

[0006] In a first aspect, embodiments of this disclosure provide a method for measuring the temperature drop of a pre-swirl gas supply system, the method comprising:

[0007] S1: Determine the total temperature of the airflow at the nozzle inlet;

[0008] S2: Determine the static pressure and total pressure at the nozzle outlet;

[0009] S3: Determine the nozzle outlet airflow velocity based on the total airflow temperature, static pressure, and total pressure;

[0010] S4: Determine the relevant parameters of the nozzle, including the nozzle geometric deflection angle, the nozzle outlet center radius, and the air supply port outlet center radius;

[0011] S5: Determine the temperature drop of the pre-swirl gas supply system based on relevant parameters and nozzle outlet airflow velocity.

[0012] Optionally, step S1 specifically includes:

[0013] S11: Measure the initial total airflow temperature a specified number of times at the total temperature measurement point in the intake chamber using a total temperature probe;

[0014] S12: Determine the total temperature of the airflow at the nozzle inlet based on the average of the total initial airflow temperatures.

[0015] Optionally, step S3 specifically includes:

[0016] S31: Determine the nozzle outlet Mach number based on static pressure and total pressure;

[0017] S32: Determine the nozzle outlet static temperature based on the total airflow temperature, static pressure, and total pressure;

[0018] S33: Determine the nozzle exit airflow velocity based on the nozzle exit Mach number.

[0019] Optionally, the nozzle exit Mach number in step S31 is expressed as:

[0020]

[0021] Where Ma represents the nozzle exit Mach number, P1 * P1 represents the total pressure, P2 represents the static pressure, and k represents the isentropic exponent.

[0022] Optionally, the nozzle outlet airflow velocity in step S33 is expressed as:

[0023]

[0024] Where V1 represents the nozzle exit velocity, c represents the local speed of sound, Ma represents the nozzle exit Mach number, k represents the isentropic exponent, and R... g T1 represents the gas constant, and T1 represents the static temperature at the nozzle outlet.

[0025] Optionally, step S5 specifically includes:

[0026] S51: Determine the nozzle outlet circumferential velocity based on the nozzle geometric deflection angle and the nozzle outlet airflow velocity;

[0027] S52: Determine the temperature drop of the pre-swirl gas supply system based on the nozzle outlet circumferential velocity, the nozzle outlet center radius, and the gas supply hole outlet center radius.

[0028] Optionally, the temperature drop of the pre-swirl gas supply system in step S52 can be expressed as:

[0029]

[0030] Where ΔT represents the temperature drop of the pre-swirl air supply system, ω represents the angular velocity of the turntable, and c p This indicates the specific heat capacity at constant pressure. The nozzle outlet circumferential velocity is represented by r1, the nozzle outlet center radius is represented by r2, and the air supply port outlet center radius is represented by r2.

[0031] Secondly, embodiments of this disclosure also provide a measuring device for the temperature drop of a pre-swirl gas supply system, the device comprising:

[0032] The total airflow temperature determination module is used to determine the total airflow temperature at the nozzle inlet.

[0033] The static pressure and total pressure determination module is used to determine the static pressure and total pressure at the nozzle outlet.

[0034] The nozzle outlet airflow velocity determination module is used to determine the nozzle outlet airflow velocity based on the total airflow temperature, static pressure, and total pressure.

[0035] The relevant parameter determination module is used to determine the relevant parameters of the nozzle, including the nozzle geometric deflection angle, the nozzle outlet center radius, and the air supply port outlet center radius.

[0036] The pre-swirl gas supply system temperature drop determination module is used to determine the temperature drop of the pre-swirl gas supply system based on relevant parameters and nozzle outlet airflow velocity.

[0037] Thirdly, embodiments of this disclosure also provide an electronic device, the electronic device comprising:

[0038] At least one processor; and

[0039] A memory that is communicatively connected to at least one processor; wherein,

[0040] When the memory stores a computer program that can be executed by at least one processor, the computer program is executed by at least one processor to enable the at least one processor to perform a method for measuring the temperature drop of a pre-swirl gas supply system as in any embodiment of the present disclosure.

[0041] Fourthly, embodiments of this disclosure provide a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements a method for measuring the temperature drop of a pre-swirl gas supply system as described in any embodiment of this disclosure.

[0042] It should be understood that the description in this section is not intended to identify key or essential features of the embodiments of the present invention, nor is it intended to limit the scope of the invention. Other features of the invention will become readily apparent from the following description.

[0043] Therefore, the present invention has the following beneficial effects:

[0044] 1. The elimination of the need to place measuring points on the turbine disk reduces processing costs and simplifies the design process.

[0045] 2. The nozzle outlet pressure signal is directly transmitted to the pressure scanning valve through the pressure tapping tube, making parameter transmission more convenient and stable.

[0046] 3. By directly arranging the pressure tap at the nozzle outlet, more experimental conditions can be accommodated. Attached Figure Description

[0047] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0048] Figure 1 This is a flowchart of a method for measuring the temperature drop of a pre-swirl gas supply system according to Embodiment 1 of the present invention;

[0049] Figure 2 This is a flowchart of another method for measuring the temperature drop of a pre-swirl gas supply system according to Embodiment 1 of the present invention;

[0050] Figure 3 This is a flowchart of another method for measuring the temperature drop of a pre-swirl gas supply system according to Embodiment 1 of the present invention;

[0051] Figure 4 This is a flowchart of another method for measuring the temperature drop of a pre-swirl gas supply system according to Embodiment 1 of the present invention;

[0052] Figure 5 This is a schematic diagram of a pre-swirl nozzle blade provided according to Embodiment 2 of the present invention;

[0053] Figure 6 This is a schematic diagram of a rotating test bench structure for a swirling gas supply system according to Embodiment 2 of the present invention;

[0054] Figure 7 This is a schematic diagram of the arrangement of total pressure measuring points at the nozzle outlet according to Embodiment 2 of the present invention;

[0055] Figure 8 This is a schematic diagram of a device for measuring the temperature drop of a pre-swirl gas supply system according to Embodiment 3 of the present invention;

[0056] Figure 9 This is a schematic diagram of the structure of an electronic device provided according to Embodiment 4 of the present invention.

[0057] Among them, 1. Nozzle inlet section, 2. Nozzle outlet section, 3. Receiver inlet section, 4. Air supply inlet section, 5. Receiver outlet section, 6. Air supply outlet section, 7. Nozzle outlet static pressure measuring point, 8. Nozzle outlet total pressure measuring point. Detailed Implementation

[0058] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0059] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0060] Example 1

[0061] Figure 1 This document provides a flowchart of a method for measuring the temperature drop of a pre-swirl gas supply system according to Embodiment 1 of the present invention. This embodiment is applicable to measuring the temperature drop of a pre-swirl gas supply system. The method can be executed by the temperature drop measuring device of the pre-swirl gas supply system provided in this disclosure. This device can be implemented in software and / or hardware and is generally integrated into a computer device. The method of this disclosure specifically includes:

[0062] S1: Determine the total temperature of the airflow at the nozzle inlet.

[0063] Figure 2 The flowchart of a method for measuring the temperature drop of a pre-swirl gas supply system provided in Embodiment 1 of the present invention is shown. Step S1 mainly includes the following steps S11 to S12.

[0064] S11: Measure the initial total airflow temperature a specified number of times at the total temperature measurement point in the intake chamber using a total temperature probe.

[0065] Specifically, two total temperature measuring points can be arranged at any position in the air intake chamber. Two circular holes with a diameter of 2mm are machined on the air intake housing so that the position of the holes coincides with the position of the total temperature measuring points. The total temperature probe is inserted into the air intake chamber through the circular holes to measure the initial total temperature of the airflow at the nozzle inlet.

[0066] S12: Determine the total temperature of the airflow at the nozzle inlet based on the average of the total initial airflow temperatures.

[0067] Specifically, when measuring the total airflow temperature, it should be collected continuously for more than 10 times, and the average value of multiple measurements at two measuring points should be taken as the total airflow temperature at the nozzle inlet under this operating condition.

[0068] It should be noted that the gap between the total temperature measuring point and the circular hole is connected with glue to prevent gas leakage during the experiment from affecting the measurement accuracy.

[0069] S2: Determine the static pressure and total pressure at the nozzle outlet.

[0070] Specifically, the nozzle outlet is annular. Four static pressure measuring points and two total pressure measuring points can be arranged at the nozzle outlet cross-section, divided into two groups. Each group has two static pressure measuring points and one total pressure measuring point. One group is arranged on the outer ring and the other on the inner ring of the nozzle. The distance ds from the center of each measuring point to the inner wall of its respective end face is 2 mm. At least 10 measurements should be taken continuously during the measurement process. The average value of the multiple measurements from both groups is taken as the static pressure and total pressure of the nozzle outlet airflow under this operating condition.

[0071] S3: Determine the nozzle outlet airflow velocity based on the total airflow temperature, static pressure, and total pressure.

[0072] Figure 3 The flowchart of a method for measuring the temperature drop of a pre-swirl gas supply system provided in Embodiment 1 of the present invention is shown. Step S3 mainly includes the following steps S31 to S33.

[0073] S31: Determine the nozzle exit Mach number based on static pressure and total pressure.

[0074] Specifically, the following relationships exist between the total temperature of the gas flow at the nozzle inlet, the static pressure of the gas flow at the nozzle outlet, the total pressure of the gas flow at the nozzle outlet, the static temperature at the nozzle outlet, and the Mach number at the nozzle outlet:

[0075]

[0076]

[0077] Among them, P1 * P1 represents total pressure, P1 represents static pressure, k represents isentropic exponent, Ma represents nozzle exit Mach number, and T1 represents total pressure. * T1 represents the total temperature of the airflow at the nozzle outlet, and T2 represents the static temperature at the nozzle outlet.

[0078] Optionally, the nozzle exit Mach number can be obtained by simplifying formula (1), that is, the nozzle exit Mach number in step S31 is expressed as:

[0079]

[0080] Where Ma represents the nozzle exit Mach number, P1 * P1 represents the total pressure, P2 represents the static pressure, and k represents the isentropic exponent.

[0081] S32: Determine the nozzle outlet static temperature based on the total airflow temperature, static pressure, and total pressure.

[0082] Specifically, the airflow through the nozzle can be considered an adiabatic process; therefore, the total inlet and outlet temperatures of the nozzle remain constant.

[0083]

[0084] Among them, T1 * This indicates the total temperature of the airflow at the nozzle exit. Let represent the total temperature of the airflow at the nozzle inlet. Substituting formula (4) into formula (2), the static temperature at the nozzle outlet can be calculated:

[0085]

[0086] Where T1 represents the nozzle outlet static temperature, T1 * This indicates the total temperature of the airflow at the nozzle exit. P1 represents the total temperature of the airflow at the nozzle inlet. * P1 represents the total pressure, P2 represents the static pressure, and k represents the isentropic exponent.

[0087] S33: Determine the nozzle exit airflow velocity based on the nozzle exit Mach number.

[0088] Optionally, the nozzle outlet airflow velocity in step S33 is expressed as:

[0089]

[0090] Where V1 represents the nozzle exit velocity, c represents the local speed of sound, Ma represents the nozzle exit Mach number, k represents the isentropic exponent, and R... g T1 represents the gas constant, and T1 represents the static temperature at the nozzle outlet.

[0091] S4: Determine the relevant parameters of the nozzle, including the nozzle geometric deflection angle, the nozzle outlet center radius, and the air supply port outlet center radius.

[0092] Specifically, the geometric deflection angle of the nozzle refers to the angle between the trailing edge of the nozzle blade and the circumferential section; the nozzle outlet center radius refers to the distance from the center of the nozzle outlet section to the central axis of the nozzle disk; and the air supply outlet center radius refers to the distance from the center of the air supply outlet section to the central axis of the turbine disk.

[0093] S5: Determine the temperature drop of the pre-swirl gas supply system based on relevant parameters and nozzle outlet airflow velocity.

[0094] Figure 4 The flowchart of a method for measuring the temperature drop of a pre-swirl gas supply system provided in Embodiment 1 of the present invention is shown. Step S5 mainly includes the following steps S51 to S52.

[0095] S51: Determine the nozzle exit circumferential velocity based on the nozzle geometric deflection angle and the nozzle exit airflow velocity.

[0096] Specifically, the circumferential velocity at the nozzle exit can be expressed as:

[0097]

[0098] in, V1 represents the nozzle exit circumferential velocity, V1 represents the nozzle exit airflow velocity, and α represents the nozzle geometric deflection angle.

[0099] S52: Determine the temperature drop of the pre-swirl gas supply system based on the nozzle outlet circumferential velocity, the nozzle outlet center radius, and the gas supply hole outlet center radius.

[0100] Optionally, the temperature drop of the pre-swirl gas supply system in step S52 can be expressed as:

[0101]

[0102] Where ΔT represents the temperature drop of the pre-swirl air supply system, ω represents the angular velocity of the turntable, and c p This indicates the specific heat capacity at constant pressure. The nozzle outlet circumferential velocity is represented by r1, the nozzle outlet center radius is represented by r2, and the air supply port outlet center radius is represented by r2. This completes the measurement of the temperature drop of the pre-swirl air supply system.

[0103] The technical solution of this invention determines the total airflow temperature at the nozzle inlet and the static and total pressure at the nozzle outlet. Based on the total airflow temperature, static and total pressure, the nozzle outlet airflow velocity is determined, and relevant nozzle parameters are also determined. These parameters include the nozzle geometric deflection angle, the nozzle outlet center radius, and the air supply port outlet center radius. The temperature drop of the pre-swirl air supply system is determined based on these parameters and the nozzle outlet airflow velocity. This eliminates the need to arrange measuring points on the turbine disk, reducing processing costs and simplifying the design process. The nozzle outlet pressure signal is directly transmitted to the pressure scanning valve via a pressure tap, making parameter transmission more convenient and stable. Furthermore, placing the pressure tap directly at the nozzle outlet allows for adaptation to a wider range of experimental conditions.

[0104] Example 2

[0105] This embodiment is a method for measuring the temperature drop of a pre-swirl gas supply system. Based on the above embodiment one, this embodiment adds an application scenario to specifically explain the measurement process of the temperature drop of the pre-swirl gas supply system.

[0106] Figure 5 This embodiment provides a schematic diagram of a pre-swirling nozzle blade. Figure 5 In the diagram, 1 represents the nozzle inlet section, 2 represents the nozzle outlet section, 3 represents the receiving hole inlet section, 4 represents the air supply hole inlet section, 5 represents the receiving hole outlet section, 6 represents the air supply hole outlet section, 7 represents the nozzle outlet static pressure measuring point, and 8 represents the nozzle outlet total pressure measuring point. Figure 6 This embodiment provides a schematic diagram of the structure of a rotary test bench for a vortex gas supply system. Figure 6 In the figure, 2 represents the nozzle exit section and α represents the nozzle geometric deflection angle. Figure 7 This invention provides a schematic diagram of the arrangement of total pressure measuring points at the nozzle outlet. Figure 7 In the diagram, 2 represents the nozzle outlet cross section, 7 represents the nozzle outlet static pressure measuring point, and 8 represents the nozzle outlet total pressure measuring point. A set of these points is arranged on both the outer and inner rings of the nozzle, and the distance ds from the center of each measuring point to the inner wall of its end face is 2 mm.

[0107] To verify the accuracy of the above implementation process, the temperature drop of the pre-swirl gas supply system can be compared with the values ​​calculated by computational fluid dynamics, as shown in Table 1 below:

[0108] Table 1 Comparison of Experimental Measurement Calculation and Numerical Calculation

[0109] Rotational speed (r / min) Temperature drop - CFD(K) Temperature drop of pre-swirl air supply system absolute deviation relative deviation 4800 19.32 18.71 0.61 3.13％ 5400 20.85 20.58 0.27 1.32％ 6000 23.45 22.81 1.14 2.74％ 7800 25.34 24.51 0.83 3.27％ 8400 25.02 24.26 0.76 3.08％ 9000 24.06 23.44 0.62 2.57％

[0110] Table 1 shows the results of the temperature drop of the pre-swirl air supply system obtained by formulas (1) to (8) under different rotational speeds, with an outlet pressure of 100 kPa, an inlet air pressure of 170 kPa, and an inlet air temperature of 293 K. The absolute and relative deviations from the CFD calculation values ​​are also shown. For example, when the rotational speed is 4800 r / min, the corresponding CFD calculation value is 19.32, the temperature drop of the pre-swirl air supply system is 18.71, the absolute deviation is 0.61, and the relative deviation is 3.13%. Furthermore, the maximum relative deviation between the two is 3.27%.

[0111] The technical solution of this invention determines the total airflow temperature at the nozzle inlet and the static and total pressure at the nozzle outlet. Based on the total airflow temperature, static and total pressure, the nozzle outlet airflow velocity is determined, and relevant nozzle parameters are also determined. These parameters include the nozzle geometric deflection angle, the nozzle outlet center radius, and the air supply port outlet center radius. The temperature drop of the pre-swirl air supply system is determined based on these parameters and the nozzle outlet airflow velocity. This eliminates the need to arrange measuring points on the turbine disk, reducing processing costs and simplifying the design process. The nozzle outlet pressure signal is directly transmitted to the pressure scanning valve via a pressure tap, making parameter transmission more convenient and stable. Furthermore, placing the pressure tap directly at the nozzle outlet allows for adaptation to a wider range of experimental conditions.

[0112] Example 3

[0113] Figure 8 This is a schematic diagram of a device for measuring the temperature drop of a pre-swirl gas supply system according to Embodiment 3 of the present invention. This device can be implemented using software and / or hardware, and is generally integrated into the electronic device performing the method. For example... Figure 8 As shown, the device includes: a total airflow temperature determination module 310 for determining the total airflow temperature at the nozzle inlet; a static pressure and total pressure determination module 320 for determining the static pressure and total pressure at the nozzle outlet; a nozzle outlet airflow velocity determination module 330 for determining the nozzle outlet airflow velocity based on the total airflow temperature, static pressure, and total pressure; a related parameter determination module 340 for determining the related parameters of the nozzle, including the nozzle geometric deflection angle, the nozzle outlet center radius, and the air supply port outlet center radius; and a pre-swirl air supply system temperature drop determination module 350 for determining the pre-swirl air supply system temperature drop based on the related parameters and the nozzle outlet airflow velocity.

[0114] Optionally, the total airflow temperature determination module 310 is specifically used to: measure the initial total airflow temperature a specified number of times at the total temperature measurement point in the air inlet chamber using a total temperature probe; and determine the total airflow temperature at the nozzle inlet based on the average value of each initial total airflow temperature.

[0115] Optionally, the nozzle outlet airflow velocity determination module 330 is specifically used to: determine the nozzle outlet Mach number based on static pressure and total pressure; determine the nozzle outlet static temperature based on total airflow temperature, static pressure, and total pressure; and determine the nozzle outlet airflow velocity based on the nozzle outlet Mach number.

[0116] Optionally, the nozzle exit Mach number in the nozzle exit airflow velocity determination module 330 is expressed as:

[0117]

[0118] Where Ma represents the nozzle exit Mach number, P1 * P1 represents the total pressure, P2 represents the static pressure, and k represents the isentropic exponent.

[0119] Optionally, the nozzle outlet airflow velocity in the nozzle outlet airflow velocity determination module 330 is expressed as:

[0120]

[0121] Where V1 represents the nozzle exit velocity, c represents the local speed of sound, Ma represents the nozzle exit Mach number, k represents the isentropic exponent, and R... g T1 represents the gas constant, and T1 represents the static temperature at the nozzle outlet.

[0122] Optionally, the pre-swirl gas supply system temperature drop determination module 350 is specifically used to: determine the nozzle outlet circumferential velocity based on the nozzle geometric deflection angle and the nozzle outlet airflow velocity; and determine the pre-swirl gas supply system temperature drop based on the nozzle outlet circumferential velocity, the nozzle outlet center radius, and the air supply hole outlet center radius.

[0123] Optionally, the temperature drop of the pre-swirl gas supply system in the pre-swirl gas supply system temperature drop determination module 350 is expressed as follows:

[0124]

[0125] Where ΔT represents the temperature drop of the pre-swirl air supply system, ω represents the angular velocity of the turntable, and c p This indicates the specific heat capacity at constant pressure. The nozzle outlet circumferential velocity is represented by r1, the nozzle outlet center radius is represented by r2, and the air supply port outlet center radius is represented by r2.

[0126] The technical solution of this invention determines the total airflow temperature at the nozzle inlet and the static and total pressure at the nozzle outlet. Based on the total airflow temperature, static and total pressure, the nozzle outlet airflow velocity is determined, and relevant nozzle parameters are also determined. These parameters include the nozzle geometric deflection angle, the nozzle outlet center radius, and the air supply port outlet center radius. The temperature drop of the pre-swirl air supply system is determined based on these parameters and the nozzle outlet airflow velocity. This eliminates the need to arrange measuring points on the turbine disk, reducing processing costs and simplifying the design process. The nozzle outlet pressure signal is directly transmitted to the pressure scanning valve via a pressure tap, making parameter transmission more convenient and stable. Furthermore, placing the pressure tap directly at the nozzle outlet allows for adaptation to a wider range of experimental conditions.

[0127] The temperature drop measuring device for a pre-swirl gas supply system provided in this embodiment of the invention can execute the temperature drop measuring method for a pre-swirl gas supply system provided in any embodiment of the invention, and has the corresponding functional modules and beneficial effects of the method.

[0128] Example 4

[0129] Figure 9 This is a schematic diagram of the structure of an electronic device 400 provided in Embodiment 4 of the present invention. The electronic device in this embodiment can be a device corresponding to the backend service platform of an application, or a mobile terminal device with an application client installed. Specifically, the electronic device can include, but is not limited to, mobile terminals such as mobile phones, laptops, digital radio receivers, PDAs (personal digital assistants), PADs (tablet computers), PMPs (portable multimedia players), and in-vehicle terminals (e.g., in-vehicle navigation terminals), as well as fixed terminals such as digital TVs and desktop computers. Figure 9 The electronic device shown is merely an example and should not be construed as limiting the functionality and scope of the embodiments disclosed herein.

[0130] like Figure 8 As shown, electronic device 400 may include a processing device (e.g., a central processing unit, a graphics processing unit, etc.) 401, which can perform various appropriate actions and processes according to a program stored in read-only memory (ROM) 402 or a program loaded from storage device 408 into random access memory (RAM) 403. RAM 403 also stores various programs and data required for the operation of electronic device 400. Processing device 401, ROM 402, and RAM 403 are interconnected via bus 404. Input / output (I / O) interface 405 is also connected to bus 404.

[0131] Typically, the following devices can be connected to I / O interface 405: input devices 406 including, for example, touchscreens, touchpads, keyboards, mice, cameras, microphones, accelerometers, gyroscopes, etc.; output devices 407 including, for example, liquid crystal displays (LCDs), speakers, vibrators, etc.; storage devices 408 including, for example, magnetic tapes, hard disks, etc.; and communication devices 409. Communication device 409 allows electronic device 400 to communicate wirelessly or wiredly with other devices to exchange data. Although Figure 3 An electronic device 400 with various devices is shown; however, it should be understood that it is not required to implement or possess all of the devices shown. More or fewer devices may be implemented or possessed alternatively.

[0132] In particular, according to embodiments of this disclosure, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of this disclosure include a computer program product comprising a computer program carried on a non-transitory computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via communication device 409, or installed from storage device 408, or installed from ROM 402. When the computer program is executed by processing device 401, it performs the functions defined in the methods of embodiments of this disclosure.

[0133] It should be noted that the computer-readable medium described in this disclosure can be a computer-readable signal medium or a computer-readable storage medium, or any combination thereof. A computer-readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination thereof. More specific examples of a computer-readable storage medium may include, but are not limited to: an electrical connection having one or more wires, a portable computer disk, a hard disk, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage device, magnetic storage device, or any suitable combination thereof. In this disclosure, a computer-readable storage medium can be any tangible medium containing or storing a program that can be used by or in conjunction with an instruction execution system, apparatus, or device. In this disclosure, a computer-readable signal medium can include a data signal propagated in baseband or as part of a carrier wave, carrying computer-readable program code. Such propagated data signals can take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination thereof. A computer-readable signal medium can be any computer-readable medium other than a computer-readable storage medium, which can send, propagate, or transmit a program for use by or in connection with an instruction execution system, apparatus, or device. The program code contained on the computer-readable medium can be transmitted using any suitable medium, including but not limited to: wires, optical fibers, RF (radio frequency), etc., or any suitable combination thereof.

[0134] In some implementations, clients and servers can communicate using any currently known or future-developed network protocol such as HTTP (Hypertext Transfer Protocol) and can interconnect with digital data communication (e.g., communication networks) of any form or medium. Examples of communication networks include local area networks (“LANs”), wide area networks (“WANs”), the Internet (e.g., the Internet of Things), and peer-to-peer networks (e.g., ad hoc peer-to-peer networks), as well as any currently known or future-developed networks.

[0135] The aforementioned computer-readable medium may be included in the aforementioned electronic device; or it may exist independently and not assembled into the electronic device.

[0136] The aforementioned computer-readable medium carries one or more programs that, when executed by the electronic device, cause the internal processes of the electronic device to perform the following: determining the total temperature of the airflow at the nozzle inlet; determining the static pressure and total pressure at the nozzle outlet; determining the airflow velocity at the nozzle outlet based on the total temperature, static pressure, and total pressure; determining relevant parameters of the nozzle, including the nozzle geometric deflection angle, the nozzle outlet center radius, and the air supply port outlet center radius; and determining the temperature drop of the pre-swirl air supply system based on the relevant parameters and the airflow velocity at the nozzle outlet.

[0137] Computer program code for performing the operations of this disclosure can be written in one or more programming languages ​​or a combination thereof, including but not limited to object-oriented programming languages ​​such as Java, Smalltalk, and C++, as well as conventional procedural programming languages ​​such as the "C" language or similar programming languages. The program code can be executed entirely on the user's computer, partially on the user's computer, as a standalone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving remote computers, the remote computer can be connected to the user's computer via any type of network, including a local area network (LAN) or a wide area network (WAN), or it can be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0138] The flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of systems, methods, and computer program products according to various embodiments of this disclosure. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions indicated in the blocks may occur in a different order than those indicated in the drawings. For example, two consecutively indicated blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in the block diagrams and / or flowcharts, and combinations of blocks in the block diagrams and / or flowcharts, can be implemented using a dedicated hardware-based system that performs the specified function or operation, or using a combination of dedicated hardware and computer instructions.

[0139] The units described in the embodiments of this disclosure can be implemented in software or in hardware. The names of the units are not, in some cases, intended to limit the specific unit.

[0140] The functions described above in this document can be performed, at least in part, by one or more hardware logic components. For example, exemplary types of hardware logic components that can be used, without limitation, include: Field Programmable Gate Arrays (FPGAs), Application-Specific Integrated Circuits (ASICs), Application Standard Products (ASSPs), System-on-Chip (SoCs), Complex Programmable Logic Devices (CPLDs), and so on.

[0141] In the context of this disclosure, a machine-readable medium can be a tangible medium that may contain or store a program for use by or in conjunction with an instruction execution system, apparatus, or device. A machine-readable medium can be a machine-readable signal medium or a machine-readable storage medium. A machine-readable medium can be, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, apparatus, or devices, or any suitable combination of the foregoing. More specific examples of machine-readable storage media include electrical connections based on one or more wires, portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fiber, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination of the foregoing.

[0142] The above description is merely a preferred embodiment of this disclosure and an explanation of the technical principles employed. Those skilled in the art should understand that the scope of this disclosure is not limited to technical solutions formed by specific combinations of the above-described technical features, but should also cover other technical solutions formed by arbitrary combinations of the above-described technical features or their equivalents without departing from the above-described concept. For example, technical solutions formed by substituting the above features with (but not limited to) technical features disclosed in this disclosure that have similar functions.

[0143] Furthermore, while the operations are described in a specific order, this should not be construed as requiring these operations to be performed in the specific order shown or in a sequential order. In certain environments, multitasking and parallel processing may be advantageous. Similarly, while several specific implementation details are included in the above discussion, these should not be construed as limiting the scope of this disclosure. Certain features described in the context of individual embodiments may also be implemented in combination in a single embodiment. Conversely, various features described in the context of a single embodiment may also be implemented individually or in any suitable sub-combination in multiple embodiments.

[0144] Although the subject matter has been described using language specific to structural features and / or methodological logic, it should be understood that the subject matter defined in the appended claims is not necessarily limited to the specific features or actions described above. Rather, the specific features and actions described above are merely illustrative examples of implementing the claims.

Claims

1. A method for measuring the temperature drop of a pre-swirl gas supply system, characterized in that, Includes the following steps: S1: Determine the total temperature of the airflow at the nozzle inlet; S2: Determine the static pressure and total pressure at the nozzle outlet; S3: Determine the nozzle outlet airflow velocity based on the total airflow temperature, the static pressure, and the total pressure; S4: Determine the relevant parameters of the nozzle, wherein the relevant parameters include the nozzle geometric deflection angle, the nozzle outlet center radius, and the air supply port outlet center radius; S5: Determine the temperature drop of the pre-swirl gas supply system based on the relevant parameters and the nozzle outlet airflow velocity; Step S3 specifically includes: S31: Determine the nozzle outlet Mach number based on the static pressure and the total pressure; S32: Determine the nozzle outlet static temperature based on the total airflow temperature, the static pressure, and the total pressure; S33: Determine the nozzle outlet airflow velocity based on the nozzle outlet Mach number; The nozzle exit Mach number in step S31 is expressed as: ； Where Ma represents the nozzle exit Mach number. P1 represents the total pressure, P2 represents the static pressure, and k represents the isentropic exponent. The nozzle outlet airflow velocity in step S33 is expressed as: ； Where V1 represents the nozzle exit velocity, c represents the local speed of sound, Ma represents the nozzle exit Mach number, k represents the isentropic exponent, and R... g T1 represents the gas constant, and T1 represents the nozzle outlet static temperature. Step S5 specifically includes: S51: Determine the nozzle outlet circumferential velocity based on the nozzle geometric deflection angle and the nozzle outlet airflow velocity; S52: Determine the temperature drop of the pre-swirl air supply system based on the circumferential velocity of the nozzle outlet, the center radius of the nozzle outlet, and the center radius of the air supply hole outlet; The temperature drop of the pre-swirl gas supply system in step S52 is expressed as follows: ； Where ΔT represents the temperature drop of the pre-swirl air supply system, and w represents the angular velocity of the turntable. p V represents the specific heat capacity at constant pressure. φ,1 The nozzle outlet circumferential velocity is represented by r1, the nozzle outlet center radius is represented by r2, and the air supply port outlet center radius is represented by r2.

2. The method for measuring the temperature drop of a pre-swirl gas supply system according to claim 1, characterized in that, Step S1 specifically includes: S11: Measure the initial total airflow temperature a specified number of times at the total temperature measurement point in the intake chamber using a total temperature probe; S12: Determine the total airflow temperature at the nozzle inlet based on the average value of the initial total airflow temperature.

3. A device for measuring the temperature drop of a pre-swirl gas supply system, characterized in that, include: The total airflow temperature determination module is used to determine the total airflow temperature at the nozzle inlet. The static pressure and total pressure determination module is used to determine the static pressure and total pressure at the nozzle outlet. A nozzle outlet airflow velocity determination module is used to determine the nozzle outlet airflow velocity based on the total airflow temperature, the static pressure, and the total pressure. The relevant parameter determination module is used to determine the relevant parameters of the nozzle, wherein the relevant parameters include the nozzle geometric deflection angle, the nozzle outlet center radius, and the air supply port outlet center radius; A pre-swirl gas supply system temperature drop determination module is used to determine the temperature drop of the pre-swirl gas supply system based on the relevant parameters and the nozzle outlet airflow velocity. The phrase "determining the nozzle outlet airflow velocity based on the total airflow temperature, the static pressure, and the total pressure" specifically includes: The nozzle exit Mach number is determined based on the static pressure and the total pressure. The nozzle outlet static temperature is determined based on the total airflow temperature, the static pressure, and the total pressure. The nozzle exit airflow velocity is determined based on the nozzle exit Mach number. The nozzle exit Mach number is expressed as: ； Where Ma represents the nozzle exit Mach number. P1 represents the total pressure, P2 represents the static pressure, and k represents the isentropic exponent. The nozzle outlet airflow velocity is expressed as: ； Where V1 represents the nozzle exit velocity, c represents the local speed of sound, Ma represents the nozzle exit Mach number, k represents the isentropic exponent, and R... g T1 represents the gas constant, and T1 represents the nozzle outlet static temperature. The phrase "determining the temperature drop of the pre-swirl gas supply system based on the relevant parameters and the nozzle outlet airflow velocity" specifically includes: The nozzle exit circumferential velocity is determined based on the nozzle geometric deflection angle and the nozzle exit airflow velocity. The temperature drop of the pre-swirl air supply system is determined based on the circumferential velocity of the nozzle outlet, the center radius of the nozzle outlet, and the center radius of the air supply port outlet. The temperature drop of the pre-swirl air supply system is expressed as follows: ； Where ΔT represents the temperature drop of the pre-swirl air supply system, w represents the angular velocity of the turntable, and c p V represents the specific heat capacity at constant pressure. φ,1 The nozzle outlet circumferential velocity is represented by r1, the nozzle outlet center radius is represented by r2, and the air supply port outlet center radius is represented by r2.

4. An electronic device, characterized in that, The electronic device includes: At least one processor; and A memory communicatively connected to the at least one processor; wherein, The memory stores a computer program that can be executed by the at least one processor to enable the at least one processor to perform the method of claims 1-2.

5. A computer storage medium, characterized in that, The computer storage medium stores computer instructions that are used to cause the processor to execute the method described in claims 1-2.

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