Gas compressor aerodynamic performance analysis method, analysis system and medium

Abstract

The invention aims to provide a gas compressor aerodynamic performance analysis method and system and a medium. The gas compressor aerodynamic performance analysis method comprises the following steps that the overall efficiency design value of a gas compressor is obtained; obtaining a blade tip clearance out-of-tolerance value and a design value of any specified stage of rotor blades of the gas compressor; obtaining an efficiency difference value when the blade tip clearance is a blade tip clearance out-of-tolerance value and a design value; calculating to obtain a third efficiency value when the blade tip clearance is the design value, enabling the actual efficiency to be equal to the difference between the third efficiency value and the efficiency difference value, and recording the outlet temperature calculation amount; the compressor outlet temperature calculated amount is obtained according to the outlet temperature calculated amount; and according to the compressor outlet temperature calculation amount, the actual complete machine efficiency of the compressor is obtained when the blade tip clearance of the specified-level rotor blade is the out-of-tolerance value. According to the method for analyzing the aerodynamic performance of the gas compressor, the efficiency and accuracy of analyzing the influence of the blade tip clearance change of the multi-stage axial flow gas compressor on the performance can be improved.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbine engines, and in particular to a compressor aerodynamic performance analysis method, analysis system and medium. Background Art

[0002] A typical civilian multi-stage (usually more than 5 stages, even up to 20 stages) axial compressor includes a rotor and a stator assembly. The rotor assembly is a rotating part. Usually, in order to avoid friction between the blades and the casing, a tip clearance is introduced, such as Figure 1 As shown, the ratio of the tip clearance b to the blade height h is approximately 1%. At the same time, a scrapable coating 90 is often provided on one side of the casing to further avoid collision and wear between the metal blades and the metal casing. Under the action of the pressure difference on both sides of the tip clearance, part of the fluid passes through the tip clearance to form a leakage flow, which usually exists in the form of a tip leakage vortex in the compressor tip area. The tip leakage vortex can cause leakage loss and blockage in the compressor, thereby reducing the efficiency and stable working range of the compressor. The compressor has relatively high requirements for the accuracy of the tip clearance, and thus has relatively high requirements for the machining accuracy of the blades and casings. In the actual machining process, it often happens that one or several stages of the casing and blades are out of tolerance, which leads to the tip clearance not meeting the requirements and affecting the aerodynamic performance of the compressor. The tip clearance of a single stage or several stages is out of tolerance. Whether the tolerance is acceptable depends on the impact on the performance of the entire multi-stage compressor. At this stage, the analysis process still faces the following two difficulties:

[0003] 1) The existing analysis methods are not accurate for the combined calculation of multi-stage compressors. Changes in the tip clearance will lead to changes in the tip leakage vortex, which will first affect the aerodynamic performance of the single-stage compressor and then affect the aerodynamic performance of the entire compressor. Designers usually use three-dimensional CFD numerical simulation to solve the flow field of the entire compressor to obtain performance changes. For multi-stage axial flow compressors, three-dimensional CFD calculations are performed by solving the viscous NS equations to calculate the flow field. The mainstream parameters of each stage are quite different from the actual situation. Especially when using three-dimensional CFD calculations to solve the mainstream parameters of multi-stage compressors (such as more than ten stages), the calculation errors between each stage will gradually accumulate, resulting in the difference between the calculation results and the actual situation gradually accumulating and amplifying. In the area near the compressor outlet, the parameters of the mainstream area are seriously distorted, and the flow field results finally solved have large errors. The performance differences caused by gap changes make it even more difficult to obtain accurate results through multi-stage combined calculations;

[0004] 2) Existing three-dimensional CFD numerical calculations often take a long time for multi-stage compressors. The more stages there are and the denser the grid, the longer the calculation time, making it difficult to quickly obtain analysis results, which affects 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 a multi-stage axial compressor. Summary of the invention

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

[0007] A method for analyzing the aerodynamic performance of a compressor to achieve the above-mentioned purpose comprises the following steps:

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

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

[0010] c. simulating and obtaining a first efficiency value of the specified stage in the compressor when the tip clearance of the rotor blade of the specified stage is the tip clearance excess value;

[0011] d. simulating and obtaining a second efficiency value of the specified stage in the compressor when the tip clearance of the rotor blade of the specified stage is the tip clearance design value;

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

[0013] f. calculating a third efficiency value of the specified stage in the compressor when the tip clearance of the specified stage rotor blade is the tip clearance design value, changing the outlet temperature of the specified stage, and obtaining the actual efficiency of the specified stage at the same time, 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 of the specified stage at this time as the outlet temperature calculation amount;

[0014] g. Obtaining the calculated compressor outlet temperature according to the calculated outlet temperature, the outlet pressure of the designated stage, the outlet pressure of the compressor, and the design value of the efficiency from the designated stage to the compressor outlet;

[0015] h. obtaining the actual overall efficiency of the compressor when the tip clearance of the rotor blades of the specified stage is the tip clearance excess value based on the calculated compressor outlet temperature, the compressor inlet pressure, the compressor inlet temperature and the compressor outlet pressure.

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

[0017] Obtaining the compressor inlet pressure, compressor inlet temperature, compressor outlet pressure and compressor outlet temperature;

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

[0019]

[0020]

[0021] Among them, eff(1~N+1) is the design value of the whole machine efficiency, N is the number of compressor stages, P 1 is the compressor inlet pressure, P N+1 is the outlet pressure of the compressor, T 1 is the compressor inlet temperature, T N+1 is the compressor outlet temperature, C p0 =0.239111645, b 1 =-1.3877943E-05, b 2 =1.305071516E-07, b 3 =-5.499968112E-10, b 4 =1.390879692E-12, b 5 =-1.45325748E-15, b 6 =5.290596006E-19; Rg=29.2712[(kgf·m) / (kg·K)]; J=426.935[(kgf·m) / (kcal)];

[0022] Among them, P 1 , P N+1 , T 1 and T N+1 All of them are measured when the tip clearance of blades at each stage of the compressor is 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 by the following formula:

[0025]

[0026] Wherein, eff(i~i+1) is the third efficiency value, P i is the inlet pressure of the specified stage; P i+1 is the outlet pressure of the specified stage, T i is the inlet temperature of the specified stage, T i+1 is the outlet temperature of the specified stage;

[0027] Among them, P i , P i+1 , T i and Ti+1 Both are measured when the tip clearance of the rotor blades of the specified stage is the design value of the tip clearance.

[0028] In one or more embodiments, in step g, the compressor outlet temperature calculation amount is calculated by 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, T′ i+1 is the outlet temperature calculation quantity, P i+1 is the outlet pressure of the specified stage, P N+1 is the outlet pressure of the compressor, T′ N+1 It is the calculated value of compressor outlet temperature.

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

[0032]

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

[0034]

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

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

[0037] On the other hand, according to some embodiments of the present 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 of the compressor stator blade and the outlet of the compressor, wherein the first sensor is used to sense the temperature of the inlet section and the outlet section of the compressor at each stage, and the second sensor is used to sense the pressure of the inlet section and the outlet section of the compressor at each stage; wherein the analysis system further comprises:

[0039] a memory for storing instructions executable by a 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 profile sensing portion, and the second sensor is a total pressure blade profile sensing portion.

[0042] The compressor aerodynamic performance analysis method can quickly and accurately analyze the effect of the tip clearance change of a single-row blade on the performance of a multi-stage axial flow compressor. While improving accuracy, it shortens the calculation and analysis time and speeds up the development progress.

[0043] The above description is only an overview of the technical solution of the present application. In order to more clearly understand the technical means of the present application, it can be implemented in accordance with the contents of the specification. In order to make the above and other purposes, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are listed below. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present application. Moreover, the same reference numerals are used throughout the drawings to represent the same components. In the drawings:

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

[0046] Figure 2 A schematic diagram of a process flow according to some embodiments of the compressor aerodynamic performance analysis method is shown;

[0047] Figure 3 Schematic diagrams of some embodiments of the compressor aerodynamic performance analysis system are shown. DETAILED DESCRIPTION

[0048] The following embodiments of the technical solution of the present application are described in detail in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present application, and are therefore only used as examples, and cannot be used to limit the scope of protection of the present application.

[0049] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the above-mentioned figure descriptions and any variations thereof are intended to cover non-exclusive inclusions.

[0050] One or more of the terms mentioned in this document are explained as follows:

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

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

[0053] High-pressure compressor: A twin-rotor aircraft engine or gas turbine, with a compression component on each of the low-pressure and high-pressure shafts. The compression component on the high-pressure shaft is called a high-pressure compressor; usually uses an axial intake method, also known as an axial compressor.

[0054] Aerodynamic Performance: The aerodynamic performance of the engine for a multi-stage axial compressor mainly includes three items, namely, the inlet conversion flow rate (the air flow rate converted from the compressor inlet conditions to the standard atmospheric conditions, in kg / s), the pressure ratio (the ratio of the compressor outlet total pressure to the inlet total pressure, dimensionless), and the efficiency (the ratio of the degree to which the compressor converts mechanical work into gas pressure energy, calculated by the inlet total temperature and total pressure parameters and the outlet total temperature and total pressure parameters, dimensionless). When designing a compressor, the flow rate and pressure ratio are easier to meet the overall index requirements, but the efficiency is more difficult to meet the standards. At the same time, the factors affecting the efficiency are also more complex, including the influence of tip clearance leakage flow, the influence of comb tooth clearance leakage flow, and the influence of blade processing tolerance. The impact of these factors on the aerodynamics is difficult to accurately calculate.

[0055] Tip Clearance: The space gap formed by the rotor blade tip and the outer casing wall, where airflow is prone to leakage.

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

[0057] On the one hand, according to some embodiments of the present application, a compressor aerodynamic performance analysis method is provided to achieve rapid and accurate analysis of the impact of tip clearance changes on the performance of a multi-stage axial flow compressor. Figure 2 The flowchart of some embodiments of the compressor aerodynamic performance analysis method is shown. The compressor aerodynamic performance analysis method 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 excess value tip_real(i) and the tip clearance design value tip_design(i) of any specified stage of the compressor rotor blade. It is understandable that excess refers to exceeding the tolerance. During the design stage of any stage of the rotor blade, its tip clearance and its tolerance range will be designed. The tip clearance value exceeding the tolerance range is the tip clearance excess value. For example, in a specific embodiment, the tip clearance design value x is obtained according to the requirements of the design stage, the tolerance range is y, and the excess value is z, |z|>|y|, then the tip clearance excess value can be obtained as x+z. It is understandable that the excess value z can be obtained based on the actual tip clearance measurement, or can be specified for subsequent calculations.

[0060] Step c. simulating to obtain the first efficiency value cfd_eff_real(i) of the specified stage in the compressor when the tip clearance of the rotor blade of the specified stage is the tip clearance excess value tip_real(i);

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

[0062] Step e. Obtaining the efficiency difference between the first efficiency value and the second efficiency value, that is, 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 blade is the tip clearance design value tip_design(i), and change the outlet temperature T of the specified stage i+1 At the same time, the actual efficiency of the specified stage is obtained, so that the actual efficiency is equal to the difference between the third efficiency value and the efficiency difference value, and the outlet temperature of the specified stage at this time is recorded as the outlet temperature calculation value T' i+1 ;

[0064] g. Calculate the quantity T' based on the outlet temperature i+1 , outlet pressure P of the specified stage i+1 , compressor outlet pressure P N+1 And the compressor outlet temperature calculation quantity T′ is obtained by specifying the design value of the efficiency from the stage to the compressor outlet eff(i+1~N+1) N+1 ;

[0065] h. Calculate the quantity T' based on the compressor outlet temperature N+1 , compressor inlet pressure P 1 , compressor inlet temperature T 1 and the compressor outlet pressure P N+1The actual overall efficiency eff(1~N+1)′ of the compressor is obtained when the tip clearance of the rotor blade of the specified stage is the tip clearance excess value tip_real(i).

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

[0067] In a specific embodiment, step a comprises:

[0068] Get the compressor inlet pressure P 1 , compressor inlet temperature T 1 , compressor outlet pressure P N+1 and the compressor outlet temperature T N+1 ;

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

[0070]

[0071]

[0072] Among them, eff(1~N+1) is the design value of the whole machine efficiency, N is the number of compressor stages, P 1 is the compressor inlet pressure, P N+1 is the outlet pressure of the compressor, T 1 is the compressor inlet temperature, T N+1 is the compressor outlet temperature, C p0 =0.239111645, b 1 =-1.3877943E-05, b 2 =1.305071516E-07, b 3 =-5.499968112E-10, b 4 =1.390879692E-12, b 5 =-1.45325748E-15, b 6 =5.290596006E-19; Rg=29.2712[(kgf·m) / (kg·K)]; J=426.935[(kgf·m) / (kcal)];

[0073] Among them, P 1 , P N+1 , T 1 and T N+1 The values ​​are measured when the tip clearance of each level of compressor blades is 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 step d and step 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 by the following formula:

[0076]

[0077] Wherein, eff(i~i+1) is the third efficiency value, P i is the inlet pressure of the specified level; P i+1 is the outlet pressure of the specified stage, T i is the inlet temperature of the specified stage, T i+1 is the outlet temperature of the specified stage;

[0078] Among them, P i , P i+1 , T i and T i+1 Both are measured when the tip clearance of the rotor blades of the specified stage is the design value of the tip clearance.

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

[0080] Further, in a specific embodiment, in step g, the compressor outlet temperature calculation amount is calculated by 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, T′ i+1 is the outlet temperature calculation quantity, P i+1 is the outlet pressure of the specified stage, P N+1 is the outlet pressure of the compressor, T′ N+1 It is the calculated value of compressor outlet temperature.

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

[0084]

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

[0086] The compressor aerodynamic performance analysis method can quickly and accurately analyze the effect of the tip clearance change of a single-row blade on the performance of a multi-stage axial flow compressor. While improving accuracy, it shortens the calculation and analysis time and speeds up the development progress.

[0087] On the other hand, according to some embodiments of the present application, a compressor aerodynamic performance analysis system is also provided, such as Figure 3 shows a schematic diagram of some embodiments of the 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. Usually, a row of stators and a row of rotors are combined into one stage 100, and the last stage includes 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 of the compressor stator blade and the outlet of the compressor, wherein the first sensor 21 is used to sense the temperature of the inlet section 20 of each stage of the compressor and the outlet section 20 of the compressor, and the second sensor 22 is used to sense the pressure of the inlet section 20 of each stage of the compressor and the outlet section 20 of the compressor; wherein the analysis system also includes:

[0089] a memory for storing instructions executable by a processor;

[0090] A processor is used to execute instructions to implement the compressor aerodynamic performance analysis method recorded in one or more embodiments as described above.

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

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

[0093] In a specific embodiment, the first sensor is a total temperature blade profile sensing portion, and the second sensor is a total pressure blade profile sensing portion.

[0094] According to another aspect of the present application, the present application also provides a computer-readable medium. The above-mentioned computer-readable medium provided by the present disclosure has computer instructions thereon. When the computer instructions are executed by a processor, the program can be executed by the processor to implement the steps executed by the program in the compressor aerodynamic performance analysis method as described in the above embodiment.

[0095] It can be understood that the processor in the previous embodiment, such as a system on a chip (SOC), a microcontroller, a microprocessor (e.g., a single-chip microcomputer), a reduced instruction set computer (RISC), an application-specific integrated circuit (ASIC), an application-specific instruction integrated processor (ASIP), a central processing unit (CPU), a graphics processing unit (GPU), a physical processing unit (PPU), a microcontroller unit, a digital signal processor (DSP), a field programmable gate array (FPGA), an advanced RISC machine (ARM), a programmable logic device (PLD), any circuit or processor capable of performing one or more functions, and a combination of one or more of the above.

[0096] The steps of the method 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 the two. The software module may reside in a RAM memory, a flash memory, a ROM memory, an EPROM memory, an EEPROM memory, a register, a hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art. An exemplary storage medium is coupled to a processor so that the processor can read and write information from / to the storage medium. In an alternative, a storage medium may be integrated into a processor. The processor and the storage medium may reside in an ASIC. The ASIC may reside in a user terminal. In an alternative, the processor and the storage medium may reside in a user terminal as discrete components.

[0097] In one or more exemplary embodiments, the functions described may be implemented in hardware, software, firmware, or any combination thereof. If implemented as a computer program product in software, each function may be stored on or transmitted by a computer-readable medium as one or more instructions or codes. Computer-readable media include both computer storage media and communication media, including any medium that facilitates the transfer of a computer program from one place to another. Storage media may be any available medium that can be accessed by a computer. As an example and not limitation, such a computer-readable medium may include RAM, ROM, EEPROM, CD-ROM or other optical disk storage, disk storage or other magnetic storage device, or any other medium that can be used to carry or store the desired program code in the form of an instruction or data structure and can be accessed by a computer. Any connection is also properly referred to as a computer-readable medium. For example, if the software is transmitted from a website, server, or other remote source using a coaxial cable, fiber optic cable, twisted pair, digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwaves, the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwaves are included in the definition of the medium. Disk and disc as used herein include compact disc (CD), laser disc, optical disc, digital versatile disc (DVD), floppy disk and Blu-ray disc, wherein disk often reproduces data magnetically, while disc reproduces data optically with lasers. Combinations of the above should also be included within the scope of computer-readable media.

[0098] The present invention is further described below by 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 following table, where T1 to T8 represent the inlet section temperature of the 1st to 8th stage, and T9 represents the outlet section temperature of the compressor. Similarly, P1 to P8 represent the inlet section pressure of the 1st to 8th stage, and P9 represents the outlet section pressure of the compressor. The efficiency of the 8-stage compressor calculated from the data in the table is 78.40%.

[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 tip clearance of the fifth stage exceeds the tolerance after machining, the tip clearance exceeds the tolerance by 0.1mm. Numerical simulation calculations are carried out for the tip clearance of the fifth stage rotor at two states, a and a+0.1mm. The efficiencies corresponding to the two sets of clearances are obtained to be 87.90% and 86.90% respectively. The tip clearance of the fifth stage exceeds the tolerance by 0.1mm, and the influence on the efficiency of the fifth stage is 1%.

[0103] According to P5, P6, T5, and T6, the efficiency of the fifth stage under the design gap is 81.96%. Adjusting T6 reduces the efficiency of this stage by 1%. At this time, the efficiency of this stage is 80.96%. The corresponding T′ 6 Equal to 468.5.

[0104] First, calculate eff(6~9), that is, substitute P6, P9, T6, T9 into formula 1, and calculate eff(6~9)=87.77%. According to eff(6~9), P6, T′ 6 , P9 calculates the new T9, namely T′ 9 =598.6

[0105] According to T1, P1, P9, T′ 9 The new eff(1~9)′=78.235% is calculated. Therefore, the analysis result can be obtained that the machining tolerance of the 5th stage tip clearance is 0.1mm, which affects the overall efficiency of the eight-stage compressor by about 78.40%-78.24%=0.16%.

[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 following table, where T1 to T7 represent the inlet section temperature of the 1st to 7th stage, and T8 represents the outlet section temperature of the compressor. Similarly, P1 to P7 represent the inlet section pressure of the 1st to 7th stage, and P8 represents the outlet section pressure of the compressor. The efficiency of the 7-stage compressor calculated from the data in the table is 78.65%.

[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 4th level blade tip clearance exceeds the tolerance after machining, the blade tip clearance exceeds the tolerance by 0.1mm;

[0110] Numerical simulation calculations were carried out for the two states of the 4th-stage rotor tip clearance a and a+0.1mm, and the efficiencies corresponding to the two sets of clearances were obtained to be 88% and 86.78% respectively. It was found that the 4th-stage tip clearance exceeded the tolerance by 0.1mm, and the impact on the 4th-stage efficiency was 1.22%.

[0111] According to P4, P5, T4, and T5, the efficiency of the fourth stage under the design gap is 86.48%. Adjusting T5 reduces the efficiency of this stage by 1.22%. At this time, the efficiency of this stage is 85.26%. The corresponding T′ 5 Equal to 428.5.

[0112] First, calculate eff(5~8), that is, substitute P6, P8, T5, T8 into formula 1, and calculate eff(5~8)=86.31%. According to eff(5~8), P5, T′ 5 , P8 calculates the new T8, namely T′ 9 =550.6

[0113] 6) According to T1, P1, P8, T′ 8 The new eff(1~8)′=78.46% is calculated. Therefore, the analysis result shows that the 0.1mm machining tolerance of the 4th stage tip clearance has an impact on the overall efficiency of the 7th stage compressor of about 78.65%-78.46%=0.19%.

[0114] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0115] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them; although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope of the technical solutions of the embodiments of the present application, and they should all be included in the scope of the claims and specification of the present application. In particular, as long as there is no structural conflict, the various technical features mentioned in the various embodiments can be combined in any way. The present application is not limited to the specific embodiments disclosed herein, but includes all technical solutions that fall within the scope of the claims.

Claims

1. A method for analyzing the aerodynamic performance of a compressor. It is characterized in that The steps include: a. Obtain the design value of the compressor's overall efficiency; b. Obtain the tip clearance tolerance value and tip clearance design value of any specified stage rotor blade of the compressor; c. simulating and obtaining a first efficiency value of the specified stage in the compressor when the tip clearance of the rotor blade of the specified stage is the tip clearance excess value; d. simulating and obtaining a second efficiency value of the specified stage in the compressor when the tip clearance of the rotor blade of the specified stage is the tip clearance design value; e. obtaining the efficiency difference between the first efficiency value and the second efficiency value; f. calculating a third efficiency value of the specified stage in the compressor when the tip clearance of the specified stage rotor blade is the tip clearance design value, changing the outlet temperature of the specified stage, and obtaining the actual efficiency of the specified stage at the same time, 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 of the specified stage at this time as the outlet temperature calculation amount; g. Obtaining the calculated compressor outlet temperature according to the calculated outlet temperature, the outlet pressure of the designated stage, the outlet pressure of the compressor, and the design value of the efficiency from the designated stage to the compressor outlet; h. obtaining the actual overall efficiency of the compressor when the tip clearance of the rotor blades of the specified stage is the tip clearance excess value based on the calculated compressor outlet temperature, the compressor inlet pressure, the compressor inlet temperature and the compressor outlet pressure.

2. The compressor aerodynamic performance analysis method according to claim 1, It is characterized in that The step a comprises: Obtaining the compressor inlet pressure, compressor inlet temperature, compressor outlet pressure and compressor outlet temperature; The overall efficiency design value is calculated by the following formula: Among them, eff(1~N+1) is the design value of the whole machine efficiency, N is the number of compressor stages, P 1 is the compressor inlet pressure, P N+1 is the outlet pressure of the compressor, T 1 is the compressor inlet temperature, T N+1 is the compressor outlet temperature, C p0 =0.239111645, b 1 =-1.3877943E-05, b 2 =1.305071516E-07, b 3 =-5.499968112E-10, b 4 =1.390879692E-12, b 5 =-1.45325748E-15, b 6 =5.290596006E-19; R g =29.2712[(kgf·m) / (kg·K)]; J=426.935[(kgf·m) / (kcal)]; Among them, P 1 , P N+1 , T 1 and T N+1 All of them are measured when the tip clearance of blades at each stage of the compressor is the design value.

3. The compressor aerodynamic performance analysis method according to claim 1, It is 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 according to claim 2, It is characterized in that In the step f, the third efficiency value is calculated by the following formula: Wherein, eff(i~i+1) is the third efficiency value, P i is the inlet pressure of the specified stage; P i+1 is the outlet pressure of the specified stage, T i is the inlet temperature of the specified stage, T i+1 is the outlet temperature of the specified stage; Among them, P i , P i+1 , T i and T i+1 Both are measured when the tip clearance of the rotor blades of the specified stage is the design value of the tip clearance.

5. The compressor aerodynamic performance analysis method according to claim 4, It is characterized in that In step g, the compressor outlet temperature calculation amount is calculated by 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, T′ i+1 is the outlet temperature calculation quantity, P i+1 is the outlet pressure of the specified stage, P N+1 is the outlet pressure of the compressor, T′ N+1 It is the calculated value of compressor outlet temperature.

6. The compressor aerodynamic performance analysis method according to claim 5, It is characterized in that The design value of the efficiency from the specified stage outlet to the compressor outlet is calculated by the following formula:

7. The compressor aerodynamic performance analysis method according to claim 6, It is characterized in that The actual overall efficiency of the compressor in step h is calculated by the following formula: Wherein, eff(1~N+1)′ is the actual overall efficiency of the compressor when the tip clearance of the rotor blade of the specified stage is the tip clearance excess value.

8. A readable medium having a computer program thereon, It is characterized in that The program is executed by a 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, It is characterized in that include: A first sensor and a second sensor are installed at the inlet of each stage of the compressor stator blade and the outlet of the compressor, wherein the first sensor is used to sense the temperature of the inlet section and the outlet section of the compressor at each stage, and the second sensor is used to sense the pressure of the inlet section and the outlet section of the compressor at each stage; wherein the analysis system further comprises: a memory for storing instructions executable by a processor; A processor, configured to execute the instructions to implement the compressor aerodynamic performance analysis method according to any one of claims 1 to 7.

10. The compressor aerodynamic performance analysis system according to claim 9, It is characterized in that The first sensor is a total temperature blade profile sensing part, and the second sensor is a total pressure blade profile sensing part.

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