A design method for active radial clearance based on thermal expansion coefficient customization

Abstract

The present invention provides an active radial clearance design method based on thermal expansion coefficient customization, which relates to the field of aero-engine technology and aims to solve the technical problem that aero-engine clearance design is difficult to meet the rapid and changing requirements of various working conditions. The engine clearance design method includes: obtaining the clearance of the engine under various working conditions, and determining the target clearance of the engine under various working conditions; based on at least one target clearance, determining the target deformation of the casing under the corresponding working condition, where the target deformation is the radial deformation of the casing; based on each target deformation, calculating the target thermal expansion coefficient of the casing under the corresponding working condition; and adjusting the structure of the casing so that the casing meets the target thermal expansion coefficient under the corresponding working condition. The engine clearance design method draws on the idea of active clearance control and utilizes the principle of passive clearance control, so that the customized casing can achieve the required control of the rotational-static clearance under various working conditions according to the target thermal expansion coefficient.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation engines, and in particular to an engine clearance design method, device, engine, equipment and storage medium. Background Art

[0002] The rotor-static clearance of an aircraft engine, that is, the radial clearance between the tip of the rotor blade and the casing (stator), has a very important impact on the performance and safety of the aircraft engine. If the rotor-static clearance is too large, the efficiency of the entire engine will drop sharply; if the rotor-static clearance is too small, it will cause harmful failures caused by friction between the rotor blade tip and the casing.

[0003] In related technologies, the design of the rotor-static clearance of aircraft engines is mainly divided into two categories: active clearance control design and passive clearance control design. Among them, the design method of active clearance control is mainly used in civil engines and ground / ship-based gas turbines. For high-maneuverability aircraft engines, due to the frequent and drastic changes in their throttle, the response speed of active clearance control is slow, and it is difficult to meet the needs of rapid and changing working conditions. In addition, the engine structure based on active clearance control design is complex and has a large mass.

[0004] The statements in this section merely provide background art related to the present invention and do not necessarily constitute prior art. Summary of the Invention

[0005] The purpose of the present invention is to provide an engine clearance design method, device, engine, equipment and storage medium to solve the technical problem that the clearance design of aircraft engines is difficult to meet the rapid and changing requirements of various working conditions.

[0006] In order to achieve the above object, the present invention provides the following technical solutions:

[0007] In a first aspect, an embodiment of the present invention provides a method for designing engine clearance, wherein the clearance is a radial clearance between a rotor blade tip and a casing, the method comprising:

[0008] Obtaining the clearance of the engine under various operating conditions, and determining a target clearance of the engine under various operating conditions;

[0009] Determining a target deformation of the casing under the corresponding working condition based on at least one target gap, wherein the target deformation is a radial deformation of the casing;

[0010] Calculating a target thermal expansion coefficient of the casing under the corresponding working condition based on each target deformation amount;

[0011] The structure of the casing is adjusted so that the casing meets the target thermal expansion coefficient under the corresponding working conditions.

[0012] In a second aspect, an embodiment of the present invention provides an engine designed using the method described in the first aspect.

[0013] In a third aspect, an embodiment of the present invention provides an engine clearance design device, wherein the clearance is a radial clearance between a rotor blade tip and a casing, and the design device includes:

[0014] an acquisition module, configured to acquire the clearance of the engine under various operating conditions and determine a target clearance of the engine under various operating conditions;

[0015] a determination module, configured to determine a target deformation of the casing under the corresponding working condition based on at least one target gap, wherein the target deformation is a radial deformation of the casing;

[0016] a calculation module, configured to calculate a target thermal expansion coefficient of the casing under the corresponding working condition based on each target deformation;

[0017] The processing module is used to adjust the structure of the casing so that the casing meets the target thermal expansion coefficient under the corresponding working condition.

[0018] In a fourth aspect, an embodiment of the present invention provides an electronic device, including:

[0019] processor; and,

[0020] Memory for storing programs;

[0021] The program includes instructions, and when the instructions are executed by a processor, the processor executes the method according to the exemplary embodiment of the present invention.

[0022] In a fifth aspect, an embodiment of the present invention provides a non-transient computer-readable storage medium, wherein the non-transient computer-readable storage medium stores computer instructions, and the computer instructions are used to cause the computer to execute the method according to the exemplary embodiment of the present invention.

[0023] One or more technical solutions provided in the exemplary embodiments of the present invention can achieve at least one of the following beneficial effects.

[0024] The engine clearance design method of the exemplary embodiment of the present invention determines one or more target clearances that can meet each operating condition based on the radial clearance between the rotor blade tip and the casing of the engine under various operating conditions; determines the target deformation of the casing based on the one or more target clearances, so that the target deformation is a known condition, and the target deformation is converted into the target thermal expansion coefficient of the casing under the corresponding operating condition through calculation. The casing structure can be adjusted and verified based on the known target thermal expansion coefficient, and then a casing that meets the target thermal expansion coefficient can be obtained. Based on this, the engine clearance design method of the exemplary embodiment of the present invention draws on the idea of active clearance control and utilizes the principle of passive clearance control, so that the customized casing can achieve the required control of the rotor-static clearance under various operating conditions based on the target thermal expansion coefficient. It is particularly suitable for scenarios where the various operating conditions of high-maneuverability aircraft engines are frequently and drastically switched. Moreover, since only the thermal expansion coefficient of the casing is adjusted, the structural complexity and dead weight of the engine will not be excessively increased. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] The accompanying drawings illustrate exemplary embodiments of the present invention and, together with the description, serve to explain the principles of the present invention. These drawings are included to provide a further understanding of the present invention and are incorporated in and constitute a part of this specification.

[0026] Figure 1 is a schematic flow chart of an engine clearance design method according to an embodiment of the present invention;

[0027] Figure 2 is a schematic structural diagram of a casing according to an embodiment of the present invention;

[0028] Figure 3 is a schematic structural diagram of a casing according to another embodiment of the present invention;

[0029] Figure 4 is a schematic block diagram of modules of a design device according to an embodiment of the present invention;

[0030] Figure 5 is a schematic block diagram of a chip according to an embodiment of the present invention;

[0031] Figure 6 is a structural block diagram of an electronic device according to an embodiment of the present invention.

[0032] Figure numerals: 1. original structure; 2. cylindrical structure; 3. disc structure; 4. flange; 5. bolt. DETAILED DESCRIPTION

[0033] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention more clearly understood, the present invention is 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 invention and are not intended to limit the present invention.

[0034] The design of the rotor-static clearance of an aero-engine is a systematic and professional comprehensive work. The current aero-engine radial clearance includes active clearance control and passive clearance control.

[0035] Active clearance control involves adjusting the gap between the rotor blade tip and the casing inner wall through external intervention. This control method manages the casing temperature and pressure by introducing air of varying temperatures and pressures under varying engine operating conditions, thereby controlling thermal deformation and maintaining a minimum rotor-to-static clearance. However, active clearance control requires additional piping and control components, making the engine structure more complex and heavier.

[0036] Passive clearance control, on the other hand, relies on the engine's internal structural design to control the rotor-to-stationary clearance, rather than relying on external energy sources. Common passive clearance control methods include pre-designing the casing's dimensions and materials, modifying coating thicknesses, adding thermal insulation, and pre-designing appropriate assembly clearances. However, existing passive clearance control methods have limited responsiveness to environmental changes, potentially impacting engine performance and reliability.

[0037] In response to the above problems, the engine clearance design method of the exemplary embodiment of the present invention draws on the idea of active clearance control and utilizes the principle of passive clearance control. By customizing the thermal expansion coefficient of the casing and utilizing the radial deformation of the casing, the rotational-static clearance requirements of the aircraft engine under various operating conditions can be met. It is especially suitable for the high-maneuverability aircraft engines under fast and changing operating conditions.

[0038] The method provided in the embodiments of the present invention can be executed by a terminal with a display function. The terminal can be a mobile phone, a tablet computer, a wearable device, an in-vehicle device, a laptop computer, an ultra-mobile personal computer (UMPC), a netbook, a PDA, or a wearable device based on augmented reality (AR) and / or virtual reality (VR) technology.

[0039] An engine clearance design method provided by an exemplary embodiment of the present invention is executed by a terminal or a chip applied in the terminal. The solution of the present invention is described below with reference to the accompanying drawings.

[0040] In the engine clearance design method provided by the exemplary embodiment of the present invention, the engine clearance is the radial clearance between the rotor blade tip and the casing. The rotor-to-stationary clearance hereinafter refers to the radial clearance between the rotor blade tip and the casing.

[0041] Figure 1 FIG. 1 shows a flow chart of an engine clearance design method according to an embodiment of the present invention. Figure 1 As shown, the engine clearance design method of the exemplary embodiment of the present invention includes:

[0042] Step 101: Obtain the clearance of the engine under various operating conditions and determine the target clearance of the engine under various operating conditions.

[0043] In some embodiments, under various working conditions, in order to obtain the gap between the tip of the rotor blade and the casing of a high-maneuverability aircraft engine, one or more testing methods can be used to obtain the above-mentioned gap based on the relative position relationship, structural characteristics and corresponding environmental requirements of the rotor blade and the casing of the aircraft engine, such as eddy current method, optical fiber method, discharge probe method, capacitance method, microwave method, finite element simulation method, etc. to obtain the rotor-static clearance.

[0044] For example, the above test method can also be used to obtain the radial deformation of the casing and the radial deformation of the rotor blade tip under various operating conditions of the aircraft engine, as well as the difference between the two, that is, the change in the rotor-static clearance.

[0045] Exemplarily, the operating conditions of an aircraft engine include typical stable state conditions, such as but not limited to ground bench test state, take-off state, envelope boundary state, typical state commonly used in the air, and cruise state.

[0046] The operating conditions described below are described using a typical stable state as an example. The aircraft engine of the exemplary embodiment of the present invention includes typical stable states such as ground slow speed, cruising, takeoff, high-altitude typical large state, and high-altitude right boundary point. The radial clearance design process of the third-stage rotor of a specific high-pressure compressor is used as an example for description.

[0047] The deformation, cold clearance, hot clearance, and clearance change (the difference between the cold clearance and the hot clearance) of the rotor blade tip and casing of a high-pressure compressor stage 3 under typical conditions were measured using the eddy current method. As shown in Table 1, the cold clearance refers to the rotor-static clearance of the engine at room temperature, and the hot clearance refers to the rotor-static clearance of the engine under corresponding operating conditions.

[0048] Table 1 Rotor-static clearance of compressor under various operating conditions

[0049]

[0050] When obtaining the clearance of the engine under various operating conditions and determining the target clearance of the engine under various operating conditions, the target clearance value under each operating condition can be different. For example, each operating condition requires a specific target clearance value, that is, it is set according to the needs of different engines, and the target clearance value changes with changes in the operating conditions.

[0051] In another optional embodiment, the target clearance value under each operating condition can be the same, that is, the same target clearance value is required under various operating conditions. In this embodiment, the required target clearance value of the aircraft engine does not change with the change of the operating conditions, but is a constant value, that is, the radial deformation of the rotor blade tip is consistent with the radial deformation of the casing.

[0052] Specifically, the minimum hot clearance value under each working condition is selected as the target clearance value. For example, the hot clearance under the high-altitude right boundary point working condition in Table 1 is 0.20 mm, which is the minimum value under each working condition. 0.20 mm is set as the target clearance value for subsequent engine clearance design.

[0053] Selecting a minimum hot clearance value can minimize the reduction in overall machine efficiency while preventing the rotor blade tips from colliding and rubbing against the inner wall of the casing, thereby preventing hazardous failures.

[0054] It should be noted that, from the perspective of aerodynamic efficiency, the thermal clearance value under an absolutely ideal state should be 0, but this absolute ideal state cannot be achieved in reality.

[0055] For example, the hot clearance under the above working conditions is The calculation of is shown in Equation 1.

[0056]

[0057] Among them, C cool It is the clearance of the engine in cold state; the superscript n is the typical state number; The radial deformation of the receiver is is the radial deformation of the rotor, in mm.

[0058] The target clearance value under each engine working condition is shown in formula 2:

[0059]

[0060] Step 102: determining a target deformation of the casing under corresponding working conditions based on at least one target gap, where the target deformation is a radial deformation of the casing;

[0061] When the target clearance is different under various working conditions, the target deformation of the casing can be determined according to the clearance value under various working conditions. That is, under various working conditions, the radial deformation of the casing can be obtained by formula three.

[0062] When the target gap is the same gap value, for example, the minimum hot gap value under each working condition, the target deformation of the casing under each working condition is That is, under various working conditions, the radial deformation of the casing can be obtained by equations 2 and 3.

[0063]

[0064] Therefore, the target deformation of the casing under various working conditions is shown in Table 2.

[0065] Step 103: Calculate the target thermal expansion coefficient of the casing under the corresponding working condition based on each target deformation amount.

[0066] Exemplarily, the target thermal expansion coefficient is positively correlated with the target deformation amount, and negatively correlated with the radius of the casing and the average temperature of the casing under corresponding working conditions.

[0067] When calculating the target thermal expansion coefficient of the casing under the corresponding working conditions, that is, at different temperatures, since the radial deformation of the casing is mainly determined by the thermal load, the target thermal expansion coefficient α can be calculated using formula 4 T,target .

[0068]

[0069] Where: T n is the average temperature of the casing under different engine operating conditions, in °C; the superscript n is the typical state number; r is the casing radius, in mm.

[0070] It should be noted that the target thermal expansion coefficient of the above-mentioned casing under different working conditions is the equivalent thermal expansion coefficient of the casing in Table 2, that is, the target thermal expansion coefficient of the entire casing to be achieved during casing design.

[0071] Table 2 Related parameters of the casing under various working conditions

[0072]

[0073] Step 104: Adjust the structure of the casing so that the casing meets the target thermal expansion coefficient under corresponding working conditions.

[0074] In some embodiments, an adjustment structure is added to the original structure of the casing so that the equivalent thermal expansion coefficient of the original structure and the adjustment structure is the target thermal expansion coefficient. This can minimize changes to the original casing structure, thereby reducing the complexity of engine design and minimizing interference with the original casing design.

[0075] Exemplarily, the adjustment structure is a cylindrical structure fitted on the original structure; or, when the outer side wall of the original structure has a flange, the adjustment structure includes at least one disc-shaped structure fitted on at least one side of the flange.

[0076] It should be noted that the above two adjustment structures can achieve the equivalent target thermal expansion coefficient of the above-mentioned casing as a whole. Any other casing combination structure that meets the above principles is also within the scope of protection of the present invention.

[0077] In the actual structural design, the combined structure is used to achieve the target thermal expansion coefficient α of the casing as a whole. T,target For example, the structure and dimensions of the adjustment structure are established by constructing a model, and then verified through finite element calculation to obtain the required casing combination structure design.

[0078] Figure 2 Schematic diagram of the structure of the casing according to an embodiment of the present invention. Figure 2 As shown, when the outer wall of the original structure 1 of the casing is a roughly smooth curved surface, by constructing a cylindrical adjustment structure to fit on the outer wall of the original structure 1, that is, by coating or installing the adjustment structure on the outer side of the original structure 1 of the casing, the thermal expansion coefficient of the casing combination structure formed by the original structure 1 and the adjustment structure is made equivalent to the target thermal expansion coefficient α to be achieved. T,target .

[0079] Figure 3 FIG. 1 is a schematic structural diagram of a casing according to another embodiment of the present invention. Figure 3 As shown, when the outer side wall of the original structure 1 has a flange 4 , the adjustment structure includes at least one disc-shaped structure attached to at least one side of the flange 4 .

[0080] In actual structural design, when the outer sidewall of the original structure 1 of the casing has a flange 4, a disc-shaped structure 3 or multiple disc-shaped structures 3 can be attached to one side of the flange 4, or a disc-shaped structure 3 or multiple disc-shaped structures 3 can be attached to both sides of the flange 4. For example, the shape of the disc-shaped structure 3 is substantially the same as that of the flange 4. Alternatively, the disc-shaped structure 3 can be wrapped around the entire outer surface of the flange 4. In this embodiment, the disc-shaped structure 3 has a cavity for accommodating the flange 4.

[0081] For example, the disc-shaped structure 3 and the flange 4 can be fixedly connected by bolts 5. For example, a circle of first through holes is provided along the circumference of the flange 4, and a circle of second through holes corresponding to the first through holes is also provided on the circumference of the disc-shaped structure 3. The disc-shaped structure 3 can be mounted on the flange 4 of the original structure 1 by passing a plurality of bolts 5 through the corresponding first through holes and second through holes, so that the disc-shaped structure 3 and the original structure 1 as a whole are equivalent to the target thermal expansion coefficient α. T,target.

[0082] In another optional embodiment, the disc-shaped structure 3 and the flange 4 may be connected by welding or bonding.

[0083] From formula 4, we can know that in order to obtain the target thermal expansion coefficient α, the combined structure of the casing adjustment structure and the original structure 1 is equivalent to T,target , it is necessary to first determine the target deformation S of the combined structure of the casing in the radial direction. combination,n , the overall target deformation of the combined structure can be obtained by Equation 5.

[0084]

[0085] in,

[0086] n is the typical state number;

[0087] S combination,n is the target deformation of the combined structure of the casing, mm;

[0088] S origin,n is the radial deformation of the original structure of the receiver, mm;

[0089] S adjustment,n is the radial deformation of the adjustment structure of the receiver, mm;

[0090] K origin,n is the radial stiffness of the original structure of the receiver, N / mm;

[0091] K adjustment,n is the radial stiffness of the adjustment structure of the receiver, N / mm;

[0092] f(a) is the fit tightness function, which is used to characterize the influence coefficient of tightness. It expresses the influence of the structural characteristics of the original structure and adjustment structure of the casing on their respective radial stiffness.

[0093] k origin,n or K adjustment,n =f(h,l,E), formula 6;

[0094] Among them, f(h,l,E) characterizes the influence of the structural characteristics and material properties of the original structure and adjustment structure of the receiver on the radial rigidity of the receiver.

[0095] The structural features of the original structure 1 and the adjustment structure of the above-mentioned casing include but are not limited to height, width, length, radius, thickness, etc., and the material properties include but are not limited to elastic modulus E, Poisson's ratio, etc.

[0096] For example, Figure 2As shown, the structural features of the casing assembly structure include: the length l of the original structure 1 A and the length l of the adjustment structure (cylindrical structure 2) A2 , the thickness h of the original structure 1 A , adjust the thickness of the structure h A2 ; It can also include the radius of the original structure 1 and the adjustment structure (cylindrical structure 2), etc.

[0097] For example, Figure 3 As shown, the structural features of the casing assembly structure include: the length l of the original structure 1 B , the thickness h of the original structure 1 B , the width of flange 4 is l B1 and height h B1 ; Adjust the width l of the structure (disc-shaped structure 3) B2 and height h B2 ; It can also include the radius of the original structure 1 and the adjustment structure (disc-shaped structure 3), etc.

[0098] As can be seen above, using Equations 5 and 6, we can estimate the basic dimensions of the casing's adjustment structure. Finite element analysis can then be used to determine the final overall casing structure (combined structure). This combined casing structure design is applicable not only to high-maneuverability aircraft engines but also to civilian aircraft engines.

[0099] An exemplary embodiment of the present invention further provides an engine designed using the engine clearance design method of the above embodiment. The engine may be a high-maneuverability aircraft engine, a civil aircraft engine, or a gas turbine.

[0100] The technical advantages of the above engine over the prior art are the same as the advantages of the above engine clearance design method, which will not be repeated here.

[0101] The above is an introduction to the solutions provided by the embodiments of the present invention. It is understandable that, in order to implement the above functions, it includes hardware structures and / or software modules corresponding to the execution of each function. Those skilled in the art should easily realize that, in combination with the units and algorithm steps of the various examples described in the embodiments disclosed herein, the present invention can be implemented in the form of hardware or a combination of hardware and computer software. Whether a function is executed in the form of hardware or computer software driving hardware depends on the specific application and design constraints of the technical solution. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of the present invention.

[0102] In embodiments of the present invention, the terminal can be divided into functional units according to the above-described method examples. For example, functional modules can be divided according to respective functions, or two or more functions can be integrated into a single processing module. The above-mentioned integrated modules can be implemented in the form of hardware or software functional modules. It should be noted that the module division in the embodiments of the present invention is illustrative and is merely a logical functional division. In actual implementation, other division methods may be used.

[0103] In the case of dividing each functional module according to each function, an exemplary embodiment of the present invention provides an engine clearance design device, where the clearance is a radial clearance between a rotor blade tip and a casing. Figure 4 FIG. 1 is a schematic block diagram of a module of a design device according to an embodiment of the present invention. Figure 4 As shown, the engine clearance design device 400 includes:

[0104] An acquisition module 401 is used to acquire the clearance of the engine under various operating conditions and determine the target clearance of the engine under various operating conditions;

[0105] A determination module 402 is configured to determine a target deformation of the casing under corresponding working conditions based on at least one target gap, where the target deformation is a radial deformation of the casing;

[0106] A calculation module 403 is used to calculate a target thermal expansion coefficient of the casing under corresponding working conditions based on each target deformation amount;

[0107] The processing module 404 is configured to adjust the structure of the casing so that the casing meets a target thermal expansion coefficient under corresponding working conditions.

[0108] As a possible implementation, the acquisition module 401 is used to acquire the clearance of the engine under various operating conditions and determine the target clearance of the engine under various operating conditions, including:

[0109] The target clearance value is different under different working conditions; or,

[0110] The target clearance value is consistent under various working conditions.

[0111] As a possible implementation manner, the acquisition module 401 is further configured to determine the target clearance as the minimum clearance of the engine under each operating condition when the target clearance values under each operating condition are consistent.

[0112] As a possible implementation, the calculation module 403 is configured to calculate the target thermal expansion coefficient of the casing under the corresponding working condition based on each target deformation, including:

[0113] The target thermal expansion coefficient is positively correlated with the target deformation, and negatively correlated with the radius of the casing and the average temperature of the casing under corresponding working conditions.

[0114] As a possible implementation, the processing module 404 is configured to adjust the structure of the casing so that the casing meets the target thermal expansion coefficient under the corresponding working condition, including:

[0115] An adjustment structure is added to the original structure 1 of the casing so that the equivalent thermal expansion coefficients of the original structure 1 and the adjustment structure are the target thermal expansion coefficients.

[0116] As a possible implementation, when the processing module 404 is used to adjust the structure of the casing, the adjustment structure is a cylindrical structure 2 that fits the original structure 1; or,

[0117] When the outer side wall of the original structure 1 has a flange 4 , the adjustment structure includes at least one disc-shaped structure 3 attached to at least one side of the flange 4 .

[0118] Figure 5 : shows a schematic block diagram of a chip according to an embodiment of the present invention. Figure 5 As shown, the chip 500 includes one or more (including two) processors 501 and a communication interface 502. The communication interface 502 can support the server to execute the data sending and receiving steps in the above method, and the processor 501 can support the server to execute the data processing steps in the above method.

[0119] Optional, such as Figure 5 As shown, the chip 500 also includes a memory 503, which may include a read-only memory and a random access memory, and provides operation instructions and data to the processor. Part of the memory may also include a non-volatile random access memory (NVRAM).

[0120] In some embodiments, as Figure 5 As shown, the processor 501 performs corresponding operations by calling the operation instructions stored in the memory (the operation instructions may be stored in the operating system). The processor 501 controls the processing operations of any one of the terminal devices, and the processor may also be called a central processing unit (CPU). The memory 503 may include a read-only memory and a random access memory, and provides instructions and data to the processor 501. A portion of the memory 503 may also include NVRAM. For example, in an application, the memory, the communication interface, and the memory are coupled together through a bus system, wherein the bus system may include a power bus, a control bus, and a status signal bus in addition to a data bus. However, for the sake of clarity, in Figure 5 Various buses are labeled as bus system 504 .

[0121] The methods disclosed in the embodiments of the present invention described above can be applied to or implemented by a processor. The processor may be an integrated circuit chip with signal processing capabilities. During implementation, each step of the method can be performed by hardware integrated logic circuits in the processor or by software instructions.

[0122] An exemplary embodiment of the present invention further provides an electronic device, comprising: at least one processor; and a memory communicatively connected to the at least one processor. The memory stores a computer program executable by the at least one processor, wherein the computer program, when executed by the at least one processor, causes the electronic device to perform a method according to an embodiment of the present invention.

[0123] Exemplary embodiments of the present invention further provide a non-transitory computer-readable storage medium storing a computer program, wherein the computer program, when executed by a processor of a computer, is used to cause the computer to perform a method according to an embodiment of the present invention.

[0124] refer to Figure 6 , a structural block diagram of an electronic device 600 that can serve as a server or client of the present invention will now be described, which is an example of a hardware device that can be applied to various aspects of the present invention.

[0125] like Figure 6 As shown, electronic device 600 includes a computing unit 601, which can perform various appropriate actions and processes according to a computer program stored in a read-only memory (ROM) 602 or a computer program loaded from a storage unit 608 into a random access memory (RAM) 603. Various programs and data required for the operation of device 600 can also be stored in RAM 603. Computing unit 601, ROM 602, and RAM 603 are connected to each other via a bus 604. An input / output (I / O) interface 605 is also connected to bus 604.

[0126] Multiple components within electronic device 600 are connected to I / O interface 605, including an input unit 606, an output unit 607, a storage unit 608, and a communication unit 609. Input unit 606 can be any type of device capable of inputting information into electronic device 600. Input unit 606 can receive input numeric or character information and generate key input signals related to user settings and / or function control of the electronic device. Output unit 607 can be any type of device capable of presenting information and may include, but is not limited to, a display, a speaker, a video / audio output terminal, a vibrator, and / or a printer. Storage unit 608 may include, but is not limited to, a magnetic disk or an optical disk. Communication unit 609 allows electronic device 600 to exchange information / data with other devices via computer networks such as the Internet and / or various telecommunication networks and may include, but is not limited to, a modem, a network card, an infrared communication device, a wireless communication transceiver and / or a chipset, such as a Bluetooth™ device, a WiFi device, a WiMax device, a cellular communication device, and / or the like.

[0127] like Figure 6 As shown, the computing unit 601 can be various general and / or special processing components with processing and computing capabilities. Some examples of the computing unit 601 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various dedicated artificial intelligence (AI) computing chips, various computing units that run machine learning model algorithms, digital signal processors (DSPs), and any appropriate processors, controllers, microcontrollers, etc. The computing unit 601 performs the various methods and processes described above. For example, in some embodiments, the method of the exemplary embodiments of the present invention can be implemented as a computer software program, which is tangibly included in a machine-readable medium, such as a storage unit 608. In some embodiments, part or all of the computer program can be loaded and / or installed on the electronic device 600 via the ROM 602 and / or the communication unit 609. In some embodiments, the computing unit 601 can be configured to execute the method in any other appropriate manner (e.g., by means of firmware).

[0128] In the context of the present invention, machine-readable medium can be a tangible medium that can contain or store a program for use with an instruction execution system, device or equipment or used in combination with an instruction execution system, device or equipment. Machine-readable medium can be a machine-readable signal medium or a machine-readable storage medium. Machine-readable medium can include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared or semiconductor systems, devices or equipment, or any suitable combination of the foregoing. More specific examples of machine-readable storage media can include electrical connections based on one or more lines, portable computer disks, hard disks, random access memories (RAM), read-only memories (ROM), erasable programmable read-only memories (EPROM or flash memory), optical fibers, portable compact disk read-only memories (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination of the foregoing.

[0129] It should be understood by those skilled in the art that the above embodiments are merely for the purpose of illustrating the present invention clearly, and are not intended to limit the scope of the present invention. For those skilled in the art, other changes or modifications may be made based on the above disclosure, and such changes or modifications are still within the scope of the present invention.

Claims

1. A method for designing engine clearance, characterized in that: The gap is a radial gap between the tip of the rotor blade and the casing, and the method includes: Obtaining the clearance of the engine under various operating conditions, and determining a target clearance of the engine under various operating conditions; Determining a target deformation of the casing under the corresponding working condition based on at least one target gap, wherein the target deformation is a radial deformation of the casing; Based on each of the target deformation amounts, the target thermal expansion coefficient of the casing under the corresponding working conditions is calculated; the target thermal expansion coefficient satisfy: ； Where: is the target deformation of the casing under various working conditions, is the average temperature of the casing under different engine operating conditions, in °C; the superscript n is the typical state number; r is the casing radius, in mm; Adjusting the structure of the casing so that the casing meets the target thermal expansion coefficient under the corresponding working condition includes: adding an adjustment structure to the original structure of the casing so that the equivalent thermal expansion coefficient of the original structure and the adjustment structure is the target thermal expansion coefficient; The adjustment structure is a cylindrical structure that fits in the original structure; or, When the outer side wall of the original structure has a flange, the adjustment structure includes at least one disc-shaped structure attached to at least one side of the flange.

2. The design method according to claim 1, characterized in that: When obtaining the clearance of the engine under various operating conditions and determining the target clearance of the engine under various operating conditions, the method includes: The target clearance value under each of the working conditions is different; or, The target gap values under each of the working conditions are consistent.

3. The design method according to claim 2, characterized in that: Obtaining the clearance of the engine under various operating conditions and determining the target clearance of the engine under various operating conditions includes: The gap is measured by using an eddy current method, an optical fiber method, a discharge probe method, a capacitance method, a microwave method or a finite element simulation method.

4. The design method according to claim 3, characterized in that: Calculating the target thermal expansion coefficient of the casing under the corresponding working condition based on each target deformation includes: The target thermal expansion coefficient is positively correlated with the target deformation amount, and negatively correlated with the radius of the casing and the average temperature of the casing under the corresponding working condition.

5. An engine, characterized in that: The invention is designed by the method according to any one of claims 1 to 4.

6. An engine clearance design device, characterized in that: Applied to the method according to any one of claims 1 to 4, the gap is a radial gap between the rotor blade tip and the casing, and the design device comprises: an acquisition module, configured to acquire the clearance of the engine under various operating conditions and determine a target clearance of the engine under various operating conditions; a determination module, configured to determine a target deformation of the casing under the corresponding working condition based on at least one target gap, wherein the target deformation is a radial deformation of the casing; a calculation module, configured to calculate a target thermal expansion coefficient of the casing under the corresponding working condition based on each target deformation; The processing module is used to adjust the structure of the casing so that the casing meets the target thermal expansion coefficient under the corresponding working condition.

7. An electronic device, characterized in that: include: processor; as well as Memory for storing programs; The program includes instructions, which, when executed by the processor, cause the processor to perform the method according to any one of claims 1 to 4.

8. A non-transitory computer-readable storage medium, characterized in that The non-transitory computer-readable storage medium stores computer instructions, and the computer instructions are used to enable the computer to execute the method according to any one of claims 1 to 4.

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