Method, system and medium for analyzing aerodynamic performance of a compressor

Abstract

The application aims to provide a compressor aerodynamic performance analysis method, an analysis system and a medium. The compressor aerodynamic performance analysis method comprises the following steps: obtaining a design value of the overall efficiency of the compressor; obtaining an over-limit value and a design value of the tip clearance of the rotor blade of any specified stage of the compressor; obtaining an efficiency difference value when the tip clearance is the over-limit value and the design value; calculating a third efficiency value when the tip clearance is the design value, so that the actual efficiency is equal to the difference between the third efficiency value and the efficiency difference value, and recording the outlet temperature calculation amount; obtaining the compressor outlet temperature calculation amount according to the outlet temperature calculation amount; and obtaining the actual overall efficiency of the compressor when the tip clearance of the rotor blade of the specified stage is the over-limit value according to the compressor outlet temperature calculation amount. The compressor aerodynamic performance analysis method can improve the efficiency and accuracy of analyzing the influence of the tip clearance change of the multistage axial flow compressor on the performance.

Description

Technical Field

[0001] This invention relates to the field of gas turbine engine technology, and in particular to a method, analysis system and medium for analyzing the aerodynamic performance of a compressor. Background Technology

[0002] A typical civilian multi-stage (usually 5 stages or more, even reaching 20 stages) axial compressor includes a rotor and stator assembly. The rotor assembly is the rotating component, and tip clearance is typically introduced to prevent blade rubbing against the casing. Figure 1 As shown, the ratio of tip clearance b to blade height h is approximately 1%. Additionally, a scrapable coating 90 is often applied to one side of the casing to further prevent abrasion between the metal blades and the metal casing. Under the pressure difference across the tip clearance, some fluid passes through the clearance, forming leakage flow. This leakage typically exists in the compressor tip region as tip leakage vortices. These vortices cause leakage losses and blockages in the compressor, thus reducing compressor efficiency and stable operating range. Compressors require high precision in tip clearance, which in turn places high demands on the machining precision of the blades and casing. However, in actual machining, deviations often occur in the machining of one or several stages of the casing and blades, leading to insufficient tip clearance and affecting the compressor's aerodynamic performance. Whether a single-stage or multi-stage tip clearance deviation is acceptable depends on its impact on the overall performance of the multi-stage compressor. Currently, this analysis still faces the following two challenges:

[0003] 1) Existing analytical methods are inaccurate for integrated calculations of multi-stage compressors. Changes in blade tip clearance lead to changes in tip leakage vortices, initially affecting the aerodynamic performance of individual compressor stages and subsequently the entire compressor. Designers typically use 3D CFD numerical simulations to solve the flow field of the entire compressor to obtain performance changes. However, for multi-stage axial compressors, 3D CFD calculations, which solve the viscous Navier-Stokes equations, result in significant differences between the mainstream parameters of each stage and reality. This is especially true when using 3D CFD to solve for the mainstream parameters of multi-stage compressors (e.g., ten or more stages), where calculation errors accumulate between stages, amplifying the discrepancy between the calculated results and reality. Near the compressor outlet, the mainstream parameters are severely distorted, leading to significant errors in the final flow field results. Performance differences caused by clearance variations are even more difficult to accurately determine through multi-stage integrated calculations.

[0004] 2) Existing 3D CFD numerical calculations often take a long time to perform integrated calculations of multi-stage compressors. The more stages and the denser the mesh, the longer the calculation time, making it difficult to obtain analysis results quickly and affecting the progress.

[0005] There is an urgent need to provide a method that can quickly and accurately analyze the impact of changes in tip clearance on the performance of multi-stage axial compressors. Summary of the Invention

[0006] The purpose of this invention is to provide a method for analyzing the aerodynamic performance of a compressor, which can improve the efficiency and accuracy of analyzing the impact of changes in tip clearance on the performance of a multi-stage axial compressor.

[0007] The compressor aerodynamic performance analysis method for achieving the aforementioned objectives includes the following steps:

[0008] a. Obtain the design value of the overall efficiency of the compressor;

[0009] b. Obtain the tip clearance deviation value and the tip clearance design value of any specified stage rotor blade of the compressor;

[0010] c. Simulation yields the first efficiency value of the specified stage in the compressor when the blade tip clearance of the specified stage rotor blades is out of tolerance.

[0011] d. Simulation yields the second efficiency value of the specified stage in the compressor when the blade tip clearance of the specified stage rotor blades is the design value of the blade tip clearance;

[0012] e. Obtain the efficiency difference between the first efficiency value and the second efficiency value;

[0013] f. Calculate the third efficiency value of the specified stage in the compressor when the blade tip clearance of the specified stage rotor blade is the design value of the blade tip clearance, change the outlet temperature of the specified stage, and at the same time obtain the actual efficiency of the specified stage, so that the actual efficiency is equal to the difference between the third efficiency value and the efficiency difference value, and record the outlet temperature of the specified stage at this time as the calculated outlet temperature.

[0014] g. The compressor outlet temperature is calculated based on the calculated outlet temperature, the outlet pressure of the specified stage, the compressor outlet pressure, and the design value of the efficiency from the specified stage to the compressor outlet.

[0015] h. Based on the compressor outlet temperature, compressor inlet pressure, compressor inlet temperature, and compressor outlet pressure, obtain the actual overall efficiency of the compressor when the blade tip clearance of the specified stage rotor blades is out of tolerance.

[0016] In one or more embodiments, step a includes:

[0017] Obtain the compressor's inlet pressure, compressor inlet temperature, compressor outlet pressure, and compressor outlet temperature;

[0018] The overall machine efficiency design value is calculated using the following formula:

[0019]

[0020]

[0021] Where eff(1~N+1) is the overall machine efficiency design value, N is the number of compressor stages, P1 is the compressor inlet pressure, and P N+1 T is the compressor outlet pressure, T1 is the compressor inlet temperature, and T... N+1 This is the compressor outlet temperature. C p0 =0.239111645, b1=-1.3877943E-05, b2=1.305071516E-07, b3=-5.499968112E-10, b4=1.390879692E-12, b 5=-1.45325748E-15, b6=5.290596006E-19; Rg=29.2712[(kgf·m) / (kg·K)]; J=426.935[(kgf·m) / (kcal)];

[0022] Among them, P1, P N+1 T1 and T N+1 All of these measurements were taken when the tip clearance of each stage of the compressor blades was at the design value.

[0023] In one or more embodiments, the first efficiency value and the second efficiency value in step d and step c are respectively obtained by three-dimensional numerical simulation calculation.

[0024] In one or more embodiments, in step f, the third efficiency value is calculated using the following formula:

[0025]

[0026] Where eff(i~i+1) is the third efficiency value, P i The inlet pressure of the specified level; P i+1 For the specified stage's outlet pressure, T i T represents the inlet temperature of the specified grade. i+1 The outlet temperature of the specified stage;

[0027] Among them, P i P i+1 T i And T i+1 All measurements were taken when the blade tip clearance of the specified stage rotor blade was the design value of the blade tip clearance.

[0028] In one or more embodiments, in step g, the compressor outlet temperature is calculated using the following formula:

[0029]

[0030] Where eff(i+1~N+1) is the design value of the efficiency from the specified stage outlet to the compressor outlet, and T′ i+1 P is the calculated value for the outlet temperature. i+1 For the specified stage of outlet pressure, P N+1 The compressor outlet pressure, T′ N+1 This is a calculated value for the compressor outlet temperature.

[0031] In one or more embodiments, the design value of the efficiency from the designated stage outlet to the compressor outlet is calculated using the following formula:

[0032]

[0033] In one or more embodiments, the actual overall efficiency of the compressor in step h is calculated using the following formula:

[0034]

[0035] Wherein, eff(1~N+1)′ is the actual overall efficiency of the compressor when the tip clearance of the specified stage rotor blades is out of tolerance.

[0036] On the other hand, according to some embodiments of this application, a readable medium having a computer program thereon is also provided, which is executed by a processor to implement the steps of the compressor aerodynamic performance analysis method as described above.

[0037] Furthermore, according to some embodiments of this application, a compressor aerodynamic performance analysis system is also provided, comprising:

[0038] A first sensor and a second sensor are installed at the inlet of each stage stator blade and at the outlet of the compressor. The first sensor is used to sense the temperature at the inlet and outlet cross-sections of each stage of the compressor, and the second sensor is used to sense the pressure at the inlet and outlet cross-sections of each stage of the compressor. The analysis system further includes:

[0039] Memory is used to store instructions that can be executed by the processor;

[0040] A processor is used to execute the instructions to implement the compressor aerodynamic performance analysis method as described above.

[0041] In one or more embodiments, the first sensor is a total temperature blade-type sensing element, and the second sensor is a total pressure blade-type sensing element.

[0042] This compressor aerodynamic performance analysis method enables rapid and accurate analysis of the impact of single-row blade tip clearance variations on the performance of multi-stage axial flow compressors. While improving accuracy, it also shortens calculation and analysis time, accelerating the development process.

[0043] The above description is only an overview of the technical solution of this application. In order to better understand the technical means of this application and to implement it in accordance with the contents of the specification, and to make the above and other objects, features and advantages of this application more obvious and understandable, the following are specific embodiments of this application. Attached Figure Description

[0044] Various other advantages and benefits will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiments below. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0045] Figure 1 A schematic diagram of the blade tip clearance is shown;

[0046] Figure 2 A flowchart illustrating some embodiments of the compressor aerodynamic performance analysis method is shown;

[0047] Figure 3 Schematic diagrams are shown according to some embodiments of this compressor aerodynamic performance analysis system. Detailed Implementation

[0048] The embodiments of the technical solution of this application will now be described in detail with reference to the accompanying drawings. These embodiments are only used to more clearly illustrate the technical solution of this application and are therefore merely examples, and should not be used to limit the scope of protection of this application.

[0049] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the application; the terms “comprising” and “having”, and any variations thereof, in the specification, claims, and foregoing description of the drawings are intended to cover non-exclusive inclusion.

[0050] One or more terms mentioned in this document are explained below:

[0051] Turbofan engine: A type of aircraft engine, generally a twin-rotor engine, mainly composed of a fan booster stage, a high-pressure compressor, a combustion chamber, a high-pressure turbine, and a low-pressure turbine.

[0052] Core engine: A crucial component of a turbofan engine, including the high-pressure compressor, combustion chamber, and high-pressure turbine.

[0053] High-pressure compressor: In a twin-rotor aircraft engine or gas turbine, there is a compression component on both the low-pressure and high-pressure shafts. The compression component on the high-pressure shaft is called the high-pressure compressor; it typically uses axial air intake and is also known as an axial compressor.

[0054] Aerodynamic Performance: The aerodynamic performance of a multi-stage axial compressor in an engine mainly includes three aspects: inlet converted flow rate (air flow rate converted from compressor inlet conditions to standard atmospheric conditions, in kg / s), pressure ratio (the ratio of compressor outlet total pressure to inlet total pressure, dimensionless), and efficiency (the proportion of mechanical work converted into gas pressure energy by the compressor, calculated using inlet and outlet total temperature and pressure parameters, dimensionless). During compressor design, flow rate and pressure ratio are relatively easy to meet overall performance requirements, while efficiency is more difficult to achieve. Furthermore, the factors affecting efficiency are complex, including the effects of leakage flow at blade tip clearance, leakage flow at ferrule clearance, and blade machining deviations. The magnitude of these factors' aerodynamic impact is difficult to calculate precisely.

[0055] Tip Clearance: The space between the rotor blade tip and the outer casing wall, where airflow can easily leak.

[0056] 3D CFD (Computational Fluid Dynamics): Computational fluid dynamics uses numerical simulation methods to solve nonlinear simultaneous mass, momentum, and energy equations to simulate the real flow conditions inside the compressor in three dimensions.

[0057] On the one hand, according to some embodiments of this application, a method for analyzing the aerodynamic performance of a compressor is provided to achieve rapid and accurate analysis of the impact of changes in tip clearance on the performance of a multi-stage axial compressor. For example... Figure 2 The following is a flowchart illustrating some embodiments of the compressor aerodynamic performance analysis method, which includes the following steps:

[0058] Step a. Obtain the design value of the compressor's overall efficiency, eff(1-N+1);

[0059] Step b. Obtain the tip clearance deviation value `tip_real(i)` and the tip clearance design value `tip_design(i)` for any specified stage of the compressor rotor blade. It is understood that deviation refers to exceeding the tolerance. During the design phase of any stage of the rotor blade, its tip clearance and tolerance range are designed. The tip clearance value exceeding the tolerance range is the tip clearance deviation value. For example, in a specific embodiment, based on the design phase requirements, the tip clearance design value `x` is obtained, the tolerance range is `y`, and the deviation value is set to `z`, where `|z|>|y|`. Therefore, the tip clearance deviation value is `x+z`. It is understood that the deviation value `z` can be obtained from actual tip clearance measurements or specified for subsequent calculations.

[0060] Step c. Simulation obtains the first efficiency value cfd_eff_real(i) of the specified stage rotor blade when the blade tip clearance of the specified stage is the tip clearance excess value tip_real(i);

[0061] Step d. Simulation yields the second efficiency value cfd_eff_design(i) of the specified stage in the compressor when the blade tip clearance of the specified stage rotor blade is the blade tip clearance design value tip_design(i);

[0062] Step e. Obtain the efficiency difference between the first efficiency value and the second efficiency value, i.e., cfd_delta(i) = cfd_eff_design(i) - cfd_effreal(i).

[0063] f. Calculate the third efficiency value eff(i~i+1) of the specified stage in the compressor when the tip clearance of the specified stage rotor blades is the tip clearance design value tip_design(i), and change the outlet temperature T of the specified stage. i+1 Simultaneously, obtain the actual efficiency of the specified stage, such that the actual efficiency equals the difference between the third efficiency value and the efficiency difference, and record the outlet temperature of the specified stage at this time as the calculated outlet temperature T′. i+1 ;

[0064] g. Calculate T′ based on the outlet temperature i+1 The designated level of outlet pressure P i+1 The outlet pressure P of the compressor N+1 The compressor outlet temperature T′ is calculated by using the design value of the efficiency from the specified stage to the compressor outlet (eff(i+1~N+1)). N+1 ;

[0065] h. Calculate T′ based on compressor outlet temperature N+1 Compressor inlet pressure P1, compressor inlet temperature T1, and compressor outlet pressure P N+1The actual overall efficiency of the compressor, eff(1~N+1)′, is obtained when the tip clearance of the specified stage rotor blades is the tip clearance excess value tip_real(i).

[0066] Unless otherwise specified, the pressure unit referred to in one or more embodiments of this application is kPa, and the temperature unit is k.

[0067] In one specific embodiment, step a includes:

[0068] Obtain the compressor inlet pressure P1, compressor inlet temperature T1, and compressor outlet pressure P. N+1 And the compressor outlet temperature T N+1 ;

[0069] The overall machine efficiency design value is calculated using the following formula:

[0070]

[0071]

[0072] Where eff(1~N+1) is the overall machine efficiency design value, N is the number of compressor stages, P1 is the compressor inlet pressure, and P N+1 T is the compressor outlet pressure, T1 is the compressor inlet temperature, and T... N+1 This is the compressor outlet temperature. C p0 =0.239111645, b1=-1.3877943E-05, b2=1.305071516E-07, b3=-5.499968112E-10, b4=1.390879692E-12, b 5=-1.45325748E-15, b6=5.290596006E-19; Rg=29.2712[(kgf·m) / (kg·K)]; J=426.935[(kgf·m) / (kcal)];

[0073] Among them, P1, P N+1 T1 and T N+1 All measurements were taken when the tip clearance of each stage of the compressor blades was at the design value.

[0074] In a specific embodiment, the first efficiency value cfd_eff_real(i) and the second efficiency value cfd_eff_design(i) in steps d and c are respectively obtained by three-dimensional numerical simulation calculation.

[0075] In a specific embodiment, in step f, the third efficiency value eff(i~i+1) is calculated using the following formula:

[0076]

[0077] Where eff(i~i+1) is the third efficiency value, P i The inlet pressure of the specified level; P i+1 For the specified stage's outlet pressure, T i T represents the inlet temperature of the specified grade. i+1 The outlet temperature of the specified stage;

[0078] Among them, P i P i+1 T i And T i+1 All measurements were taken when the blade tip clearance of the specified stage rotor blade was the design value of the blade tip clearance.

[0079] Furthermore, during the process of changing the outlet temperature of a specified stage, the actual efficiency of the specified stage is obtained by calculating the equivalent average specific heat.

[0080] Furthermore, in a specific embodiment, in step g, the compressor outlet temperature is calculated using the following formula:

[0081]

[0082] Where eff(i+1~N+1) is the design value of the efficiency from the specified stage outlet to the compressor outlet, and T′ i+1 P is the calculated value for the outlet temperature. i+1 For the specified stage of outlet pressure, P N+1 The compressor outlet pressure, T′ N+1 This is a calculated value for the compressor outlet temperature.

[0083] In a specific embodiment, the actual overall efficiency of the compressor in step h is calculated using the following formula:

[0084]

[0085] Wherein, eff(1~N+1)′ is the actual overall efficiency of the compressor when the tip clearance of the specified stage rotor blades is out of tolerance.

[0086] This compressor aerodynamic performance analysis method enables rapid and accurate analysis of the impact of single-row blade tip clearance variations on the performance of multi-stage axial flow compressors. While improving accuracy, it also shortens calculation and analysis time, accelerating the development process.

[0087] On the other hand, according to some embodiments of this application, a compressor aerodynamic performance analysis system is also provided, such as... Figure 3 Schematic diagrams are shown according to some embodiments of this compressor aerodynamic performance analysis system. Figure 3 The blades connected to the outer casing 10 are stator blades 11, and the blades connected to the inner hub are rotor blades 12. Typically, one row of stators and one row of rotors are combined into one stage 100, and the final stage contains two rows of stators and one row of rotors. The compressor aerodynamic performance analysis system includes:

[0088] A first sensor 21 and a second sensor 22 are installed at the inlet of each stage stator blade and at the outlet of the compressor. The first sensor 21 is used to sense the temperature at the inlet section 20 and outlet section 20 of each stage of the compressor, and the second sensor 22 is used to sense the pressure at the inlet section 20 and outlet section 20 of each stage of the compressor. The analysis system also includes:

[0089] Memory is used to store instructions that can be executed by the processor;

[0090] A processor for executing instructions to implement the compressor aerodynamic performance analysis method described in one or more of the foregoing embodiments.

[0091] It can be understood that, for the first stage of the compressor, its inlet temperature and pressure are equivalent to the inlet temperature and pressure of the entire compressor. For any stage of the compressor, its inlet temperature and pressure are measured by the first sensor 21 and the second sensor 22 located at the inlet cross-section of that stage, and its outlet temperature and pressure are measured by the first sensor 21 and the second sensor 22 located at the inlet cross-section of the next stage.

[0092] In one specific embodiment, the first sensor 21 and the second sensor 22 are disposed at the leading edge of each stage stator blade.

[0093] In one specific embodiment, the first sensor is a total temperature blade-type sensing element, and the second sensor is a total pressure blade-type sensing element.

[0094] According to another aspect of this application, a computer-readable medium is also provided. The computer-readable medium provided herein has computer instructions. When executed by a processor, these computer instructions can implement the steps performed by the program in the compressor aerodynamic performance analysis method described in the above embodiments.

[0095] It is understood that the processor in the preceding embodiments may be one or more of the following combinations: System-on-a-Chip (SOC), microcontroller, microprocessor (e.g., microcontroller), Reduced Instruction Set Computer (RISC), Application-Specific Integrated Circuit (ASIC), Application-Specific Instruction Integrated Processor (ASIP), Central Processing Unit (CPU), Graphics Processing Unit (GPU), Physical Processing Unit (PPU), Microcontroller Unit, Digital Signal Processor (DSP), Field Programmable Gate Array (FPGA), Advanced RISC Machine (ARM), Programmable Logic Device (PLD), or any circuit or processor capable of performing one or more functions.

[0096] The steps of the methods described in conjunction with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of both. The software module may reside in RAM memory, flash memory, ROM memory, EPROM memory, EEPROM memory, registers, hard disk, removable disk, CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to a processor such that the processor can read and write information to / from the storage medium. In an alternative, the storage medium may be integrated into the processor. The processor and storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In an alternative, the processor and storage medium may reside as discrete components in the user terminal.

[0097] In one or more exemplary embodiments, the described functionality may be implemented in hardware, software, firmware, or any combination thereof. If implemented in software as a computer program product, the functionality may be stored or transmitted as one or more instructions or code on or through a computer-readable medium. A computer-readable medium includes both computer storage media and communication media, encompassing any medium that facilitates the transfer of a computer program from one location to another. A storage medium may be any available medium accessible to a computer. By way of example and not limitation, such a computer-readable medium may include RAM, ROM, EEPROM, CD-ROM or other optical disc storage, disk storage or other magnetic storage devices, or any other medium that can be used to carry or store desired program code in the form of instructions or data structures and is accessible to a computer. Any connection is also legitimately referred to as a computer-readable medium. For example, if the software is transmitted from a website, server, or other remote source using coaxial cable, fiber optic cable, twisted pair, digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwave, then the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwave are included in the definition of a medium. As used in this article, disk and disc include compact discs (CDs), laser discs, optical discs, digital multi-purpose discs (DVDs), floppy disks, and Blu-ray discs. Disks typically reproduce data magnetically, while discs reproduce data optically using lasers. Combinations of these should also be included within the scope of computer-readable media.

[0098] The present invention will be further illustrated below through two specific embodiments.

[0099] Example 1

[0100] Taking the interstage test measurement parameters of an 8-stage compressor as an example, the tip clearance of each stage is the design value 'a'. The temperature and pressure measurement results at the inlet of each stage are shown in the table below, where T1 to T8 represent the inlet section temperatures of stages 1 to 8, respectively, and T9 represents the compressor outlet section temperature. Similarly, P1 to P8 represent the inlet section pressures of stages 1 to 8, respectively, and P9 represents the compressor outlet section pressure. The efficiency of the 8-stage compressor is calculated to be 78.40% based on the data in the table.

[0101] P1 101 T1 288 P2 141 T2 328 P3 184 T3 358 P4 239 T4 398 P5 311 T5 428 P6 404 T6 468 P7 525 T7 498 P8 683 T8 538 P9 887 T9 598

[0102] If the blade tip clearance of the 5th stage is out of tolerance after machining, the blade tip clearance exceeds the tolerance by 0.1mm. Numerical simulation calculations are carried out for the two states of blade tip clearance of the 5th stage rotor, a and a+0.1mm. The efficiencies corresponding to the two sets of clearances are 87.90% and 86.90%, respectively. It is found that the blade tip clearance of the 5th stage exceeds the tolerance by 0.1mm, and the impact on the efficiency of the 5th stage is 1%.

[0103] Based on P5, P6, T5, and T6, the efficiency of stage 5 under the design clearance is calculated to be 81.96%. Adjusting T6 reduces the efficiency of this stage by 1%, and the efficiency of this stage is now 80.96%. The corresponding T′6 is 468.5.

[0104] First, calculate eff(6-9), that is, substitute P6, P9, T6, and T9 into Formula 1 to obtain eff(6-9) = 87.77%. Based on eff(6-9), P6, T′6, and P9, calculate the new T9, that is, T′9 = 598.6.

[0105] Based on T1, P1, P9, and T′9, the new eff(1~9)′=78.235% is calculated. Therefore, the analysis results show that the machining deviation of the tip clearance of the fifth stage blade is 0.1mm, which has an impact of approximately 78.40%-78.24%=0.16% on the overall efficiency of the eighth-stage compressor.

[0106] Example 2

[0107] Taking the interstage test measurement parameters of a 7-stage compressor as an example, the tip clearance of each stage is the design value 'a'. The temperature and pressure measurement results at the inlet of each stage are shown in the table below, where T1 to T7 represent the inlet section temperatures of stages 1 to 7, respectively, and T8 represents the compressor outlet section temperature. Similarly, P1 to P7 represent the inlet section pressures of stages 1 to 7, respectively, and P8 represents the compressor outlet section pressure. The efficiency of the 7-stage compressor is calculated to be 78.65% based on the data in the table.

[0108] P1 101 T1 288 P2 141 T2 323 P3 184 T3 358 P4 239 T4 393 P5 311 T5 428 P6 404 T6 463 P7 525 T7 498 P8 683 T8 550

[0109] If the fourth-stage blade tip clearance is out of tolerance, the blade tip clearance will exceed the tolerance by 0.1mm.

[0110] Numerical simulations were conducted for the tip clearance of the fourth-stage rotor blades in two states: a and a+0.1 mm. The efficiencies corresponding to the two clearances were 88% and 86.78%, respectively. The tip clearance of the fourth-stage blades was found to be out of tolerance by 0.1 mm, and its impact on the efficiency of the fourth stage was 1.22%.

[0111] Based on P4, P5, T4, and T5, the efficiency of the fourth stage under the design clearance is calculated to be 86.48%. Adjusting T5 reduces the efficiency of this stage by 1.22%, and the efficiency of this stage is now 85.26%. At this point, the corresponding T′5 is equal to 428.5.

[0112] First, calculate eff(5-8), that is, substitute P6, P8, T5, and T8 into Formula 1 to obtain eff(5-8) = 86.31%. Based on eff(5-8), P5, T′5, and P8, calculate the new T8, that is, T′9 = 550.6.

[0113] 6) Based on T1, P1, P8, and T′8, the new eff(1~8)′=78.46% is calculated. Therefore, the analysis results show that the 0.1mm deviation in the tip clearance of the 4th stage compressor has an impact of approximately 78.65%-78.46%=0.19% on the overall efficiency of the 7th stage compressor.

[0114] In this document, the term "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0115] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and not to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. These modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application, and they should all be covered within the scope of the claims and specification of this application. In particular, as long as there is no structural conflict, the various technical features mentioned in the embodiments can be combined in any way. This application is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A method for analyzing the aerodynamic performance of a compressor, characterized in that, Includes the following steps: a. Obtain the design value of the overall efficiency of the compressor; b. Obtain the tip clearance deviation value and the tip clearance design value of any specified stage rotor blade of the compressor; c. Simulation yields the first efficiency value of the specified stage in the compressor when the blade tip clearance of the specified stage rotor blades is out of tolerance. d. Simulation yields the second efficiency value of the specified stage in the compressor when the blade tip clearance of the specified stage rotor blades is the design value of the blade tip clearance; e. Obtain the efficiency difference between the first efficiency value and the second efficiency value; f. Calculate the third efficiency value of the specified stage in the compressor when the blade tip clearance of the specified stage rotor blade is the design value of the blade tip clearance, change the outlet temperature of the specified stage, and at the same time obtain the actual efficiency of the specified stage, so that the actual efficiency is equal to the difference between the third efficiency value and the efficiency difference value, and record the outlet temperature of the specified stage at this time as the calculated outlet temperature. g. The compressor outlet temperature is calculated based on the calculated outlet temperature, the outlet pressure of the specified stage, the compressor outlet pressure, and the design value of the efficiency from the specified stage to the compressor outlet. h. Based on the compressor outlet temperature, compressor inlet pressure, compressor inlet temperature, and compressor outlet pressure, obtain the actual overall efficiency of the compressor when the blade tip clearance of the specified stage rotor blades is out of tolerance.

2. The compressor aerodynamic performance analysis method as described in claim 1, characterized in that, Step a includes: Obtain the compressor's inlet pressure, compressor inlet temperature, compressor outlet pressure, and compressor outlet temperature; The overall machine efficiency design value is calculated using the following formula: Where eff(1~N+1) is the overall machine efficiency design value, N is the number of compressor stages, P1 is the compressor inlet pressure, and P N+1 T is the compressor outlet pressure, T1 is the compressor inlet temperature, and T... N+1 This is the compressor outlet temperature. C p0 =0.239111645, b1=-1.3877943E-05, b2=1.305071516E-07, b3=-5.49996811 2E-10, b4=1.390879692E-12, b5=-1.45325748E-15, b6=5.290596006E-19; R g =29.2712[(kgf·m) / (kg·K)]; J=426.935[(kgf·m) / (kcal)]; Among them, P1, P N+1 T1 and T N+1 All of these measurements were taken when the tip clearance of each stage of the compressor blades was at the design value.

3. The compressor aerodynamic performance analysis method as described in claim 1, characterized in that, The first efficiency value and the second efficiency value in step d and step c are respectively obtained by three-dimensional numerical simulation calculation.

4. The compressor aerodynamic performance analysis method as described in claim 2, characterized in that, In step f, the third efficiency value is calculated using the following formula: Where eff(i~i+1) is the third efficiency value, P i The inlet pressure of the specified level; P i+1 For the specified stage's outlet pressure, T i T represents the inlet temperature of the specified grade. i+1 The outlet temperature of the specified stage; Among them, P i P i+1 T i And T i+1 All measurements were taken when the blade tip clearance of the specified stage rotor blade was the design value of the blade tip clearance.

5. The compressor aerodynamic performance analysis method as described in claim 4, characterized in that, In step g, the compressor outlet temperature is calculated using the following formula: Where eff(i+1~N+1) is the design value of the efficiency from the specified stage outlet to the compressor outlet, and T′ i+1 P is the calculated value for the outlet temperature. i+1 For the specified stage of outlet pressure, P N+1 The compressor outlet pressure, T′ N+1 This is a calculated value for the compressor outlet temperature.

6. The compressor aerodynamic performance analysis method as described in claim 5, characterized in that, The design value of the efficiency from the designated stage outlet to the compressor outlet is calculated using the following formula:

7. The compressor aerodynamic performance analysis method as described in claim 6, characterized in that, The actual overall efficiency of the compressor mentioned in step h is calculated using the following formula: Wherein, eff(1~N+1)′ is the actual overall efficiency of the compressor when the tip clearance of the specified stage rotor blades is out of tolerance.

8. A readable medium having a computer program thereon, characterized in that, The program is executed by the processor to implement the steps of the compressor aerodynamic performance analysis method as described in any one of claims 1-7.

9. A compressor aerodynamic performance analysis system, characterized in that, include: A first sensor and a second sensor are installed at the inlet of each stage stator blade and at the outlet of the compressor. The first sensor is used to sense the temperature at the inlet and outlet cross-sections of each stage of the compressor, and the second sensor is used to sense the pressure at the inlet and outlet cross-sections of each stage of the compressor. The analysis system further includes: Memory is used to store instructions that can be executed by the processor; A processor for executing the instructions to implement the compressor aerodynamic performance analysis method as described in any one of claims 1 to 7.

10. The compressor aerodynamic performance analysis system as described in claim 9, characterized in that, The first sensor is a total temperature blade-shaped sensing element, and the second sensor is a total pressure blade-shaped sensing element.

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