Design method of integrated CMC turbine outer ring for small and medium aero-engine

Abstract

The application relates to the technical field of engine design, and discloses a kind of overall CMC turbine outer ring design methods for small and medium-sized aero-engines, comprising: obtaining the real working condition data of small and medium-sized aero-engines, and determining the boundary conditions of overall CMC turbine outer ring design based on the real working condition data;Based on the boundary conditions and simulation test data, overall design is carried out to obtain the turbine outer ring design result;Based on the simulation model, the turbine outer ring design result is simulated and simulated by multi-physical field numerical simulation and high-temperature thermal adaptation test, and the design result is verified.The application identifies the real working condition of engine as the design boundary in advance, accurately calculates the equivalent diameter of outer ring, the assembly gap of heterogeneous parts, the thickness of protective coating and the safety compression range of sealing ring in sequence, relies on multi-physical field simulation to check stress extrusion defects in advance, supports high-temperature thermal adaptation test to quantitatively judge deformation uniformity, quantitatively calculates experience dependence, shortens the research and development cycle, and reduces the trial production cost.

Description

Technical Field

[0001] This invention relates to the field of engine design technology, and specifically to an integrated CMC turbine outer ring design method for small and medium-sized aero engines. Background Technology

[0002] Ceramic matrix composites (CMCs) are an important material for advanced aero-engines due to their advantages such as high temperature resistance and low coefficient of expansion. The configuration of CMC turbine outer rings varies depending on the application in different aero-engines. Large aero-engines, due to their larger diameter, typically employ a segmented design for their turbine outer rings. The design methodology usually involves determining the fiber layup, defining the manufacturing process, conducting design work, performing strength simulations, and carrying out relevant performance tests, forming a complete design process. Similar methods are used in the design and application of traditional metal outer rings.

[0003] In small and medium-sized aero engines, the turbine diameter is usually no more than 400mm. The integral configuration design has more advantages in tip clearance control. The connection structure of the integral turbine outer ring configuration is very different from that of the segmented outer ring. The installation method of the integral turbine outer ring is mostly based on the slot structure, and the cooling sealing structure basically adopts the full-circle sealing ring design. The fit between the integral outer ring configuration and the metal parts is prone to problems such as high temperature extrusion mismatch. For the above reasons, the segmented outer ring design method is difficult to solve the design problems of the integral CMC outer ring.

[0004] To meet the evolving needs of small and medium-sized aero-engines, turbine inlet temperatures are gradually rising, and the turbine outer ring, as a typical hot-end component, is subjected to extreme environmental conditions. To further improve engine performance, there are generally two options: first, to use an integral turbine outer ring to reduce tip gas leakage; second, to use a more heat-resistant material to fabricate the turbine outer ring. However, although various structural design schemes for integral ceramic matrix composite turbine outer rings exist, they all rely on experience for preliminary design and lack a design method for integral ceramic turbine outer rings tailored to the actual needs of engines. The feasibility of these schemes needs further verification, and the design boundaries of integral ceramic turbine outer rings are challenging, failing to fundamentally solve the mismatch problem in the heterogeneous connection structure between the outer ring and the metal. Summary of the Invention

[0005] This invention provides an integrated CMC turbine outer ring design method for small and medium-sized aero engines, in order to solve the problems of complex and inefficient CMC turbine outer ring design process for small and medium-sized aero engines.

[0006] In a first aspect, the present invention provides a method for designing an integral CMC turbine outer ring for small and medium-sized aero-engines, the method comprising: Obtain real operating condition data of small and medium-sized aero engines, and determine the boundary conditions for the integral CMC turbine outer ring design based on the real operating condition data; Based on boundary conditions and simulation test data, an integrated design was carried out to obtain the design results of the integrated CMC turbine outer ring. Based on the simulation model, multiphysics numerical simulation was performed on the design results of the integral CMC turbine outer ring, and the simulation results were analyzed to determine whether the simulation results meet the design requirements. If the simulation results meet the design requirements, a high-temperature thermal adaptation test will be conducted based on the corresponding integral CMC turbine outer ring design results, and the simulation model will be verified and evaluated based on the test results.

[0007] The present invention provides an integrated CMC turbine outer ring design method for small and medium-sized aero-engines. By identifying the actual operating conditions of the engine as the design boundary in advance, the method accurately calculates the equivalent diameter of the outer ring, the assembly clearance of heterogeneous parts, the thickness of the protective coating, and the safe compression range of the sealing ring. It relies on multi-physics simulation to identify stress extrusion defects in advance, and then uses high-temperature thermal adaptation tests to quantitatively evaluate the deformation uniformity. This method fills the gap in the design method of integrated ceramic outer rings for small and medium-sized aero-engines. The entire process uses quantitative calculations to reduce reliance on experience, solves the problem of thermal mismatch of heterogeneous structures from the source, reduces the need for later iterative tests, effectively shortens the R&D cycle, reduces the trial production cost, and improves the high-temperature reliability and service life of the turbine outer ring.

[0008] In one optional implementation, an integral design is performed based on boundary conditions and simulation test data to obtain the integral CMC turbine outer ring design result, including: High-temperature deformation simulation calculations were performed on the turbine rotor of small and medium-sized aero-engines to determine the equivalent diameter of the outer ring; Based on the equivalent diameter of the outer ring, the thermal expansion difference between the metal and ceramic is calculated to determine the assembly gap and assembly structure. The coating system thickness is determined based on the rotor speed and elongation of small and medium-sized aero engines; The compression of the turbine rotor is determined by axial elastic force calculation; Based on boundary conditions, outer ring equivalent diameter, assembly clearance and assembly structure, coating system thickness, and turbine rotor compression, an integral design was carried out to obtain the design result of the integral CMC turbine outer ring.

[0009] The integrated CMC turbine outer ring design method for small and medium-sized aero-engines provided by this invention accurately calculates the cold-processed dimensions of the outer ring, the metal-ceramic fitting clearance, and the protective coating thickness through a step-by-step design process. It limits the compression amplitude of the sealing ring through axial elastic force verification. All design parameters are derived based on the actual operating conditions of the engine, thus overcoming the drawbacks of relying solely on experience-based design. The entire design process is interconnected, with simultaneous constraints on dimensions, connections, protection, and stress. This proactively avoids potential hazards such as high-temperature extrusion, blade abrasion, and ceramic stress cracking, resulting in a more reliable design scheme. It also reduces the need for repeated iterative testing in the later stages, saving R&D time and prototyping costs. This provides a complete and feasible implementation path for the standardized design of integrated CMC turbine outer rings.

[0010] In one optional implementation, high-temperature deformation simulation calculations are performed on the turbine rotor of a small-to-medium-sized aero-engine to determine the equivalent diameter of the outer ring, including: The maximum deformation of the turbine rotor blade tip, the CMC linear expansion coefficient and the equivalent diameter of the working outer ring were obtained. Through high-temperature simulation calculations, the simulated deformation of the integral CMC turbine outer ring under different engine loads was obtained. The inner diameter of the ceramic outer ring after expansion is determined based on the simulated deformation, and the outer diameter of the rotor after expansion is determined based on the maximum deformation of the turbine rotor blade tip. The equivalent diameter of the outer ring is calculated in reverse by combining the safety clearance constraints of the inner and outer diameters.

[0011] The integrated CMC turbine outer ring design method for small and medium-sized aero-engines provided by this invention relies on real engine operating conditions to conduct synchronous high-temperature deformation simulation, and simultaneously acquires high-temperature deformation data of the rotor and CMC outer ring. Using the blade tip safety clearance specified by the whole engine as a hard constraint, the cold equivalent diameter of the outer ring is derived in reverse. This changes the traditional method of roughly setting the outer ring size based on experience, and realizes precise quantitative design of blade tip clearance. It accurately matches the expansion difference between the rotor and ceramic ring under high-temperature operating conditions, which avoids structural damage caused by blades scraping the ceramic outer ring during high-temperature operation, and also prevents gas leakage and reduced engine efficiency caused by excessive clearance. It ensures the turbine thermal performance and component operation reliability from the source of size design.

[0012] In one alternative implementation, the compression of the turbine rotor is determined by calculating the axial elastic force, including: Obtain the original height, elastic stiffness, bearing area of ​​the outer ring of the CMC turbine, and ultimate compressive stress of the CMC material; Based on the relationship between the compression of the sealing ring and the axial elastic force, the axial compressive stress borne by the outer ring of the CMC turbine under different compression amplitudes is calculated. The compression constraint threshold is determined based on the axial compressive stress, and the compression constraint threshold is compared with the ultimate compressive stress of CMC material. The smaller value of the two is taken as the compression amount of the turbine rotor.

[0013] The present invention provides a design method for an integral CMC turbine outer ring for small and medium-sized aero-engines. By quantitatively calculating the axial compressive stress caused by the compression of the sealing ring, and combining the compression limit of the sealing ring itself with the pressure bearing limit of the ceramic material, the assembly compression parameters are determined. On the one hand, this method can ensure that the sealing ring generates sufficient elastic force to effectively seal the cooling airflow and avoid cold air leakage from affecting the cooling effect. On the other hand, it can control the axial pressure borne by the CMC outer ring within the material's safe range, effectively preventing cracking and breakage of brittle ceramics due to stress concentration, thus balancing sealing performance and the integrity of the ceramic structure.

[0014] In one optional implementation, the simulation results are analyzed to determine whether they meet the design requirements, including: Based on the simulation results, the stress data and overall deformation distribution data of the CMC turbine outer ring body and metal connection structure were determined. Compare the stress data at various points of the CMC turbine outer ring body and metal connection structure with the maximum strength threshold. If the stress data at various points of the CMC turbine outer ring body and metal connection structure are all less than the maximum strength threshold, then check the uniformity of the overall deformation based on the overall deformation distribution data. If the overall deformation uniformity meets the preset uniformity requirements, then based on the overall deformation distribution data, it is determined whether there is high-temperature extrusion interference at various points between the CMC turbine outer ring and the metal connection structure. If there is no high-temperature extrusion interference, then the simulation results are determined to meet the design requirements.

[0015] The integrated CMC turbine outer ring design method for small and medium-sized aero-engines provided by this invention relies on stress and deformation data output from multiphysics simulation to carry out layered progressive verification. First, it verifies whether the stress in each part is lower than the material strength limit. Then, it checks the uniformity of outer ring deformation and whether there is high-temperature extrusion interference between ceramic and metal parts. This forms a complete and rigorous simulation judgment logic, which comprehensively identifies potential failure risks such as excessive stress, uneven deformation, and hot extrusion of heterogeneous structures in advance. Design defects are identified before trial production, reducing the number of physical iterations. At the same time, it ensures that the structural strength, deformation characteristics, and assembly adaptability of the CMC outer ring meet the high-temperature service requirements of small and medium-sized aero-engines.

[0016] In one optional implementation, the simulation model is validated and evaluated based on experimental results, including: A heating cycle test bench was built based on the design results of the integral CMC turbine outer ring. Multiple measuring points were set along the circumference of the CMC turbine outer ring, and radial deformation data of each measuring point were obtained. The uniformity of the test deformation of the CMC turbine outer ring is calculated based on the radial deformation data of each measuring point and the total number of measuring points, and the high-temperature deformation performance is evaluated based on the non-uniformity of the test deformation. The radial deformation data at each measuring point is compared with the overall deformation distribution data in the simulation results, and the accuracy of the simulation model is verified based on the comparison results.

[0017] The present invention provides a design method for an integral CMC turbine outer ring for small and medium-sized aero-engines. By simulating the real high-temperature service environment through a heated cycle test bench, radial deformation data is collected from multiple points along the outer ring circumference. The degree of deformation non-uniformity is quantitatively calculated to intuitively evaluate the quality of high-temperature deformation of the outer ring. At the same time, the measured deformation data is compared with the simulation results to verify the accuracy of the model. This method can not only quantitatively assess the real high-temperature deformation performance of the integral CMC turbine outer ring and accurately identify the failure risks caused by uneven circumferential deformation of the outer ring, but also correct and verify the previous multiphysics simulation model, improve the credibility of simulation calculations, and achieve two-way verification between simulation design and physical testing, thereby reducing design deviations.

[0018] Secondly, this invention provides an integrated CMC turbine outer ring design device for small and medium-sized aero-engines, the device comprising: The real-condition data acquisition module is used to acquire real-condition data of small and medium-sized aero engines and determine the boundary conditions of the integral CMC turbine outer ring design based on the real-condition data. The integrated design module is used to perform integrated design based on boundary conditions and simulation test data, and obtain the integrated CMC turbine outer ring design results; The simulation calculation module is used to perform multiphysics numerical simulation of the design results of the integral CMC turbine outer ring based on the simulation model, and to analyze the simulation results to determine whether the simulation results meet the design requirements. The test verification module is used to conduct high-temperature thermal adaptation tests based on the corresponding integral CMC turbine outer ring design results if the simulation results meet the design requirements, and to verify and evaluate the simulation model based on the test results.

[0019] Thirdly, the present invention provides an electronic device, comprising: a memory and a processor, the memory and the processor being communicatively connected to each other, the memory storing computer instructions, and the processor executing the computer instructions to perform the method described in the first aspect or any corresponding embodiment thereof.

[0020] Fourthly, the present invention provides a computer-readable storage medium storing computer instructions for causing a computer to perform the method described in the first aspect or any corresponding embodiment thereof.

[0021] Fifthly, the present invention provides a computer program product, including computer instructions for causing a computer to perform the method described in the first aspect or any corresponding embodiment thereof. Attached Figure Description

[0022] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of an application scenario according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the first process of the integrated CMC turbine outer ring design method for small and medium-sized aero-engines according to an embodiment of the present invention. Figure 3 This is a second flowchart illustrating the integrated CMC turbine outer ring design method for small and medium-sized aero-engines according to an embodiment of the present invention. Figure 4 This is a schematic diagram of the high-temperature deformation curve in the integrated CMC turbine outer ring design method for small and medium-sized aero-engines according to an embodiment of the present invention. Figure 5 This is a schematic diagram of the coordination of different configuration positioning structures in the integrated CMC turbine outer ring design method for small and medium-sized aero-engines according to an embodiment of the present invention. Figure 6 This is a schematic diagram of a heating cycle test bench in the integrated CMC turbine outer ring design method for small and medium-sized aero-engines according to an embodiment of the present invention; Figure 7 This is a complete flowchart of a specific embodiment of the integrated CMC turbine outer ring design method for small and medium-sized aero-engines according to an embodiment of the present invention. Figure 8 This is a structural block diagram of an integrated CMC turbine outer ring design device for small and medium-sized aero-engines according to an embodiment of the present invention; Figure 9 This is a schematic diagram of the hardware structure of an electronic device according to an embodiment of the present invention. Detailed Implementation

[0024] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0025] It is understood that before using the technical solutions disclosed in the various embodiments of the present invention, users should be informed of the types, scope of use, and usage scenarios of the personal information involved in the present invention and their authorization should be obtained in accordance with relevant laws and regulations through appropriate means.

[0026] In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0027] As an optional application scenario of this invention, such as Figure 1 As shown, the CMC turbine outer ring design system may include at least one terminal device and at least one server. Figure 1 The system is illustrated in the example, which includes a computer 101, a mobile terminal 102, and a server 103, and the terminal devices such as the computer 101 and the mobile terminal 102 are connected to the server 103 through a network 110.

[0028] Specifically, the terminal device can be a smartphone, tablet, laptop, PDA, desktop computer, game console, smart TV, smart wearable device, in-vehicle terminal, VR (Virtual Reality) device, AR (Augmented Reality) device, etc. Server 103 can be a standalone physical server, a server cluster, a distributed system, or a cloud server providing cloud services. Network 110 can be a wired or wireless network, examples of which include, but are not limited to, the Internet, corporate intranet, local area network, wide area network, mobile communication network, and combinations thereof.

[0029] This invention provides an integrated CMC turbine outer ring design method for small and medium-sized aero-engines. Through multi-stage parameter design and numerical simulation, it aims to improve the design efficiency of the CMC turbine outer ring for small and medium-sized aero-engines.

[0030] According to an embodiment of the present invention, an embodiment of an integral CMC turbine outer ring design method for small and medium-sized aero-engines is provided. It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. Furthermore, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be executed in a different order than that shown here.

[0031] This embodiment provides a method for designing an integral CMC turbine outer ring for small and medium-sized aero-engines, which can be used in the aforementioned computer system. Figure 2 This is a flowchart of an integrated CMC turbine outer ring design method for small and medium-sized aero-engines according to an embodiment of the present invention, such as... Figure 2 As shown, the process includes the following steps: Step S201: Obtain real operating condition data of small and medium-sized aero engines, and determine the boundary conditions of the integral CMC turbine outer ring design based on the real operating condition data.

[0032] Specifically, in the real engine service condition identification stage, core operating condition data of small and medium-sized aero engines during actual operation are obtained, including but not limited to: the highest speed that the turbine can reach when the engine is working, the highest temperature of the gas inside the turbine, and the working pressure of the gas; at the same time, the minimum safety clearance standard that must be maintained between the turbine blades and the outer ring as specified in the overall design is obtained, as well as the radial deformation curve of the rotor from cold state to high temperature and high speed operation, from which the maximum radial elongation of the rotor during operation is extracted.

[0033] In addition, basic material parameters can be collected simultaneously, including: the thermal expansion characteristics of CMC ceramic matrix composites, the maximum compressive stress that ceramic materials can withstand; the thermal expansion characteristics of metal casings, pins, and slot connectors; and assembly-related constraints such as the original dimensions and elastic characteristics of cooling sealing structures.

[0034] Based on all the collected basic data, the boundary conditions for the integral CMC turbine outer ring design are determined. Subsequent designs must not exceed these boundary conditions to ensure that the design conforms to the actual operating environment of the engine.

[0035] Step S202: Based on the boundary conditions and simulation test data, perform an overall design to obtain the overall CMC turbine outer ring design result.

[0036] Specifically, simulation tests were conducted on key design parameters of small and medium-sized aero-engines to obtain simulation test data, including but not limited to: high-temperature deformation data of turbine rotors, cold assembly clearance, coating thickness, etc. At the same time, the process and performance basic data obtained from the simulation tests of material and connection structure prototypes were referenced, and all design parameters were integrated with boundary conditions to carry out an overall design, resulting in the overall CMC turbine outer ring design. Step S203: Based on the simulation model, perform multiphysics numerical simulation on the design results of the integral CMC turbine outer ring, analyze the simulation results, and determine whether the simulation results meet the design requirements.

[0037] Specifically, before physical processing, multiphysics numerical simulation is performed. For the designed turbine outer ring and connecting structure, strength and deformation calculations are carried out under working temperature conditions using mature commercial software. The stress and deformation of the material at any point of the CMC outer ring and connecting structure are obtained. The stress value should meet the maximum strength requirement of the material, and the deformation value should meet the requirement of uniform deformation. If there is no extrusion between the CMC outer ring and the metal, the design is considered to have passed the numerical simulation analysis. The design that passes the numerical simulation analysis is selected.

[0038] If the stress value does not meet the maximum strength requirement of the material, the deformation value does not meet the deformation uniformity requirement, or there is extrusion between the outer ring of the CMC turbine and the metal, then the corresponding design has not passed the numerical simulation analysis and should be abandoned directly.

[0039] Step S204: If the simulation results meet the design requirements, a high-temperature thermal adaptation test is conducted based on the corresponding integral CMC turbine outer ring design results, and the simulation model is verified and evaluated based on the test results.

[0040] Specifically, while the design obtained through numerical simulation analysis theoretically meets the design requirements, problems may arise in actual operating conditions. Therefore, it is necessary to further verify the simulation results that meet the design requirements through real-world experiments. Based on the simulation results that meet the design requirements, an integral CMC turbine outer ring test piece is fabricated, a heating cycle test bench is built, and high-temperature thermal adaptation tests are conducted to simulate the engine's heating, holding, and cooling cycles. The test results are then used to re-evaluate whether the CMC turbine outer ring meets the actual operating requirements. Simultaneously, the test results are compared with the data in the simulation results to generate a complete test evaluation report and assess the accuracy of the simulation model.

[0041] The integrated CMC turbine outer ring design method for small and medium-sized aero-engines provided in this embodiment uses the actual operating conditions of the engine as the design boundary in advance. It then accurately calculates the equivalent diameter of the outer ring, the assembly gap of heterogeneous parts, the thickness of the protective coating, and the safe compression range of the sealing ring. It relies on multiphysics simulation to identify stress extrusion defects in advance, and then uses high-temperature thermal adaptation tests to quantitatively evaluate the deformation uniformity. This method fills the gap in the design method of integrated ceramic outer rings for small and medium-sized aero-engines. It uses quantitative calculations throughout the process to reduce reliance on experience, solves the problem of thermal mismatch of heterogeneous structures from the source, reduces the need for later iterative tests, effectively shortens the R&D cycle, reduces the trial production cost, and improves the high-temperature reliability and service life of the turbine outer ring.

[0042] This embodiment provides a method for designing an integral CMC turbine outer ring for small and medium-sized aero-engines, which can be used in the aforementioned computer system. Figure 3 This is a flowchart of an integrated CMC turbine outer ring design method for small and medium-sized aero-engines according to an embodiment of the present invention, such as... Figure 3 As shown, the process includes the following steps: Step S301: Obtain real-world operating data for small and medium-sized aero-engines, and determine the boundary conditions for the integral CMC turbine outer ring design based on this data. For details, please refer to [link to relevant documentation]. Figure 2 Step S201 of the illustrated embodiment will not be described again here.

[0043] Step S302: Based on the boundary conditions and simulation test data, perform an overall design to obtain the overall CMC turbine outer ring design result.

[0044] Specifically, step S302 includes: Step S3021: Perform high-temperature deformation simulation calculations on the turbine rotor of small and medium-sized aero-engines to determine the equivalent diameter of the outer ring.

[0045] Precisely determine the cold-state dimensions of the integral CMC turbine outer ring at the factory to ensure that the blade tips will not rub against the ceramic outer ring when the engine is operating at high temperatures, and at the same time, prevent gas leakage and reduced engine efficiency due to excessive clearance.

[0046] Specifically, step S3021 includes: Step a1: Obtain the maximum deformation of the turbine rotor blade tip, the CMC linear expansion coefficient under working conditions, and the equivalent diameter of the working outer ring. Through high-temperature simulation calculation, obtain the simulated deformation of the integral CMC turbine outer ring under different engine loads.

[0047] Specifically, deformation data of the metal outer ring, ceramic outer ring, and rotor blade tip as a function of temperature are obtained, and plots are generated based on the deformation data as shown below. Figure 4 The high-temperature deformation curve shown is used to determine the maximum deformation of the rotor blade tip based on the deformation curve of the rotor blade tip, as follows: Figure 4 As shown, the maximum deformation of the rotor blade tip is 1.5 mm, which is only an example and is not a limitation.

[0048] The rotor is made of metal. When heated to high temperature and rotated at high speed, it will extend outward in tandem. By combining the collected rotor deformation curves, the final size of the rotor after the overall outer diameter increases under extreme working conditions can be determined.

[0049] Ceramic materials only expand when heated to high temperatures, without elongation due to rotation. Based on the obtained ceramic expansion characteristics, outer ring design diameter, and maximum operating temperature, the extent of overall outward expansion of the ceramic ring during operation can be determined.

[0050] Step a2: Determine the inner diameter of the ceramic outer ring after expansion based on the simulated deformation, determine the outer diameter of the rotor after expansion based on the maximum deformation of the turbine rotor blade tip, and calculate the equivalent diameter of the outer ring in reverse by combining the safety clearance constraints of the inner and outer diameters.

[0051] Specifically, when the engine is operating at high temperatures, the inner diameter of the expanded ceramic outer ring, minus the outer diameter of the expanded rotor, must meet the minimum safety clearance required by the entire engine. Based on this matching logic, the diameter of the ceramic outer ring under normal temperature processing conditions is deduced. Deformation calculations of the integral CMC turbine outer ring under different engine loads at high temperatures are performed, and the deformation is compared with the rotor deformation. The equivalent diameter of the outer ring under the engine blade tip clearance requirement is calculated in reverse. The formula is: Equivalent outer ring diameter = Temperature × Linear expansion coefficient × Turbine rotor diameter + Blade tip clearance value + Rotor working diameter (the sum of the rotor's cold-state diameter and rotational elongation).

[0052] Once the dimensions are determined, a verification can be performed. By substituting the extreme temperature, the expansion of the rotor and ceramic ring can be simulated respectively, and the actual clearance between the blade and the outer ring at high temperature can be calculated to confirm that the clearance meets the requirements of the whole machine. If the clearance is too small after simulation and there is a risk of scratching, the cold-state dimensions of the outer ring can be readjusted and the calculation can be repeated until the clearance standard is met.

[0053] The integrated CMC turbine outer ring design method for small and medium-sized aero-engines provided in this embodiment relies on real engine operating conditions to conduct synchronous high-temperature deformation simulation, and simultaneously acquires high-temperature deformation data of the rotor and CMC outer ring. The cold equivalent diameter of the outer ring is derived in reverse with the blade tip safety clearance specified by the whole engine as a hard constraint. This changes the traditional method of roughly setting the outer ring size based on experience, and realizes precise quantitative design of blade tip clearance. It accurately matches the expansion difference between the rotor and ceramic ring under high-temperature operating conditions, which avoids structural damage caused by blades scraping the ceramic outer ring during high-temperature operation, and also avoids gas leakage and reduced engine efficiency caused by excessive clearance. It ensures the turbine thermal performance and component operation reliability from the source of size design.

[0054] Step S3022: Based on the equivalent diameter of the outer ring, calculate the thermal expansion difference between the metal and the ceramic to determine the assembly gap and assembly structure.

[0055] Specifically, the integral CMC turbine outer ring is mainly assembled with a metal casing using two structures: pin fixing and slot boss matching. The thermal expansion range of ceramic and metal materials is very different. When operating at high temperature, the metal expands more, and the originally reserved assembly gap will shrink, which can easily squeeze the brittle ceramic and cause cracking. To address this issue, the connection structure selection and gap matching design were completed.

[0056] First, based on the overall engine installation space and disassembly / maintenance requirements, determine whether to use a pin-type or slot-type positioning structure, and determine the basic dimensions of the mating parts. Second, compare the thermal expansion differences between the metal and ceramic parts, calculate the difference in expansion after temperature increases, and determine how much the assembly clearance will shrink at high temperatures. Using a standard clearance selection table corresponding to different operating temperatures, determine the minimum safe clearance that must be maintained during high-temperature operation of the engine to avoid interference compression at high temperatures. Then, based on the required safe clearance at high temperatures, determine the initial clearance that needs to be reserved at the pin and slot positions during room-temperature assembly. If the cold-state clearance is too small, the clearance will disappear after heating, compressing the ceramic; if the clearance is too large, it will cause circumferential wobbling of the outer ring and insufficient positioning accuracy. The final selected cold-state assembly clearance must ensure that a safe clearance always exists between the metal and ceramic mating parts under all operating conditions, from room-temperature assembly to the highest operating temperature, preventing compression damage.

[0057] The special configuration of the integral CMC turbine outer ring generally employs either a pin-fixed type or a slotted fit type. Both of these structures involve clearance fit between the metal parts and the ceramic slots. For example... Figure 5 The diagram shows the positioning structure fit. Table 1 shows the fit clearance selection under different temperature conditions. High temperature conditions can cause compression and damage to the metal-ceramic connection structure. If the fit clearance in the table is selected according to the actual engine operating conditions, the thermal expansion coordination of the connection structure under high temperature conditions can be achieved.

[0058] Table 1 Selection of fit clearance under different temperature conditions

[0059] Step S3023: Determine the coating system thickness based on the rotor speed and elongation of the small and medium-sized aero-engine.

[0060] Specifically, a dual-layer coating system is applied to the inner side of the ceramic outer ring. The bottom layer is an environmental barrier coating (EBC) to insulate the ceramic substrate from high-temperature combustion gases. The top layer is a wear-resistant coating; if the blade experiences slight radial misalignment, only the coating will wear down, without damaging the blade or the ceramic body. This dual-layer coating system plays a crucial role in mitigating the risk of high-speed scraping between the turbine blade tip and the outer ring, providing buffering scraping force, heat insulation, and preventing combustion gas corrosion.

[0061] There is a strict upper limit to the total coating thickness; the combined thickness of the two coating layers cannot exceed 1.6 mm. The specific coating thickness is determined based on two core operating conditions of the engine: first, the maximum operating speed of the rotor. The higher the speed, the greater the relative speed of the blades scraping against the outer ring, requiring a thicker wear-resistant layer to improve wear resistance and buffering capacity; second, the maximum radial elongation of the rotor during high-temperature operation. The greater the rotor deformation, the greater the radial displacement range of the blades, requiring more allowance for wear resistance.

[0062] Based on the collected rotational speed and rotor deformation data, and referring to the coating system thickness selection table shown in Table 2, the total coating thickness suitable for this engine was determined. After matching, two checks were performed: First, check whether the total thickness does not exceed the upper limit of 1.6 mm. If the recommended thickness exceeds the limit, adjust the thickness distribution ratio of the heat insulation layer and the wear-resistant layer; Second, confirm that the thickness of the wearable surface layer is greater than the maximum radial offset of the blade to ensure that only the coating is worn under extreme operating conditions, and the ceramic substrate is not damaged.

[0063] Table 2 Coating System Thickness Selection Table

[0064] Step S3024: Determine the compression of the turbine rotor by calculating the axial elastic force.

[0065] Specifically, step S3024 above includes: Step b1: Obtain the original height of the sealing ring, elastic stiffness, bearing area of ​​the outer ring of the CMC turbine, and ultimate compressive stress of the CMC material.

[0066] Specifically, the outer ring is protected from cooling gas leakage by a C-type or W-type elastic sealing ring. The sealing ring is compressed during assembly, which in turn generates a continuous axial thrust on the outer ring. CMC ceramic is brittle and cannot withstand excessive axial pressure, which can easily lead to stress concentration and localized fracture. Therefore, it is necessary to calculate the turbine rotor compression through axial elastic force to prevent stress concentration from damaging the CMC turbine outer ring body.

[0067] The original height in free state, its own elastic stiffness, the area of ​​the load-bearing region of the ceramic outer ring, and the maximum compressive stress that the ceramic material can withstand; at the same time, in accordance with the rigid design requirements, the overall compression of the sealing ring cannot exceed 5% of its original height.

[0068] Step b2: Based on the correspondence between the compression of the sealing ring and the axial elastic force, calculate the axial compressive stress borne by the outer ring of the CMC turbine under different compression amplitudes.

[0069] Specifically, based on the preset compression amount of the sealing ring, the total axial pressure exerted by the sealing ring on the outer ring after assembly is calculated, and then the compressive stress borne by the ceramic body is calculated in combination with the force-bearing area of ​​the outer ring.

[0070] Step b3: Determine the compression constraint threshold based on the axial compressive stress, and compare the compression constraint threshold with the ultimate compressive stress of the CMC material, taking the smaller value as the compression amount of the turbine rotor.

[0071] Specifically, on the one hand, the compression limit of 5% cannot be exceeded, and on the other hand, the compressive stress borne by the ceramic cannot exceed the material's allowable limit. The maximum allowable compression range under both constraints is calculated, and the smaller value is taken as the final design compression.

[0072] If the maximum compression range calculated based solely on ceramic strength is less than 5%, the compression amount of the sealing ring is reduced based on the material strength. If the allowable compression range of the material exceeds 5%, then 5% is directly used as the upper limit of compression. This method controls the axial pressure within a safe range, preventing the ceramic outer ring from being crushed by the elastic sealing ring.

[0073] The integrated CMC turbine outer ring design method for small and medium-sized aero-engines provided in this embodiment determines the assembly compression parameters by quantitatively calculating the axial compressive stress caused by the compression of the sealing ring and combining the compression limit of the sealing ring itself with the pressure bearing limit of the ceramic material. On the one hand, it can ensure that the sealing ring generates sufficient elastic force to effectively seal the cooling airflow and avoid cold air leakage from affecting the cooling effect; on the other hand, it can control the axial pressure borne by the CMC outer ring within the material's safe range, effectively preventing brittle ceramics from cracking and breaking due to stress concentration, thus balancing sealing performance and ceramic structural integrity.

[0074] Step S3025: Based on boundary conditions, equivalent diameter of outer ring, assembly clearance and assembly structure, coating system thickness and turbine rotor compression, an integral design is performed to obtain the integral CMC turbine outer ring design result.

[0075] Specifically, all key parameters determined in each step are integrated, including engine operating condition boundary constraints, outer ring equivalent reference diameter, assembly structure form and cold assembly clearance, composite coating layer thickness, and sealing ring assembly compression. The integrated structural design is completed by coordinating the four dimensions of structural dimensions, connection assembly, protective coating, and sealing stress. The overall CMC turbine outer ring design result file, which includes geometric dimensions, assembly scheme, coating process, and assembly preload parameters, is output for subsequent multiphysics simulation verification and test piece processing.

[0076] The integrated CMC turbine outer ring design method for small and medium-sized aero-engines provided in this embodiment accurately calculates the cold-processed dimensions of the outer ring, the metal-ceramic fitting clearance, and the protective coating thickness through a step-by-step design process. The compression range of the sealing ring is limited by axial elastic force verification. All design parameters are derived based on the actual operating conditions of the engine, thus overcoming the drawbacks of relying solely on experience-based design. The entire design process is interconnected, with simultaneous constraints on dimensions, connections, protection, and stress. This proactively avoids potential hazards such as high-temperature extrusion, blade abrasion, and ceramic stress cracking, resulting in a more reliable design scheme. It also reduces the need for repeated iterative testing in the later stages, saving R&D time and prototyping costs. This provides a complete and feasible implementation path for the standardized design of integrated CMC turbine outer rings.

[0077] Step S303: Based on the simulation model, perform multiphysics numerical simulation on the design results of the integral CMC turbine outer ring, analyze the simulation results, and determine whether the simulation results meet the design requirements.

[0078] Specifically, step S303 includes: Step S3031: Based on the simulation results, determine the stress data and overall deformation distribution data of each part of the CMC turbine outer ring body and the metal connection structure.

[0079] Specifically, after completing the multiphysics coupled numerical simulation calculation of the integral CMC turbine outer ring, the full-domain calculation results are extracted from the simulation software, covering all areas of the CMC turbine outer ring matrix, metal connection structures such as pins / boobs, and all key locations such as the ceramic-metal mating contact surface. The equivalent stress, compressive stress, and tensile stress values ​​at each location are obtained, and the location and peak stress of stress concentration areas are fully recorded. Overall deformation distribution data: the deformation displacement values ​​of each location in the circumferential and radial directions of the entire ring under high-temperature conditions are extracted to obtain the radial deformation distribution law of the entire outer ring. The areas with large local deformation and skewed deformation are recorded to form a complete outer ring deformation cloud map and corresponding measurement point deformation values.

[0080] Step S3032: Compare the stress data of each part of the CMC turbine outer ring body and the metal connection structure with the maximum strength threshold. If the stress data of each part of the CMC turbine outer ring body and the metal connection structure are all less than the maximum strength threshold, then check the uniformity of the overall deformation based on the overall deformation distribution data.

[0081] Specifically, the ultimate bearing strength of the CMC ceramic matrix and the maximum allowable strength of the metal connector material are set respectively. The stress at various points on the ceramic outer ring is compared with the ceramic strength threshold, and the stress in the metal connector structure is compared with the metal strength threshold. If the stress at any point exceeds the maximum strength threshold of the corresponding material, the simulation result is directly determined to be unsatisfactory, and the structural parameters need to be adjusted and redesigned and simulated. If the stress at all points on the ceramic outer ring and the metal connector is lower than their respective strength thresholds, it means that the structural strength meets the safety standards, and the next level of verification is entered. Based on the extracted full-ring deformation distribution data, the deformation difference at various points on the circumference of the outer ring is checked to determine whether the overall deformation is uniform.

[0082] Step S3033: If the overall deformation uniformity meets the preset uniformity requirements, then determine whether there is high-temperature extrusion interference at various points between the CMC turbine outer ring and the metal connection structure based on the overall deformation distribution data. If there is no high-temperature extrusion interference, then determine that the simulation results meet the design requirements.

[0083] Specifically, an allowable standard for the circumferential deformation difference of the outer ring is set in advance. The radial deformation values ​​at each measuring point of the outer ring are compared. If the circumferential deformation difference is controlled within the preset range, it indicates that the deformation uniformity is qualified, and the heterogeneous assembly interference check is performed. If the deformation difference is too large, the outer ring will show local gap shift and local stress concentration, and the simulation is deemed unqualified. Combining the deformation of the ceramic outer ring and the metal connector under high temperature load, the gap change of the mating contact surface of the two is checked to determine whether an interference contact state occurs after the temperature rise due to metal expansion compressing the ceramic matrix.

[0084] If the deformation uniformity meets the standard and there is no high-temperature extrusion interference at all mating positions between ceramic and metal, and all three-layer checks pass, the simulation results are deemed to meet the design requirements and can proceed to the subsequent high-temperature thermal adaptation test. If the deformation uniformity does not meet the standard, or there is high-temperature extrusion interference between metal and ceramic, the simulation is deemed unqualified, and the simulation iteration is repeated after optimizing the structural dimensions and assembly gap parameters.

[0085] The integrated CMC turbine outer ring design method for small and medium-sized aero-engines provided in this embodiment relies on stress and deformation data output from multiphysics simulation to conduct layered and progressive verification. First, it verifies whether the stress in each part is lower than the material strength limit. Then, it checks the uniformity of outer ring deformation and whether there is high-temperature extrusion interference between ceramic and metal parts. This forms a complete and rigorous simulation judgment logic, which comprehensively identifies potential failure risks such as excessive stress, uneven deformation, and hot extrusion of heterogeneous structures in advance. Design defects are identified before trial production, reducing the number of physical iterations. At the same time, it ensures that the structural strength, deformation characteristics, and assembly adaptability of the CMC outer ring meet the high-temperature service requirements of small and medium-sized aero-engines.

[0086] Step S304: If the simulation results meet the design requirements, a high-temperature thermal adaptation test is conducted based on the corresponding integral CMC turbine outer ring design results, and the simulation model is verified and evaluated based on the test results.

[0087] Specifically, step S304 above includes: Step S3041: Based on the design results of the integral CMC turbine outer ring, a heating cycle test bench is built, multiple measuring points are set along the circumference of the CMC turbine outer ring, and radial deformation data of each measuring point is obtained.

[0088] Specifically, for the integral CMC turbine outer ring design analyzed through numerical simulation, high-temperature thermal compatibility testing and evaluation of the integral ceramic matrix composite turbine outer ring are required. Based on the previously output complete integral CMC turbine outer ring design drawings, dimensional parameters, and assembly process, a physical test piece is fabricated, and a system is built according to the engine's actual high-temperature service conditions. Figure 6 The heating cycle test bench shown simulates the temperature load of the engine through repeated cycles of heating, high-temperature holding, and cooling, thus reproducing the actual working temperature environment of the turbine outer ring.

[0089] After assembling the CMC turbine outer ring test piece, several displacement measuring points are evenly arranged around the entire circumference of the outer ring, covering all key circumferential positions of the outer ring, and equipped with displacement acquisition sensor equipment. The heating cycle test is started, and multiple cold and hot cycles are completed according to the preset temperature curve. The radial deformation values ​​of each measuring point at different temperature stages are collected synchronously throughout the process, and the original measured deformation data of each position in the entire circumference are completely recorded, providing the measured basic data for subsequent deformation performance evaluation and simulation benchmarking.

[0090] Step S3042: Calculate the test deformation uniformity of the CMC turbine outer ring based on the radial deformation data of each measuring point and the total number of measuring points, and evaluate the high-temperature deformation performance based on the test deformation non-uniformity.

[0091] Specifically, the uniformity of the experimental deformation of the CMC turbine outer ring is calculated based on the radial deformation values ​​of all circumferential measuring points and the total number of measuring points. A high-temperature deformation control variable evaluation method considering characteristic point boundary conditions is constructed to meet the needs of real engines. The deformation non-uniformity H is defined as the criterion. A larger value indicates a more non-uniform tendency in the outer ring deformation, resulting in poorer deformation uniformity at high temperatures and a higher risk of sudden changes in local blade tip clearance, local stress concentration, and localized ceramic cracking during operation. Conversely, a smaller value indicates better circumferential deformation consistency and more stable high-temperature service performance. The calculation formula is as follows:

[0092] Where x is the radial deformation value at the measuring point, n is the number of circumferential measuring points, and i is the number of measuring points.

[0093] The experimental calculation results can determine the deformation performance of the integral CMC turbine outer ring, providing data support for its design. By calculating the deformation non-uniformity value and comparing it against preset acceptance criteria, a comprehensive evaluation of the outer ring's high-temperature deformation performance is completed. This allows for a direct assessment of the deformation performance of the current integral CMC turbine outer ring structure under high-temperature cycling conditions, and identifies design defects.

[0094] Step S3043: Compare the radial deformation data of each measuring point with the overall deformation distribution data in the simulation results, and verify the accuracy of the simulation model based on the comparison results.

[0095] Specifically, the simulated radial deformation calculation values ​​at the locations corresponding one-to-one with the test measurement points are extracted in the simulation. The measured deformation data and the simulated deformation data at the same measurement point are compared item by item, and the deviation and relative error between the two sets of data are calculated.

[0096] If the errors of deformation data at each measuring point are all within the pre-set allowable error range, it indicates that the load, material parameters, and boundary conditions of the multiphysics simulation model built in the early stage are consistent with the real working conditions, and the calculation accuracy of the simulation model is reliable. In the future, the model can be used to carry out rapid design iteration of the same type of outer ring. If the deformation data at multiple measurement points deviates beyond the allowable range, it indicates that there are parameter deviations in the simulation model. It is necessary to combine experimental measured data to correct the boundary conditions such as the expansion coefficient of the simulation material, assembly constraints, and temperature loads, and recalibrate the simulation model to improve the realism and accuracy of the simulation calculation.

[0097] The integrated CMC turbine outer ring design method for small and medium-sized aero-engines provided in this embodiment uses a heated cycle test bench to simulate the real high-temperature service environment. By collecting radial deformation data from multiple points along the outer ring's circumference, the degree of deformation non-uniformity is quantitatively calculated to intuitively evaluate the quality of the outer ring's high-temperature deformation. At the same time, the measured deformation data is compared with the simulation results to verify the model's accuracy. This method can not only quantitatively assess the real high-temperature deformation performance of the integrated CMC turbine outer ring and accurately identify potential failures caused by uneven circumferential deformation of the outer ring, but also correct and verify the previous multiphysics simulation model, improve the credibility of simulation calculations, and achieve two-way verification between simulation design and physical testing, thereby reducing design deviations.

[0098] In one specific embodiment, such as Figure 7 The diagram shown is a complete flowchart illustrating the integrated CMC turbine outer ring design method for small and medium-sized aero-engines provided in this embodiment. A 1200kW-class small and medium-sized turboprop aero-engine is equipped with an integrated CMC ceramic matrix composite turbine outer ring, designed as follows... Figure 7 The complete process shown completes the entire design and experimental verification.

[0099] (1) Collect all boundary input parameters of the whole machine and lock the design constraints: Extreme operating conditions: maximum turbine speed nmax=32000r / min, maximum gas temperature Td=1180℃, gas static pressure P=0.85MPa; Clearance constraint: Minimum safe tip clearance for high-temperature steady-state operation =0.3mm; Rotor deformation: Cold rotor outer diameter =360mm, total radial elongation of rotor rotation and high temperature under extreme operating conditions. =0.62mm; Basic material parameters: CMC ceramic expansion coefficient Metal casing / pin expansion coefficient CMC allows for ultimate compressive stress. =120MPa; C-type sealing ring free height H=4mm, elastic stiffness k=1200N / mm.

[0100] (2) Substitute the operating parameters to calculate the equivalent diameter of the outer ring in the cold state: Combine the rotor's high-temperature outer diameter, CMC high-temperature expansion, and 0.3mm safety clearance constraint to calculate the equivalent diameter of the outer ring in the cold state. 360.96mm; Simulation of the radial deformation of the rotor and ceramic ring across the entire temperature range yielded the expansion difference curve of the two throughout the heating process from 0 to 1180℃, providing a basis for subsequent assembly clearance design; High-temperature working clearance verification: At extreme temperatures, the difference between the inner diameter of the outer ring expansion and the outer diameter of the rotor is 0.34mm, which is greater than the required minimum clearance of 0.3mm, eliminating the risk of blade scratching, and the dimensional parameters are qualified.

[0101] (3) The internal installation space of the engine is compact and the frequency of disassembly and maintenance is low. A pin-type positioning assembly structure is selected. The thermal expansion difference between the metal pin and the CMC mating part is calculated: the metal expansion is much greater than that of ceramic at 1180℃, and the high temperature gap is reduced by 0.18mm. The minimum high temperature safety gap of 0.05mm under 1180℃ working condition is matched by referring to the table, and the cold assembly reserved gap of 0.23mm is determined in reverse. This gap can ensure that the ceramic and metal do not have excessive compression in the whole temperature range, and avoid ceramic cracking.

[0102] (4) Given that the rotor's maximum speed is 32000 r / min and its maximum elongation is 0.62 mm, the total thickness of the composite coating is matched to 1.2 mm (below the rigid upper limit of 1.6 mm) according to the coating selection table. Layering: EBC thermal insulation base layer 0.4 mm, abrasion-resistant surface layer 0.8 mm. The thickness of the abrasion-resistant surface layer is greater than the rotor's maximum radial offset. Under extreme working conditions, only the coating will wear, without damaging the CMC substrate and metal blades.

[0103] (5) Basic parameters: Free height of sealing ring 4mm, stiffness 1200N / mm, axial bearing area of ​​outer ring A=1850mm2, CMC ultimate compressive stress 120MPa; maximum allowable compressive displacement calculated from material strength: =1.85mm, corresponding to a theoretical compression ratio of 46.25%; with an additional 5% compression limit constraint, 5% corresponds to a maximum compression displacement of 0.2mm. Taking the smaller value, the assembly compression displacement is determined to be 0.2mm, with a compression ratio of 5%.

[0104] After assembly, the axial pressure F = 240 N, and the outer ring compressive stress σ = 0.13 MPa. With a pressure rating of 120MPa, it meets the safety requirements for ceramic pressure bearing, while the sealing ring has sufficient elasticity to seal off cooling airflow leakage.

[0105] (6) Integrate the above-mentioned outer ring equivalent diameter, pin assembly gap, 1.2mm composite coating, and 5% sealing ring compression to complete the three-dimensional structural design; build a temperature-stress-deformation multiphysics simulation model and load it under the extreme working condition of 1180℃: the maximum stress in the whole domain is 86MPa, which is lower than the CMC and the strength threshold of metal materials; the circumferential deformation difference of the outer ring is only 0.07mm, and the deformation uniformity meets the standard; there is no high-temperature extrusion interference between the ceramic and the pin mating surface; the simulation is qualified and enters the test stage.

[0106] (7) Fabricate the CMC outer ring test piece according to the design dimensions, build a heating cycle test bench, and evenly arrange 8 radial displacement measuring points along the circumference of the outer ring. Conduct 50 cycles of 100℃~1180℃ cold and hot cycle tests, and collect the radial deformation measured data of the 8 measuring points throughout the process.

[0107] The calculated deformation nonuniformity index H=0.06, far below the unqualified threshold of 0.2, indicating excellent high-temperature deformation performance of the outer ring. Comparing the measured deformation at eight measuring points with the corresponding simulated data, the maximum relative error was 3.7%, within the ±5% allowable error range, demonstrating reliable simulation model accuracy. The integrated CMC turbine outer ring design provided in this embodiment meets all performance requirements for high-temperature service in small and medium-sized aero-engines, and the design process can be implemented for overall engine assembly.

[0108] This embodiment also provides an integrated CMC turbine outer ring design device for small and medium-sized aero-engines. This device is used to implement the above embodiments and preferred embodiments, and details already described will not be repeated. As used below, the term "module" can be a combination of software and / or hardware that implements a predetermined function. Although the device described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0109] This embodiment provides an integrated CMC turbine outer ring design device for small and medium-sized aero engines, such as... Figure 8 As shown, it includes: The real operating condition data acquisition module 801 is used to acquire real operating condition data of small and medium-sized aero engines and determine the boundary conditions of the integral CMC turbine outer ring design based on the real operating condition data.

[0110] The integrated design module 802 is used to perform integrated design based on boundary conditions and simulation test data, and obtain the integrated CMC turbine outer ring design results.

[0111] The simulation calculation module 803 is used to perform multiphysics numerical simulation on the design results of the integral CMC turbine outer ring based on the simulation model, and to analyze the simulation results to determine whether the simulation results meet the design requirements.

[0112] The test verification module 804 is used to conduct high-temperature thermal adaptation tests based on the corresponding integral CMC turbine outer ring design results if the simulation results meet the design requirements, and to verify and evaluate the simulation model based on the test results.

[0113] In some alternative implementations, the monolithic design module 802 includes: The high-temperature deformation calculation unit is used to perform high-temperature deformation simulation calculations on the turbine rotor of small and medium-sized aero-engines and determine the equivalent diameter of the outer ring.

[0114] The assembly parameter determination unit is used to calculate the thermal expansion difference between metal and ceramic based on the equivalent diameter of the outer ring, and to determine the assembly gap and assembly structure.

[0115] The coating thickness determination unit is used to determine the coating system thickness based on the rotor speed and elongation of small and medium-sized aero engines.

[0116] The compression calculation unit is used to determine the compression of the turbine rotor by calculating the axial elastic force.

[0117] The overall design unit is used to perform an overall design based on boundary conditions, equivalent diameter of the outer ring, assembly clearance and assembly structure, coating system thickness, and turbine rotor compression, resulting in an overall CMC turbine outer ring design.

[0118] In some alternative implementations, the simulation calculation module 803 includes: The data extraction unit is used to determine the stress data and overall deformation distribution data of various parts of the CMC turbine outer ring body and metal connection structure based on the simulation results.

[0119] The first verification unit is used to compare the stress data of the CMC turbine outer ring body and the metal connection structure with the maximum strength threshold. If the stress data of the CMC turbine outer ring body and the metal connection structure are all less than the maximum strength threshold, the uniformity of the overall deformation is verified based on the overall deformation distribution data.

[0120] The second verification unit is used to determine whether there is high-temperature extrusion interference at various points of the CMC turbine outer ring and the metal connection structure if the overall deformation uniformity meets the preset uniformity requirements. If there is no high-temperature extrusion interference, the simulation results are determined to meet the design requirements.

[0121] In some alternative implementations, the test verification module 804 includes: The test bench construction unit is used to build a heating cycle test bench based on the design results of the integral CMC turbine outer ring, set multiple measuring points along the circumference of the CMC turbine outer ring, and obtain radial deformation data of each measuring point.

[0122] The test performance evaluation unit is used to calculate the test deformation uniformity of the CMC turbine outer ring based on the radial deformation data of each measuring point and the total number of measuring points, and to evaluate the high-temperature deformation performance based on the test deformation non-uniformity.

[0123] The model verification unit is used to compare the radial deformation data of each measuring point with the overall deformation distribution data in the simulation results, and to verify the accuracy of the simulation model based on the comparison results.

[0124] The integrated CMC turbine outer ring design device for small and medium-sized aero-engines provided in this embodiment of the invention can execute the integrated CMC turbine outer ring design method for small and medium-sized aero-engines provided in any embodiment of the invention, and has the corresponding functional modules and beneficial effects of the method. Further functional descriptions of the various modules and units are the same as in the corresponding embodiments described above, and will not be repeated here.

[0125] Figure 9 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention.

[0126] The following is a detailed reference. Figure 9 This diagram illustrates a structural schematic suitable for implementing an electronic device according to embodiments of the present invention. The electronic device may include a processor (e.g., a central processing unit, graphics processor, etc.) 901, which can perform various appropriate actions and processes according to a program stored in read-only memory (ROM) 902 or a program loaded from memory 908 into random access memory (RAM) 903. The RAM 903 also stores various programs and data required for the operation of the electronic device. The processor 901, ROM 902, and RAM 903 are interconnected via a bus 904. An input / output (I / O) interface 905 is also connected to the bus 904.

[0127] Typically, the following devices can be connected to I / O interface 905: input devices 906 including, for example, touchscreens, touchpads, keyboards, mice, cameras, microphones, accelerometers, gyroscopes, etc.; output devices 907 including, for example, liquid crystal displays (LCDs), speakers, vibrators, etc.; memory devices 908 including, for example, magnetic tapes, hard disks, etc.; and communication devices 909. Communication device 909 allows electronic devices to exchange data via wireless or wired communication with other devices. Although Figure 9 Electronic devices with various devices are shown, but it should be understood that it is not required to implement or have all of the devices shown, and more or fewer devices may be implemented or have instead.

[0128] In particular, according to embodiments of the present invention, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, embodiments of the present invention include a computer program product comprising a computer program carried on a non-transitory computer-readable medium, the computer program containing program code for performing the methods shown in the flowcharts. In such embodiments, the computer program can be downloaded and installed from a network via a communication device 909, or installed from a memory 908, or installed from a ROM 902. When the computer program is executed by a processor 901, it performs the functions defined in the integrated CMC turbine outer ring design method for small and medium-sized aero-engines according to embodiments of the present invention.

[0129] Figure 9 The electronic device shown is merely an example and should not be construed as limiting the functionality and scope of use of the embodiments of the present invention.

[0130] This invention also provides a computer-readable storage medium. The methods described above according to embodiments of the invention can be implemented in hardware or firmware, or implemented as computer code that can be recorded on a storage medium, or implemented as computer code downloaded via a network and originally stored on a remote storage medium or a non-transitory machine-readable storage medium and then stored on a local storage medium. Thus, the methods described herein can be processed by software stored on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. The storage medium can be a magnetic disk, optical disk, read-only memory, random access memory, flash memory, hard disk, or solid-state drive, etc.; further, the storage medium can also include combinations of the above types of memory. It is understood that computers, processors, microprocessor controllers, or programmable hardware include storage components capable of storing or receiving software or computer code. When the software or computer code is accessed and executed by the computer, processor, or hardware, the integrated CMC turbine outer ring design method for small and medium-sized aero-engines shown in the above embodiments is implemented.

[0131] A portion of this invention can be applied as a computer program product, such as computer program instructions, which, when executed by a computer, can invoke or provide the methods and / or technical solutions according to the invention through the operation of the computer. Those skilled in the art will understand that the forms in which computer program instructions exist in a computer-readable medium include, but are not limited to, source files, executable files, installation package files, etc. Correspondingly, the ways in which computer program instructions are executed by a computer include, but are not limited to: the computer directly executing the instructions, or the computer compiling the instructions and then executing the corresponding compiled program, or the computer reading and executing the instructions, or the computer reading and installing the instructions and then executing the corresponding installed program. Here, the computer-readable medium can be any available computer-readable storage medium or communication medium accessible to a computer.

[0132] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A method for designing an integral CMC turbine outer ring for small and medium-sized aero-engines, characterized in that, The method includes: Obtain real operating condition data of small and medium-sized aero engines, and determine the boundary conditions for the integral CMC turbine outer ring design based on the real operating condition data; Based on the boundary conditions and simulation test data, an integrated design was carried out to obtain the integrated CMC turbine outer ring design results; Based on the simulation model, multiphysics numerical simulation was performed on the design results of the integral CMC turbine outer ring, and the simulation results were analyzed to determine whether the simulation results met the design requirements. If the simulation results meet the design requirements, a high-temperature thermal adaptation test is conducted based on the corresponding integral CMC turbine outer ring design results, and the simulation model is verified and evaluated based on the test results.

2. The method according to claim 1, characterized in that, Based on the aforementioned boundary conditions and simulation test data, an integrated design is performed to obtain the integrated CMC turbine outer ring design results, including: High-temperature deformation simulation calculations were performed on the turbine rotor of the aforementioned small and medium-sized aero-engines to determine the equivalent diameter of the outer ring; Based on the equivalent diameter of the outer ring, the thermal expansion difference between the metal and ceramic is calculated to determine the assembly gap and assembly structure. The coating system thickness is determined based on the rotor speed and elongation of small and medium-sized aero engines; The compression of the turbine rotor is determined by axial elastic force calculation; Based on the aforementioned boundary conditions, outer ring equivalent diameter, assembly clearance and assembly structure, coating system thickness, and turbine rotor compression, an integral design is performed to obtain the integral CMC turbine outer ring design result.

3. The method according to claim 2, characterized in that, High-temperature deformation simulation calculations were performed on the turbine rotor of the aforementioned small and medium-sized aero-engine to determine the equivalent diameter of the outer ring, including: The maximum deformation of the turbine rotor blade tip, the CMC linear expansion coefficient and the equivalent diameter of the working outer ring were obtained. Through high-temperature simulation calculations, the simulated deformation of the integral CMC turbine outer ring under different engine loads was obtained. The inner diameter of the ceramic outer ring after expansion is determined based on the simulated deformation amount, and the outer diameter of the rotor after expansion is determined based on the maximum deformation of the turbine rotor blade tip. The equivalent diameter of the outer ring is calculated in reverse by combining the safety clearance constraints between the inner and outer diameters.

4. The method according to claim 1, characterized in that, The compression of the turbine rotor is determined by axial elastic force calculation, including: Obtain the original height, elastic stiffness, bearing area of ​​the outer ring of the CMC turbine, and ultimate compressive stress of the CMC material; Based on the relationship between the compression of the sealing ring and the axial elastic force, the axial compressive stress borne by the outer ring of the CMC turbine under different compression amplitudes is calculated. The compression constraint threshold is determined based on the axial compressive stress, and the compression constraint threshold is compared with the ultimate compressive stress of the CMC material. The smaller of the two values ​​is taken as the compression amount of the turbine rotor.

5. The method according to claim 1, characterized in that, Analyze the simulation results to determine whether they meet the design requirements, including: Based on the simulation results, the stress data and overall deformation distribution data of the CMC turbine outer ring body and metal connection structure are determined. The stress data of each part of the CMC turbine outer ring body and the metal connection structure are compared with the maximum strength threshold. If the stress data of each part of the CMC turbine outer ring body and the metal connection structure are all less than the maximum strength threshold, the uniformity of the overall deformation is checked according to the overall deformation distribution data. If the overall deformation uniformity meets the preset uniformity requirement, then based on the overall deformation distribution data, it is determined whether there is high-temperature extrusion interference at various points between the CMC turbine outer ring and the metal connection structure. If there is no high-temperature extrusion interference, then it is determined that the simulation results meet the design requirements.

6. The method according to claim 5, characterized in that, The simulation model is verified and evaluated based on the experimental results, including: A heating cycle test bench was built based on the design results of the integral CMC turbine outer ring. Multiple measuring points were set along the circumference of the CMC turbine outer ring, and radial deformation data of each measuring point were obtained. The uniformity of the test deformation of the CMC turbine outer ring is calculated based on the radial deformation data of each measuring point and the total number of measuring points, and the high-temperature deformation performance is evaluated based on the non-uniformity of the test deformation. The radial deformation data at each measuring point is compared with the overall deformation distribution data in the simulation results, and the accuracy of the simulation model is verified based on the comparison results.

7. An integrated CMC turbine outer ring design device for small and medium-sized aero-engines, characterized in that, The device includes: The real operating condition data acquisition module is used to acquire real operating condition data of small and medium-sized aero engines and determine the boundary conditions of the integral CMC turbine outer ring design based on the real operating condition data. An integrated design module is used to perform an integrated design based on the boundary conditions and simulation test data, and obtain the integrated CMC turbine outer ring design result; The simulation calculation module is used to perform multiphysics numerical simulation on the design results of the integral CMC turbine outer ring based on the simulation model, and to analyze the simulation results to determine whether the simulation results meet the design requirements. The test verification module is used to conduct high-temperature thermal adaptation tests based on the corresponding integral CMC turbine outer ring design results if the simulation results meet the design requirements, and to verify and evaluate the simulation model based on the test results.

8. An electronic device, characterized in that, include: A memory and a processor, the memory and the processor being communicatively connected to each other, the memory storing computer instructions, the processor executing the computer instructions to perform the method of any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer instructions for causing a computer to perform the method of any one of claims 1 to 6.

10. A computer program product, characterized in that, Includes computer instructions for causing a computer to perform the method of any one of claims 1 to 6.

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