A compressor stability enhancement design method, device, computer equipment and medium

Abstract

The present application relates to a compressor stability enhancement design method, device, computer equipment and medium. The method includes: first, performing numerical simulation on the target compressor blade to determine the flow separation region on the suction surface of each blade height section, and then determining the starting position, height and cut-off position of the stability enhancement structure according to the position of the flow separation region, the dimensionless value of the blade chord length and the dimensionless value of the maximum blade thickness; finally, obtaining the stability enhancement structures generated on all or part of the blade height sections within the entire blade height range of the same blade, constructing a compressor stability enhancement device, and controlling the oncoming flow above the target compressor blade to transition from laminar flow to turbulent flow through the compressor stability enhancement device, thereby enhancing the blade's anti-backpressure ability and delaying the process of flow separation migration on the blade suction surface, and significantly expanding the stable operating range of the compressor blade while controlling and maintaining the compressor efficiency.

Description

Technical Field

[0001] This application relates to the technical field of compressor stability augmentation, and particularly to a compressor stability augmentation design method, device, computer device, and medium. Background Art

[0002] With the continuous improvement of the development goals of high-performance aero-engines, there is an increasing demand for its important core component - the compressor to simultaneously have the ability to operate stably at higher loads and within a wider range. When increasing the compressor stage load, the most direct method is to increase the rotor tangential speed to enhance its work capacity. However, limited by the strength of the structural materials and the flow losses caused by high tip speeds, the speed cannot be increased indefinitely. In addition, under high-load operating conditions, the degree of pressure recovery in the compressor blade passage increases, that is, the adverse pressure gradient in the passage is higher, which is more likely to cause flow separation, further reducing the efficiency and stability of the compressor. However, the stable operating range of the compressor has a very important impact on the reliable operation of the whole machine. If non-steady operating conditions such as whole-machine surge are to be avoided and the engine operating range is to be broadened, first of all, the stable operating margin of the compressor must be ensured to be large enough.

[0003] In recent years, a large number of studies have been continuously carried out to reduce the flow loss of compressors and increase the stable operating range of compressors. Scholars generally summarize it as the compressor stability augmentation and flow control technology, whose essence is to use corresponding technical means to change and control the flow state of gas in order to achieve the purpose of improving the performance of the compressor. The current flow stability augmentation technologies applied in compressors can be roughly divided into two categories according to whether they consume external energy: one is the technology that requires external equipment to input energy into the gas in the compressor and establish a control loop, which is called the active flow control technology. The advantage of this technology is that the effect is obvious and it is flexible to use, while the disadvantage is that it requires additional auxiliary devices and control systems, increasing the weight of the engine and the system complexity. The active flow control technology generally includes technologies such as blade jets, endwall jets, tip blowing, etc. mainly based on blowing, and technologies such as endwall boundary layer suction, blade boundary layer suction, etc. mainly based on suction. Compared with the active flow control technology, another passive flow control technology that does not consume external energy and controls the gas flow state by adjusting and changing the blade passage structure is more feasible and operable, and has been widely applied to aeroengines. Due to its strong engineering realizability, these methods are also the focus of current relevant researchers. According to their action modes and positions, they can be divided into methods such as endwall profiling, vortex generators, and casing treatments. In the actual application process, it is also possible to achieve the purpose of stability augmentation by combining one or more methods. However, for the passive flow control technology, it is difficult to significantly increase the stable operating range of the compressor under the condition of basically unchanged efficiency by a single method. Either the stable operating range is increased, but its efficiency is greatly lost; or the efficiency is increased, but the impact on the stable operating range is limited. Summary of the Invention

[0004] Based on this, in view of the above technical problems, it is necessary to provide a compressor stability augmentation design method, device, computer equipment, and medium that can enhance the stable operating margin and range of the compressor while maintaining the compressor efficiency.

[0005] A compressor stability augmentation design method, the method comprising:

[0006] Perform numerical simulation on the blades of the target compressor to determine the flow separation regions on the suction surfaces of each blade height section, and upstream of the starting position of the flow separation region, determine the starting position of the stability augmentation structure according to the blade chord length;

[0007] Generate a tangent line of the suction surface curve at the starting position, draw a perpendicular line with a set size along the tangent line of the suction surface curve to intersect with the suction surface curve, and the intersection point of the perpendicular line with the set size and the suction surface curve is located near the flow separation region;

[0008] Determine the height of the stability augmentation structure based on the set - size vertical line and the maximum blade thickness, and determine the cut - off position of the stability augmentation structure according to the intersection point of the set - size vertical line and the tangent of the suction surface curve;

[0009] Determine the stability augmentation structure generated on any blade - height cross - section based on the starting position, height, and cut - off position, obtain the stability augmentation structures generated on all or some blade - height cross - sections within the entire blade height range of the same blade, construct a compressor stability augmentation device, and control the oncoming flow above the target compressor blade to transition from laminar flow to turbulent flow through the compressor stability augmentation device. At the same time, suppress the upstream propagation of the separated flow downstream during the process of increasing back - pressure to achieve the stability augmentation of the compressor blade.

[0010] In one embodiment, upstream of the starting position of the flow separation region, determine the starting position of the stability augmentation structure according to the blade chord length, including:

[0011] According to the oncoming flow direction above the suction surface, upstream of the starting position of the flow separation region, determine the starting position of the stability augmentation structure according to the dimensionless value of the blade chord length; wherein, the value range of the starting position is 0% - 90% of the dimensionless value of the blade chord length.

[0012] In one embodiment, starting from the starting position of the stability augmentation structure, the oncoming flow above the suction surface flows downstream along the tangent of the suction surface curve.

[0013] In one embodiment, determine the height of the stability augmentation structure according to the set - size vertical line and the maximum blade thickness, including:

[0014] Near the flow separation region, determine the height of the stability augmentation structure according to the set - size vertical line; wherein, the value range of the height is 0% - 40% of the dimensionless value of the maximum blade thickness.

[0015] In one embodiment, on different blade - height cross - sections, by adjusting the dimensionless values of the blade structure parameters, the starting position, height, and cut - off position of the generated stability augmentation structure are uncertain; wherein, the blade structure parameters include the blade chord length and the maximum blade thickness.

[0016] A compressor stability augmentation device is prepared by the above - mentioned compressor stability augmentation design method.

[0017] In one embodiment, within the entire blade height range of the same blade, the distribution form of the compressor stability augmentation device includes full - blade - height distribution, partial - blade - height distribution, and segmented distribution.

[0018] A computer device includes a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, the following steps are implemented:

[0019] Perform numerical simulation on the target compressor to determine the flow separation region on the suction surface of each blade height section. Upstream of the starting position of the flow separation region, determine the starting position of the stability enhancement structure according to the blade chord length;

[0020] Generate a tangent line of the suction surface curve at the starting position, draw a perpendicular line of a set size along the tangent line of the suction surface curve to intersect with the suction surface curve, and the intersection point of the perpendicular line of the set size and the suction surface curve is near the flow separation region;

[0021] Determine the height of the stability enhancement structure according to the perpendicular line of the set size and the maximum blade thickness, and determine the cut-off position of the stability enhancement structure according to the intersection point of the perpendicular line of the set size and the tangent line of the suction surface curve;

[0022] Determine the stability enhancement structure generated on any blade height section according to the starting position, height and cut-off position, obtain the stability enhancement structures generated on all or part of the blade height sections within the entire blade height range of the same blade, construct a compressor stability enhancement device, and control the oncoming flow above the target compressor blade to transition from laminar flow to turbulent flow through the compressor stability enhancement device, while suppressing the upstream propagation of the separated flow downstream of the oncoming flow during the process of increasing back pressure, so as to achieve the stability enhancement of the compressor blade.

[0023] A computer-readable storage medium, on which a computer program is stored. When the computer program is executed by a processor, the following steps are implemented:

[0024] Perform numerical simulation on the target compressor blade to determine the flow separation region on the suction surface of each blade height section. Upstream of the starting position of the flow separation region, determine the starting position of the stability enhancement structure according to the blade chord length;

[0025] Generate a tangent line of the suction surface curve at the starting position, draw a perpendicular line of a set size along the tangent line of the suction surface curve to intersect with the suction surface curve, and the intersection point of the perpendicular line of the set size and the suction surface curve is near the flow separation region;

[0026] Determine the height of the stability enhancement structure according to the perpendicular line of the set size and the maximum blade thickness, and determine the cut-off position of the stability enhancement structure according to the intersection point of the perpendicular line of the set size and the tangent line of the suction surface curve;

[0027] Determine the stability enhancement structure generated on any blade height section according to the starting position, height and cut-off position, obtain the stability enhancement structures generated on all or part of the blade height sections within the entire blade height range of the same blade, construct a compressor stability enhancement device, and control the oncoming flow above the target compressor blade to transition from laminar flow to turbulent flow through the compressor stability enhancement device, while suppressing the upstream propagation of the separated flow downstream of the oncoming flow during the process of increasing back pressure, so as to achieve the stability enhancement of the compressor blade.

[0028] The above compressor stability augmentation design method determines the flow separation region on the suction surface of the blade at the blade height section through numerical simulation of the target compressor blade. Upstream of the starting position of the flow separation region, the starting position of the stability augmentation structure is determined according to the blade chord length. Then, a tangent line of the suction surface curve is generated at the starting position of the stability augmentation structure, and a perpendicular line of a set size is drawn along the tangent line to intersect with the suction surface curve. Next, the height of the stability augmentation structure is determined according to the perpendicular line of the set size and the maximum blade thickness, and the cut-off position of the stability augmentation structure is determined according to the intersection point of the perpendicular line of the set size and the tangent line. Finally, the stability augmentation structure generated on any blade height section is determined according to the above starting position, height, and cut-off position, and the stability augmentation structures generated on all or part of the blade height sections within the entire blade height range of the same blade are obtained to construct a compressor stability augmentation device. The incoming flow above the target compressor blade is controlled by the compressor stability augmentation device to transition from laminar flow to turbulent flow, thereby enhancing the blade's ability to resist backpressure and delaying the migration process of flow separation on the blade suction surface. On the premise of controlling and maintaining the compressor efficiency, the stable operating range of the compressor blade is greatly expanded. In addition, the present application also constructs a compressor stability augmentation device on the compressor blade according to the above compressor stability augmentation design method, which can achieve stability augmentation without carrying external devices and consuming external energy, has a compact structure, and reduces the mass and complexity of the compressor system. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is a schematic flow chart of a compressor stability augmentation design method in an embodiment;

[0030] Figure 2 It is a schematic diagram of generating a stability augmentation structure on any blade height section in an embodiment

[0031] Figure 3 It is a three-dimensional structure schematic diagram of a compressor stability augmentation device in an embodiment;

[0032] Figure 4 It is a three-dimensional structure schematic diagram of compressor stability augmentation devices with different distribution forms in an embodiment: (a) is a compressor stability augmentation device with partial blade height distribution, and (b) is a compressor stability augmentation device with segmented distribution;

[0033] Figure 5 It is a schematic diagram of comparing the performance of the stability augmentation processed cascade with the original configuration in an embodiment;

[0034] Figure 6 It is an internal structure diagram of a computer device in an embodiment. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0035] In order to make the objectives, technical solutions and advantages of the present application more clear and understandable, the present application will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0036] In one embodiment, as Figure 1 shown, a compressor stability enhancement design method is provided, including the following steps:

[0037] Step S1: First, perform numerical simulation on the target compressor blade to determine the flow separation region on the suction surface of each blade height section. Upstream of the starting position of the flow separation region, determine the starting position of the stability enhancement structure according to the blade chord length.

[0038] Step S2: Then, generate a tangent line of the suction surface curve at the starting position of the stability enhancement structure, and draw a perpendicular line with a set size along the tangent line of the suction surface curve to intersect with the suction surface curve. The intersection point of the perpendicular line with the set size and the suction surface curve is located near the flow separation region.

[0039] Step S3: Next, determine the height of the stability enhancement structure according to the perpendicular line with the set size and the maximum blade thickness, and determine the cut-off position of the stability enhancement structure according to the intersection point of the perpendicular line with the set size and the tangent line of the suction surface curve.

[0040] Step S4: Finally, determine the stability enhancement structure generated on any blade height section according to the above starting position, height and cut-off position, obtain the stability enhancement structures generated on all or part of the blade height sections within the entire blade height range of the same blade, construct a compressor stability enhancement device, and control the oncoming flow above the target compressor blade to transition from laminar flow to turbulent flow through the compressor stability enhancement device, while suppressing the forward propagation of the separated flow downstream of the oncoming flow during the increase in back pressure, so as to achieve the stability enhancement of the compressor blade.

[0041] Specifically, as Figure 2As shown, for any blade height section of the target compressor blade, Inflow is the inflow direction, and Outflow is the outflow direction. First, by numerically simulating the target compressor, the parameters of any blade height can be obtained. Thus, the DE region on the suction surface of each blade height section is determined as the flow separation region under the target operating condition. Then, upstream of the starting position D of the flow separation region, the starting position of the stabilization structure is determined as point A. The position of point A is determined by the dimensionless value of the blade chord length λ, ranging from 0% to 90% of the dimensionless value of the blade chord length λ. Then, a tangent line AC is drawn to the suction surface curve at the starting position A, ensuring that the incoming flow field above the suction surface is almost undeflected from point A and continues to flow downstream along the new tangent line AC. A perpendicular line BC is then drawn along the tangent line AC to intersect the suction surface curve. The intersection point B of the perpendicular line BC and the suction surface curve is located within the flow separation region DE. The intersection C of the vertical line BC and the tangent line AC is the end position of the stabilizer structure. The height of the vertical line BC is the height of the stabilizer structure. The height is determined by the dimensionless value of the maximum blade thickness tmax, and the value range is 0% to 40% of the dimensionless value of the maximum blade thickness tmax. The above steps can be used to determine the starting position, height, and end position of the stabilizer structure for any blade height section. Repeating these steps for each blade height section will eventually construct the compressor stabilizer.

[0042] It can be understood that the process of the compressor gradually approaching the stall area from the stable working point and thus leaving the stable operation occurs when the downstream back pressure continues to increase and the reverse pressure gradient in the channel continues to increase, resulting in large-scale flow separation. Since there is often a large-scale separation on the back side of the compressor blade, that is, the suction side, this part of the separated flow continues to move upstream as the back pressure increases. At the same time, in some cases, it will also merge with the separated flow in the corner area. This flow feature is closely related to the instability of the compressor blade. Therefore, in order to delay the process of flow separation migrating on the suction side, that is, to expand the stable working range of the blade, the present application uses the above-mentioned compressor stabilization design method, combined with the original flow field characteristics and information of the blade channel, to construct a compressor stabilization device with a rear step structure, thereby effectively controlling the position of the area where the laminar flow area on the compressor blade transitions to turbulent flow, enhancing the blade channel's ability to resist back pressure, and suppressing the trend of the downstream flow separation area forward or deteriorating upstream under variable back pressure or variable angle of attack. Under the premise of controlling losses, the stable working range of the blade is greatly improved.

[0043] In one embodiment, the starting position, height and end position of the generated stabilization structure are uncertain on different blade height sections by adjusting the dimensionless values of the blade structural parameters; wherein the blade structural parameters include the blade chord length λ and the blade maximum thickness tmax.

[0044] It should be understood that although Figure 1The steps in the flowchart are shown in sequence according to the arrows, but these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise specified in this document, there is no strict order restriction for the execution of these steps, and these steps can be executed in other orders. Moreover, Figure 1 at least a portion of the steps may include multiple sub-steps or multiple stages. These sub-steps or stages are not necessarily completed at the same time, but can be executed at different times. The execution order of these sub-steps or stages is not necessarily sequential, but can be executed alternately or in rotation with at least a portion of other steps or sub-steps or stages of other steps.

[0045] In one embodiment, according to the above-described compressor stability enhancement design method, a compressor stability enhancement device is provided, as Figure 3 shown. The distribution form of the compressor stability enhancement device within the entire blade height range of the same blade is full-span distribution, and the stability enhancement structures generated by each blade height section have the same starting position, height, and cut-off position.

[0046] Specifically, as Figure 4 shown, the distribution form of the compressor stability enhancement device within the entire blade height range of the same blade further includes partial-span distribution, segmented distribution, and other forms. Among them, Figure 4 (a) shows a compressor stability enhancement device with partial-span distribution. Within the entire blade height range h of the same blade, a stability enhancement structure is generated only within the blade height range of length l, and the stability enhancement structures generated by each blade height section within this range have the same starting position, height, and cut-off position; Figure 4 (b) shows a compressor stability enhancement device with segmented distribution. Within the entire blade height range of the same blade, stability enhancement structures are generated for all blade height sections, but the stability enhancement structures in different segments have different starting positions, heights, and cut-off positions. For different target operating conditions, compressor stability enhancement devices with different distribution forms can be selected for stability enhancement.

[0047] For the specific limitations of the compressor stability enhancement device, reference can be made to the limitations of the compressor stability enhancement design method in the above text, which will not be elaborated here.

[0048] Furthermore, the present application also takes the flow of a supersonic cascade as an example to verify the effect of a compressor stability-enhancing design method proposed above. The basic parameters of the supersonic cascade are shown in Table 1. The inlet Mach number is greater than 1, and its flow characteristic is that there is flow separation and reattachment at the foot of the oblique shock wave on the suction surface, forming a closed separation bubble along the blade height direction. According to the method proposed above, the starting position point A of the stability-enhancing structure is arranged at 33% of the axial chord length, and the height of the stability-enhancing structure is 15.6% of the maximum blade thickness. The stability-enhancing structure can be determined based on these two dimensions, and the total mass accounts for 1.5% of the original blade. The same parameters are used within the full blade height range. Figure 5 The curves of the angle of attack and loss distribution after the stability-enhancing treatment are given. Compared with the original cascade configuration, the angle of attack range of the cascade after the stability-enhancing treatment is increased by nearly 46%, greatly broadening the working range of the supersonic cascade. In addition, in terms of loss, the stability-enhancing cascade does not bring obvious loss to the prototype cascade. Its distribution trend and law are the same as those of the prototype cascade. At an angle of attack of +0.5, its performance is even better than that of the prototype cascade. Within the entire positive angle of attack range, the increase in its loss is less than 2%. Thus, the purpose of greatly improving the stable operating margin of the compressor while maintaining the efficiency is achieved, further supporting the feasibility of the method proposed in the present invention.

[0049] Table 1 Basic parameters of the supersonic cascade

[0050] parameter numerical value blade chord length λ 125 mm pitch 87.5 mm blade height h 167.5 mm installation angle 48.5° bend angle 8.8° designed inlet airflow angle 57.7° inlet Mach number 1.09

[0051] According to the method proposed above, the starting position point A of the stability-enhancing structure is arranged at 33% of the axial chord length, and the height of the stability-enhancing structure is 15.6% of the maximum blade thickness. The stability-enhancing structure can be determined based on these two dimensions, and the total mass accounts for 1.5% of the original blade. The same parameters are used within the full blade height range. Figure 5 The curves of the angle of attack and loss distribution after the stability-enhancing treatment are given. Compared with the original cascade configuration, the angle of attack range of the cascade after the stability-enhancing treatment is increased by nearly 46%, greatly broadening the working range of the supersonic cascade. In addition, in terms of loss, the stability-enhancing cascade does not bring obvious loss to the prototype cascade. Its distribution trend and law are the same as those of the prototype cascade. At an angle of attack of +0.5, its performance is even better than that of the prototype cascade. Within the entire positive angle of attack range, the increase in its loss is less than 2%. Thus, the purpose of greatly improving the stable operating margin of the compressor while maintaining the efficiency is achieved, further supporting the feasibility of the method proposed in the present invention.

[0052] In one embodiment, a computer device is provided. The computer device can be a terminal, and its internal structure diagram can be as Figure 6As shown in the figure. The computer device includes a processor, a memory, a network interface, a display screen, and an input device connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs in the non-volatile storage medium. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, it realizes a compressor stability enhancement design method. The display screen of the computer device can be a liquid crystal display screen or an electronic ink display screen. The input device of the computer device can be a touch layer covering the display screen, or buttons, trackballs, or touchpads provided on the outer shell of the computer device, or an external keyboard, touchpad, or mouse, etc.

[0053] Those skilled in the art can understand that Figure 6 the structure shown in the figure is only a block diagram of some structures related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine some components, or have different component arrangements.

[0054] In one embodiment, a computer device is provided, including a memory and a processor. The memory stores a computer program. When the processor executes the computer program, the following steps are implemented:

[0055] Perform numerical simulation on the target compressor blade to determine the flow separation region on the suction surface of each blade height section. Upstream of the starting position of the flow separation region, determine the starting position of the stability enhancement structure according to the blade chord length;

[0056] Generate a tangent line of the suction surface curve at the starting position, draw a perpendicular line with a set size along the tangent line of the suction surface curve to intersect with the suction surface curve. The intersection point of the perpendicular line with the set size and the suction surface curve is located near the flow separation region;

[0057] Determine the height of the stability enhancement structure according to the perpendicular line with the set size and the maximum thickness of the blade, and determine the cut-off position of the stability enhancement structure according to the intersection point of the perpendicular line with the set size and the tangent line of the suction surface curve;

[0058] Determine the stability enhancement structure generated on any blade height section according to the starting position, height, and cut-off position, obtain the stability enhancement structures generated on all or some blade height sections within the entire blade height range of the same blade, construct a compressor stability enhancement device, and control the oncoming flow above the target compressor blade to transition from laminar flow to turbulent flow through the compressor stability enhancement device, while suppressing the forward propagation of the separated flow downstream of the oncoming flow during the process of increasing the back pressure, so as to achieve the stability enhancement of the compressor blade.

[0059] In one embodiment, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the following steps are implemented:

[0060] Perform numerical simulation on the target compressor blade to determine the flow separation region on the suction surface of each blade height section. Upstream of the starting position of the flow separation region, determine the starting position of the stability augmentation structure according to the blade chord length;

[0061] Generate a tangent line of the suction surface curve at the starting position, draw a perpendicular line of a set size along the tangent line of the suction surface curve to intersect with the suction surface curve, and the intersection point of the perpendicular line of the set size and the suction surface curve is located near the flow separation region;

[0062] Determine the height of the stability augmentation structure according to the perpendicular line of the set size and the maximum blade thickness, and determine the cut-off position of the stability augmentation structure according to the intersection point of the perpendicular line of the set size and the tangent line of the suction surface curve;

[0063] Determine the stability augmentation structure generated on any blade height section according to the starting position, height, and cut-off position, obtain the stability augmentation structures generated on all or part of the blade height sections within the entire blade height range of the same blade, construct a compressor stability augmentation device, and control the oncoming flow above the target compressor blade to transition from laminar flow to turbulent flow through the compressor stability augmentation device, while suppressing the forward propagation of the separated flow downstream of the oncoming flow during the increase of the back pressure, so as to achieve the stability augmentation of the compressor blade.

[0064] Those of ordinary skill in the art can understand that all or part of the processes of implementing the methods in the above embodiments can be completed by instructing relevant hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above methods. Among them, any reference to a memory, storage, database, or other medium used in the embodiments provided in the present application can include non-volatile and / or volatile memories. Non-volatile memories can include read-only memory (ROM), programmable ROM (PROM), electrically programmable ROM (EPROM), electrically erasable programmable ROM (EEPROM), or flash memory. Volatile memories can include random access memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in various forms, such as static RAM (SRAM), dynamic RAM (DRAM), synchronous DRAM (SDRAM), double data rate SDRAM (DDR SDRAM), enhanced SDRAM (ESDRAM), synchronous link (Synchlink) DRAM (SLDRAM), Rambus direct RAM (RDRAM), direct memory bus dynamic RAM (DRDRAM), and Rambus dynamic RAM (RDRAM), etc.

[0065] The technical features of the above embodiments can be combined arbitrarily. For the sake of brevity of description, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered as the scope described in this specification.

[0066] The above-described embodiments merely represent several implementation manners of the present application. The description thereof is relatively specific and detailed, but it should not be construed as a limitation on the scope of the invention patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present application, several modifications and improvements can still be made, and these all belong to the protection scope of the present application. Therefore, the protection scope of the patent of the present application shall be subject to the appended claims.

Claims

1. A compressor stability improvement design method, characterized in that, The method includes: Performing numerical simulation on the target compressor blade to determine the flow separation region on the suction surface of each blade height section, and upstream of the starting position of the flow separation region, determining the starting position of the stability augmentation structure according to the blade chord length; Generating a tangent line of the suction surface curve at the starting position, making a perpendicular line with a set size along the tangent line of the suction surface curve to intersect with the suction surface curve, and the intersection point of the perpendicular line with the set size and the suction surface curve is located near the flow separation region; Determining the height of the stability augmentation structure according to the perpendicular line with the set size and the maximum blade thickness, and determining the cut-off position of the stability augmentation structure according to the intersection point of the perpendicular line with the set size and the tangent line of the suction surface curve; Determining the stability augmentation structure generated on any blade height section according to the starting position, height and cut-off position, obtaining the stability augmentation structures generated on all or part of the blade height sections within the entire blade height range of the same blade, constructing a compressor stability augmentation device, and controlling the oncoming flow above the target compressor blade to transition from laminar flow to turbulent flow through the compressor stability augmentation device, and at the same time suppressing the forward propagation of the separated flow downstream during the increase of the back pressure, so as to achieve the stability augmentation of the compressor blade.

2. The method according to claim 1, characterized in that Upstream of the starting position of the flow separation region, determining the starting position of the stability augmentation structure according to the blade chord length, includes: According to the oncoming flow direction above the suction surface, upstream of the starting position of the flow separation region, determining the starting position of the stability augmentation structure according to the dimensionless value of the blade chord length; wherein, the value range of the starting position is 0% to 90% of the dimensionless value of the blade chord length.

3. The method according to claim 2, characterized in that, Starting from the starting position of the stability augmentation structure, the oncoming flow above the suction surface flows downstream along the tangent line of the suction surface curve.

4. The method according to claim 3, wherein Determining the height of the stability augmentation structure according to the perpendicular line with the set size and the maximum blade thickness, includes: Near the flow separation region, determining the height of the stability augmentation structure according to the perpendicular line with the set size; wherein, the value range of the height is 0% to 40% of the dimensionless value of the maximum blade thickness.

5. The method according to claim 1, characterized in that, On different blade height sections, by adjusting the dimensionless values of the blade structure parameters, the starting position, height and cut-off position of the generated stability augmentation structure are uncertain; wherein, the blade structure parameters include the blade chord length and the maximum blade thickness.

6. A compressor stability augmentation device, characterized in that, The device is prepared by the method according to any one of claims 1 to 5.

7. The device according to claim 6, characterized in that, Within the entire blade height range of the same blade, the distribution form of the compressor stability augmentation device includes full blade height distribution, partial blade height distribution and segmented distribution.

8. A computer device, comprising a memory and a processor, the memory storing a computer program, characterized in that, When the processor executes the computer program, it implements the steps of the method according to any one of claims 1 to 5.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the computer program is executed by the processor, it implements the steps of the method according to any one of claims 1 to 5.

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