A method and system for reducing dimensionality of circumferentially non-uniform performance parameters of an aeroengine rim seal

Abstract

The application relates to the technical field of aero-engines and discloses a circumferential non-uniform performance parameter dimension reduction characterization method and system for aero-engine rim sealing, which utilizes dimensionless pressure coefficients at multiple circumferential positions of an upstream and downstream sealing cavity of a rim sealing structure, constructs a curve of the upstream and downstream pressure coefficients changing with a circumferential angle, extracts upstream and downstream circumferential average pressures, high-pressure and low-pressure area average pressures, substitutes the four groups of high-pressure and low-pressure combinations into one-dimensional design calculation, obtains two groups of gas invasion temperatures and two groups of cold gas outflow temperatures, and calculates overall temperature characterization values of gas invasion and cold gas outflow of the sealing cavity according to a circumferential angle proportion of the downstream high-pressure and low-pressure areas. The method makes up for the deficiency of traditional one-dimensional design which does not sufficiently consider the influence of three-dimensional circumferential non-uniform pressure, can quantize the degrees of gas invasion and cold gas outflow under the one-dimensional framework, significantly improves the one-dimensional design calculation accuracy of a secondary air system of an aero-engine high-pressure turbine, and provides important support for the design and development of the secondary air system.

Description

Technical Field

[0001] This invention relates to the field of aero-engine technology, and discloses a method and system for dimensionality reduction characterization of circumferential non-uniform performance parameters of aero-engine rim seals. Background Technology

[0002] To improve the performance of aero engines, turbine inlet air temperatures have been continuously increased, rising from 1200K to over 2000K. However, this increase in inlet air temperature leads to greater thermal loads on hot-end components, increasing the likelihood of thermal fatigue and high-temperature creep causing fractures and deformations, thus affecting operational safety. Therefore, advanced secondary air cooling systems are needed to prevent overheating of rotating components such as the turbine disk and blades, and to reduce thermal stress.

[0003] The cooling airflow drawn from the compressor will enter the turbine hot end components for cooling protection after passing through the complex secondary air system transmission channel. The cold airflow in the secondary air cooling system will pass through the pre-swirl intake system, the rotor-rotor disk cavity, the rotor-stationary disk cavity, the rim seal, etc., and then enter the main channel and the internal cooling channel of the moving blade, providing cold air protection for the rotor disk, the stationary / moving blade end wall and the moving blade respectively.

[0004] The flow structure at the rim sealing gap is highly complex due to factors such as mainstream circumferential pressure, pumping effect, and the three-dimensional unsteady flow structure of the rim. The intrusion mechanism of the combustion gas at the rim sealing gap can be summarized as rotation-induced intrusion and externally induced intrusion, with externally induced intrusion having the most significant impact on the sealing efficiency of the rim seal. Externally induced intrusion is caused by the unsteady circumferential pressure distribution above the disc cavity rim sealing gap, originating from the interference between the high-pressure region of the stationary blade wake and the stagnation region of the moving blade leading edge. This unsteady interference effect further intensifies the intrusion of the mainstream combustion gas.

[0005] In the one-dimensional design of the secondary air system of aero-engine high-pressure turbines, the average pressure upstream and downstream of the rim seal is typically used to approximate the intensity of gas intrusion and temperature distribution at the seal gap. However, due to the lack of sufficient consideration of the non-uniformity of the mainstream circumferential pressure distribution, this method is difficult to accurately assess the actual degree of gas intrusion and local temperature in the rim seal area, thus failing to guarantee the actual cooling and sealing effect of the designed sealing structure. Summary of the Invention

[0006] The purpose of this invention is to provide a method and system for dimensionality reduction characterization of circumferential non-uniform performance parameters of aero-engine rim seals. This method can fully consider the influence of three-dimensional circumferential non-uniform pressure and quantify the degree of gas intrusion and cold gas outflow of the rim seal within a one-dimensional design calculation framework, thereby achieving high-precision dimensionality reduction characterization of the circumferential non-uniform performance parameters of aero-engine rim seals.

[0007] To achieve the above-mentioned technical effects, the technical solution adopted by the present invention is as follows:

[0008] A method for dimensionality reduction characterization of circumferential non-uniform performance parameters of aero-engine rim seals includes: Based on the local static pressure at multiple circumferential positions upstream and downstream of the sealing cavity at the wheel rim sealing structure of the aero-engine, as well as the total pressure at the inlet of the stator blade upstream and the static pressure at the inlet of the moving blade downstream of the sealing cavity, the dimensionless pressure coefficient at the corresponding circumferential position upstream and downstream of the sealing cavity are calculated respectively. Based on the dimensionless pressure coefficients at the corresponding circumferential positions upstream and downstream of the sealing cavity, a first curve representing the change of the dimensionless pressure coefficient with the relative circumferential angle in the upstream pressure distribution of the sealing cavity, and a second curve representing the change of the dimensionless pressure coefficient with the relative circumferential angle in the downstream pressure distribution are constructed. The local static pressure corresponding to the average value of the dimensionless pressure coefficient within one blade cycle on the first curve is determined as the first circumferential average pressure upstream of the sealing cavity. The first upstream pressure average value of the local static pressure at all circumferential positions above the first circumferential average pressure within the corresponding blade cycle, and the second upstream pressure average value of the local static pressure at all circumferential positions below the first circumferential average pressure are calculated. The local static pressure corresponding to the average value of the dimensionless pressure coefficient within one blade cycle on the second curve is determined as the second circumferential average pressure downstream of the sealing cavity. The first downstream average pressure of the local static pressure at all circumferential positions above the second circumferential average pressure and the second downstream average pressure of the local static pressure at all circumferential positions below the second circumferential average pressure are calculated within the corresponding blade cycle. Using the combined conditions of the first upstream pressure average and the first downstream pressure average as input, the first gas intrusion temperature under the corresponding combined conditions is obtained through one-dimensional design calculation; using the combined conditions of the first upstream pressure average and the second downstream pressure average as input, the second gas intrusion temperature under the corresponding combined conditions is obtained through one-dimensional design calculation. Based on the proportion of the circumferential angle of all circumferential positions above the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, the proportion of the circumferential angle of all circumferential positions below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, as well as the first gas intrusion temperature and the second gas intrusion temperature, the temperature characterization value of the gas intrusion area of ​​the sealing cavity is obtained by analysis. Using the combined conditions of the second upstream pressure average and the first downstream pressure average as input, the first cold air outlet temperature under the corresponding combined conditions is obtained through one-dimensional design calculation; using the combined conditions of the second upstream pressure average and the second downstream pressure average as input, the second cold air outlet temperature under the corresponding combined conditions is obtained through one-dimensional design calculation. Based on the proportion of the circumferential angle of all circumferential positions above the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, the proportion of the circumferential angle of all circumferential positions below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, and the first cold air outlet temperature and the second cold air outlet temperature, the temperature characterization value of the cold air outlet region of the sealing cavity is obtained by analysis.

[0009] Furthermore, the dimensionless pressure coefficient at the corresponding circumferential position upstream of the sealing cavity ,in To seal the local static pressure at the corresponding circumferential position upstream of the cavity, The static pressure at the inlet of the moving blade at the corresponding circumferential position downstream of the sealing cavity. The total pressure at the stator inlet at the corresponding circumferential position upstream of the sealing cavity; Dimensionless pressure coefficient at the circumferential position downstream of the sealing cavity , To seal the local static pressure at the corresponding circumferential position downstream of the cavity, The static pressure at the inlet of the moving blade at the corresponding circumferential position downstream of the sealing cavity. The total pressure at the inlet of the stationary vane at the corresponding circumferential position upstream of the sealing cavity.

[0010] Furthermore, the method for constructing a first curve characterizing the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity as a function of the relative circumferential angle, and a second curve characterizing the dimensionless pressure coefficient of the downstream pressure distribution as a function of the relative circumferential angle, includes: Fourier curve fitting was performed on the dimensionless pressure coefficients at the upstream and downstream circumferential positions of the sealing cavity to obtain the curves representing the change of the dimensionless pressure coefficients with the circumferential angle, which characterize the corresponding pressure distribution.

[0011] Furthermore, the circumferential angle percentage of all circumferential positions above the average dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve is used as the weighting coefficient of the first gas intrusion temperature, and the circumferential angle percentage of all circumferential positions below the average dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve is used as the weighting coefficient of the second gas intrusion temperature. The weighted summation is then performed to obtain the temperature characterization value of the gas intrusion area of ​​the sealing cavity. The weighting coefficients of the first cold air outlet temperature are obtained by weighting the proportion of the circumferential angles of all circumferential positions above the average value of the dimensionless pressure coefficients of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, and the weighting coefficients of the second cold air outlet temperature are obtained by weighting and summing the weighted values.

[0012] To achieve the above-mentioned technical effects, the present invention also provides a dimensionality reduction characterization system for the circumferential non-uniform performance parameters of aero-engine rim seals, used to implement the aforementioned method for dimensionality reduction characterization of the circumferential non-uniform performance parameters of aero-engine rim seals, comprising: The data acquisition module is used to calculate the dimensionless pressure coefficients at the corresponding circumferential positions upstream and downstream of the sealing cavity based on the local static pressure at multiple circumferential positions upstream and downstream of the sealing cavity at the sealing cavity of the aero-engine wheel rim sealing structure, as well as the total pressure at the upstream stator inlet and the static pressure at the downstream moving blade inlet of the sealing cavity. The pressure distribution curve construction module is used to construct a first curve characterizing the change of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity with the relative circumferential angle, and a second curve characterizing the change of the dimensionless pressure coefficient of the downstream pressure distribution with the relative circumferential angle, based on the dimensionless pressure coefficient at the corresponding circumferential position upstream of the sealing cavity and the dimensionless pressure coefficient at the corresponding circumferential position downstream of the sealing cavity. The first curve analysis module is used to determine the local static pressure corresponding to the average value of the dimensionless pressure coefficient within one blade cycle on the first curve as the first circumferential average pressure upstream of the sealing cavity, and to calculate the first upstream pressure average value of the local static pressure at all circumferential positions higher than the first circumferential average pressure within the corresponding blade cycle, and the second upstream pressure average value of the local static pressure at all circumferential positions lower than the first circumferential average pressure. The second curve analysis module is used to determine the local static pressure corresponding to the average value of the dimensionless pressure coefficient within one blade cycle on the second curve as the second circumferential average pressure downstream of the sealing cavity, and to calculate the first downstream average pressure of the local static pressure at all circumferential positions that are higher than the second circumferential average pressure within the corresponding blade cycle, and the second downstream average pressure of the local static pressure at all circumferential positions that are lower than the second circumferential average pressure. The gas intrusion temperature analysis module is used to obtain the first gas intrusion temperature under the corresponding combination conditions by taking the first upstream pressure average value and the first downstream pressure average value as input and through one-dimensional design calculation; and to obtain the second gas intrusion temperature under the corresponding combination conditions by taking the first upstream pressure average value and the second downstream pressure average value as input and through one-dimensional design calculation. The intrusion area temperature characterization module is used to analyze and obtain the temperature characterization value of the gas intrusion area of ​​the sealing cavity by considering the following parameters: the percentage of circumferential angles of all circumferential positions above the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve; the percentage of circumferential angles of all circumferential positions below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve; the first gas intrusion temperature; and the second gas intrusion temperature. The cold air outlet temperature analysis module is used to obtain the first cold air outlet temperature under the corresponding combination conditions by taking the combination of the second upstream pressure average value and the first downstream pressure average value as input and through one-dimensional design calculation; and to obtain the second cold air outlet temperature under the corresponding combination conditions by taking the combination of the second upstream pressure average value and the second downstream pressure average value as input and through one-dimensional design calculation. The outflow region temperature characterization module is used to analyze and obtain the temperature characterization value of the cold air outflow region of the sealing cavity based on the proportion of the circumferential angle of all circumferential positions above the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, the proportion of the circumferential angle of all circumferential positions below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, as well as the first cold air outflow temperature and the second cold air outflow temperature.

[0013] Furthermore, in the data acquisition module, the dimensionless pressure coefficient at the corresponding circumferential position upstream of the sealing cavity... ,in To seal the local static pressure at the corresponding circumferential position upstream of the cavity, The static pressure at the inlet of the moving blade at the corresponding circumferential position downstream of the sealing cavity. The total pressure at the stator inlet at the corresponding circumferential position upstream of the sealing cavity; Dimensionless pressure coefficient at the circumferential position downstream of the sealing cavity , To seal the local static pressure at the corresponding circumferential position downstream of the cavity, The static pressure at the inlet of the moving blade at the corresponding circumferential position downstream of the sealing cavity. The total pressure at the inlet of the stationary vane at the corresponding circumferential position upstream of the sealing cavity.

[0014] Furthermore, the pressure distribution curve construction module is used to perform Fourier curve fitting on the dimensionless pressure coefficient at the corresponding circumferential position upstream of the sealing cavity and the corresponding circumferential position downstream, respectively, to obtain the curve of the dimensionless pressure coefficient as a function of the circumferential angle, which characterizes the corresponding pressure distribution.

[0015] Furthermore, in the intrusion area temperature characterization module, the proportion of the circumferential angle of all circumferential positions above the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve within the corresponding blade cycle is used as the weighting coefficient of the first gas intrusion temperature, and the proportion of the circumferential angle of all circumferential positions below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve within the corresponding blade cycle is used as the weighting coefficient of the second gas intrusion temperature. The weighted sum is then used to obtain the gas intrusion area temperature characterization value of the sealing cavity. In the outflow region temperature characterization module, the circumferential angle ratio of all circumferential positions above the average dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve is used as the weighting coefficient of the first cold air outflow temperature, and the circumferential angle ratio of all circumferential positions below the average dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve is used as the weighting coefficient of the second cold air outflow temperature. The weighted summation is then performed to obtain the temperature characterization value of the cold air outflow region of the sealing cavity.

[0016] Compared with the prior art, the beneficial effects of this invention are: 1. This invention introduces a dimensionless pressure coefficient to establish a correlation between the circumferential non-uniform pressure distribution of the wheel rim seal and the pressure at the upstream inlet and outlet. Based on the fact that the distribution law of the dimensionless pressure coefficient is basically consistent under different operating conditions, it can ensure that the corresponding upstream and downstream non-uniform pressure distribution of the wheel rim seal can be quickly determined even under different operating conditions of the aero-engine. By expressing the dimensionless pressure coefficient of the circumferential distribution with a high-precision curve and effectively integrating it into the dimension reduction characterization model of the circumferential non-uniform pressure of the wheel rim seal, the average pressure of the upstream and downstream non-uniform pressure distribution can be accurately and quickly extracted.

[0017] 2. The dimensionality reduction method of the circumferential non-uniform pressure of the wheel rim seal of the present invention is based on the circumferential distribution law and corresponding pressure characteristics of the gas intrusion and cold air outflow regions in the sealing cavity. It realizes the partition calculation of the gas intrusion and cold air outflow regions in the front and rear disk cavities of the turbine, and effectively integrates it into the one-dimensional design calculation of the secondary air system of the aero-engine, which significantly improves the calculation accuracy of the one-dimensional design.

[0018] 3. This invention fully considers the periodic changes in pressure at the upstream and downstream positions of the sealing cavity due to the rotation of the moving blades. Therefore, in the overall temperature characterization of the gas intrusion and cold gas outflow regions of the rim seal, the temperature of multiple gas intrusion and cold gas outflow regions calculated based on the circumferential non-uniform pressure dimensionality reduction integration method of the rim seal is introduced to calculate and evaluate the overall temperature characterization value of the gas intrusion and cold gas outflow regions. This method can accurately calculate the average temperature of the gas intrusion and cold gas outflow regions under the condition of fully considering the mainstream non-uniform circumferential pressure distribution, thereby effectively evaluating the actual sealing and cooling effect of the rim seal structure. Attached Figure Description

[0019] Figure 1 The flowchart shows the method for dimensionality reduction characterization of circumferential non-uniform performance parameters of aero-engine rim seals in this embodiment. Figure 2 This is a block diagram of the dimensionality reduction characterization system for the circumferential non-uniform performance parameters of the aero-engine rim seal in the embodiment. Figure 3 This is a schematic diagram of the sealing cavity structure of the rim seal in the embodiment; Figure 4 This is a schematic diagram of the first curve in the embodiment; Figure 5 This is a schematic diagram showing the relative circumferential angle percentage of the first downstream pressure average value and the second downstream pressure average value on the second curve within one blade cycle in the embodiment. The module includes: 1. Pressure distribution curve construction module; 2. First curve analysis module; 3. Second curve analysis module; 4. Gas intrusion temperature analysis module; 5. Intrusion area temperature characterization module; 6. Cold air outflow temperature analysis module; 7. Outflow area temperature characterization module; 8. Sealing cavity; 9. Data acquisition module. Detailed Implementation

[0020] The present invention will now be described in further detail with reference to the embodiments and accompanying drawings. However, this should not be construed as limiting the scope of the above-described subject matter of the present invention to the following embodiments; all technologies implemented based on the content of the present invention fall within the scope of the present invention.

[0021] Example 1 See Figures 1 to 3 A method for dimensionality reduction characterization of circumferential non-uniform performance parameters of aero-engine rim seals, comprising: Based on the local static pressure at multiple circumferential positions upstream of the sealing cavity 8 at the wheel rim sealing structure of the aero-engine, the local static pressure at multiple circumferential positions downstream of the sealing cavity 8, the total pressure at the inlet of the stator blade upstream of the sealing cavity 8 and the static pressure at the inlet of the moving blade downstream of the sealing cavity 8, the dimensionless pressure coefficient at the corresponding circumferential position upstream of the sealing cavity 8 and the dimensionless pressure coefficient at the corresponding circumferential position downstream of the sealing cavity 8 are calculated respectively. Based on the dimensionless pressure coefficient at the corresponding circumferential position upstream of the sealing cavity 8 and the dimensionless pressure coefficient at the corresponding circumferential position downstream of the sealing cavity 8, a first curve characterizing the change of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 with the relative circumferential angle, and a second curve characterizing the change of the dimensionless pressure coefficient of the downstream pressure distribution with the relative circumferential angle are constructed. The local static pressure corresponding to the average value of the dimensionless pressure coefficient within one blade cycle on the first curve is determined as the first circumferential average pressure upstream of the sealing cavity 8. The first upstream pressure average value of the local static pressure at all circumferential positions above the first circumferential average pressure within the corresponding blade cycle, and the second upstream pressure average value of the local static pressure at all circumferential positions below the first circumferential average pressure are calculated. The local static pressure corresponding to the dimensionless pressure coefficient average value within one blade cycle on the second curve is the second circumferential average pressure downstream of the sealing cavity 8. The first downstream average pressure of the local static pressure at all circumferential positions higher than the second circumferential average pressure within the corresponding blade cycle, and the second downstream average pressure of the local static pressure at all circumferential positions lower than the second circumferential average pressure are calculated. Using the combined conditions of the first upstream pressure average and the first downstream pressure average as input, the first gas intrusion temperature under the corresponding combined conditions is obtained through one-dimensional design calculation; using the combined conditions of the first upstream pressure average and the second downstream pressure average as input, the second gas intrusion temperature under the corresponding combined conditions is obtained through one-dimensional design calculation. Based on the proportion of the circumferential angle of all circumferential positions above the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 within one blade cycle on the second curve, the proportion of the circumferential angle of all circumferential positions below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 within one blade cycle on the second curve, as well as the first gas intrusion temperature and the second gas intrusion temperature, the temperature characterization value of the gas intrusion area of ​​the sealing cavity 8 is obtained by analysis. Using the combined conditions of the second upstream pressure average and the first downstream pressure average as input, the first cold air outlet temperature under the corresponding combined conditions is obtained through one-dimensional design calculation; using the combined conditions of the second upstream pressure average and the second downstream pressure average as input, the second cold air outlet temperature under the corresponding combined conditions is obtained through one-dimensional design calculation. Based on the proportion of the circumferential angle of all circumferential positions above the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 within one blade cycle on the second curve, the proportion of the circumferential angle of all circumferential positions below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 within one blade cycle on the second curve, and the first cold air outlet temperature and the second cold air outlet temperature, the temperature characterization value of the cold air outlet region of the sealing cavity 8 is obtained by analysis.

[0022] In this embodiment, dimensionless pressure coefficients at multiple circumferential positions upstream and downstream of the sealing cavity 8 at the rim sealing structure of the aero-engine are used to construct a first curve characterizing the change of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 with the relative circumferential angle, and a second curve characterizing the change of the dimensionless pressure coefficient of the downstream pressure distribution with the relative circumferential angle. The average pressure of the upstream and downstream of the sealing cavity 8 in the entire circumferential direction is extracted based on the corresponding curves. Then, the average pressure of the high-pressure region (higher than the average pressure) and the average pressure of the low-pressure region (lower than the average pressure) in the circumferential direction are calculated respectively. By substituting the upstream high-pressure and downstream high-pressure combinations, and the upstream high-pressure and downstream low-pressure combinations, into one-dimensional design calculations, the temperatures of two sets of gas intrusion regions can be obtained. Similarly, by substituting the upstream low-pressure and downstream high-pressure combinations, and the upstream low-pressure and downstream low-pressure combinations, into one-dimensional design calculations, the temperatures of two sets of cold air outflow regions can be obtained. Finally, by determining the proportion of the downstream high-pressure and low-pressure regions in the circumferential angle of the sealing cavity 8, the overall temperature characterization values ​​of gas intrusion and cold air outflow in the rim sealing region can be calculated respectively. This method overcomes the shortcomings of traditional one-dimensional design calculations that do not fully consider the influence of three-dimensional circumferential non-uniform pressure. It can quantify the degree of gas intrusion and cold air outflow in the rim seal within the one-dimensional design calculation framework, thereby significantly improving the accuracy of one-dimensional design calculations for the high-pressure turbine secondary air system of aero-engines and providing important support for the design and development of aero-engine secondary air systems.

[0023] To achieve the above-mentioned technical effects, the present invention also provides a dimensionality reduction characterization system for the circumferential non-uniform performance parameters of aero-engine rim seals, used to implement the aforementioned method for dimensionality reduction characterization of the circumferential non-uniform performance parameters of aero-engine rim seals, comprising: The data acquisition module 9 is used to calculate the dimensionless pressure coefficient at the corresponding circumferential position upstream of the sealing cavity 8 and the dimensionless pressure coefficient at the corresponding circumferential position downstream of the sealing cavity 8 based on the local static pressure at multiple circumferential positions upstream of the sealing cavity 8, the local static pressure at multiple circumferential positions downstream of the sealing cavity 8, the total pressure at the inlet of the stator blade upstream of the sealing cavity 8 and the static pressure at the inlet of the moving blade downstream of the sealing cavity 8. The pressure distribution curve construction module 1 is used to construct a first curve characterizing the change of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 with the relative circumferential angle, and a second curve characterizing the change of the dimensionless pressure coefficient of the downstream pressure distribution with the relative circumferential angle, based on the dimensionless pressure coefficient of the upstream corresponding circumferential position of the sealing cavity 8 and the dimensionless pressure coefficient of the downstream pressure distribution. The first curve analysis module 2 is used to determine the local static pressure corresponding to the average value of the dimensionless pressure coefficient within one blade cycle on the first curve as the first circumferential average pressure upstream of the sealing cavity 8, and to calculate the first upstream pressure average value of the local static pressure at all circumferential positions higher than the first circumferential average pressure within the corresponding blade cycle, and the second upstream pressure average value of the local static pressure at all circumferential positions lower than the first circumferential average pressure. The second curve analysis module 3 is used to determine the local static pressure corresponding to the average value of the dimensionless pressure coefficient within one blade cycle on the second curve as the second circumferential average pressure downstream of the sealing cavity 8, and to calculate the first downstream pressure average value of the local static pressure at all circumferential positions higher than the second circumferential average pressure within the corresponding blade cycle, and the second downstream pressure average value of the local static pressure at all circumferential positions lower than the second circumferential average pressure. The gas intrusion temperature analysis module 4 is used to obtain the first gas intrusion temperature under the corresponding combination conditions by one-dimensional design calculation, taking the first upstream pressure average value and the first downstream pressure average value as input; and to obtain the second gas intrusion temperature under the corresponding combination conditions by one-dimensional design calculation, taking the first upstream pressure average value and the second downstream pressure average value as input. The intrusion area temperature characterization module 5 is used to analyze and obtain the temperature characterization value of the gas intrusion area of ​​the sealing cavity 8 by considering the proportion of the circumferential angle of all circumferential positions with a dimensionless pressure coefficient value higher than the average value of the upstream pressure distribution of the sealing cavity 8 within one blade cycle on the second curve, the proportion of the circumferential angle of all circumferential positions with a dimensionless pressure coefficient value lower than the average value of the upstream pressure distribution of the sealing cavity 8 within one blade cycle on the second curve, the first gas intrusion temperature, and the second gas intrusion temperature. The cold air outlet temperature analysis module 6 is used to obtain the first cold air outlet temperature under the corresponding combination conditions by one-dimensional design calculation, taking the combination conditions of the second upstream pressure average value and the first downstream pressure average value as input; and to obtain the second cold air outlet temperature under the corresponding combination conditions by one-dimensional design calculation, taking the combination conditions of the second upstream pressure average value and the second downstream pressure average value as input. The outflow region temperature characterization module 7 is used to analyze and obtain the temperature characterization value of the cold air outflow region of the sealing cavity 8 by considering the proportion of the circumferential angle of all circumferential positions above the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 within one blade cycle on the second curve, the proportion of the circumferential angle of all circumferential positions below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 within one blade cycle on the second curve, the first cold air outflow temperature, and the second cold air outflow temperature.

[0024] In this embodiment, the pressure distribution curve construction module is used to perform Fourier curve fitting on the dimensionless pressure coefficient at the upstream circumferential position and the downstream circumferential position of the sealing cavity 8, respectively, to obtain the curve of the dimensionless pressure coefficient as a function of the circumferential angle, which characterizes the corresponding pressure distribution.

[0025] Example 2 See Figure 1 , Figures 3 to 5 A method for dimensionality reduction characterization of circumferential non-uniform performance parameters of aero-engine rim seals, comprising: I. Characterization of Circumferential Non-uniform Pressure on Wheel Flange Seals Step 1.1: Obtain the local static pressure at multiple circumferential positions of the aero-engine rim seal structure. 、 The total pressure at the upstream stationary vane inlet of the sealing cavity 8 And the static pressure at the downstream moving blade inlet of the sealing cavity 8 The local static pressure includes the static pressure upstream of the wheel flange seal. 、 Downstream static pressure of wheel flange seal ; In this embodiment, the local static pressure at multiple circumferential locations 、 The total pressure at the upstream stationary vane inlet of the sealing cavity 8 And the static pressure at the downstream moving blade inlet of the sealing cavity 8 Real non-uniform pressure data can be obtained through experimental measurement or through simple two-dimensional design calculations, thus it has strong availability.

[0026] Step 1.2: Based on the local static pressure and the total pressure at the upstream stationary vane inlet of the sealing cavity 8... 8. Sealing cavity downstream moving blade inlet static pressure The dimensionless pressure coefficient at the upstream circumferential position of the sealing cavity 8 was obtained through analysis. Dimensionless pressure coefficient at the corresponding circumferential position downstream ; In this embodiment, the dimensionless pressure coefficient at the circumferential position upstream of the sealing cavity 8 is... According to Analysis yielded the dimensionless pressure coefficient at the circumferential position downstream of sealing cavity 8. According to The results were obtained through analysis.

[0027] Step 1.3: Measure the dimensionless pressure coefficient of the sealing cavity 8. , Fourier curve fitting was performed to obtain the dimensionless pressure coefficient characterizing the pressure distribution upstream of the sealing cavity 8 as a function of the relative circumferential angle. The first curve showing the change, and the dimensionless pressure coefficient of the downstream pressure distribution as a function of the relative circumferential angle. The changing second curve; In this embodiment, the circumferential distribution of the dimensionless pressure coefficient is calculated using a Fourier curve fitting method, with the Fourier series expanded to 5-7 times the circumferential angle. The sine and cosine functions are used. Employing the Fourier series curve fitting method, a high-precision functional expression of the dimensionless pressure coefficient distributed circumferentially can be achieved, and this expression can be effectively integrated into a dimension-reduced characterization model of the non-uniform circumferential pressure of the wheel rim seal. For example... Figure 4 The Fourier fitting curve (first curve) of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 as a function of the relative circumferential angle is given.

[0028] II. Dimensional reduction of circumferential non-uniform pressure in the rim seal Step 2.1: Based on the obtained first curve, determine the local static pressure corresponding to the average value of the dimensionless pressure coefficient within one blade cycle on the first curve as the first circumferential average pressure upstream of the sealing cavity 8. Then, statistical analysis was conducted on the pressure exceeding the first circumferential average pressure within the corresponding blade cycle. The average value of the first upstream pressure at all circumferential locations of local static pressure and lower than the average pressure of the first week. The average value of the second upstream pressure at all circumferential locations under local static pressure ; Based on the obtained second curve, the local static pressure corresponding to the average dimensionless pressure coefficient within one blade cycle on the second curve is the second circumferential average pressure downstream of the sealing cavity 8. Then, statistical analysis was conducted on the corresponding blade cycle to determine the pressure exceeding the second circumferential average pressure. The average first downstream pressure at all circumferential locations under local static pressure and lower than the average pressure of the second week. The average second downstream pressure at all circumferential locations under local static pressure The relevant average pressure values ​​are as follows: Figure 5 As shown.

[0029] Step 2.2: Using the average value of the first upstream pressure Average downstream pressure The combination conditions are taken as input, and the first gas intrusion temperature under the corresponding combination conditions is obtained through one-dimensional design calculation. T ruqin1 ; based on the average value of the first upstream pressure Second downstream average pressure The combination conditions are taken as input, and the second gas intrusion temperature under the corresponding combination conditions is obtained through one-dimensional design calculation. T ruqin2 ; For the turbine disk cavity rim seal, its upstream high-pressure zone corresponds to the gas intrusion area, and its upstream low-pressure zone corresponds to the cold gas outflow area. Therefore, in this embodiment, for the gas intrusion area, the upstream pressure of the sealing cavity 8 of the rim seal structure is... The downstream pressure of the sealed cavity 8 is respectively and Upstream high pressure Combined with downstream high voltage By combining and substituting these values ​​into the one-dimensional design calculation, the first gas intrusion temperature can be obtained. T ruqin1 ; Upstream high pressure With downstream low voltage By combining and substituting these values ​​into the one-dimensional design calculation, the second gas intrusion temperature can be obtained. T ruqin2 .

[0030] Step 2.3: Using the average value of the second upstream pressure Average downstream pressure The combination conditions are taken as input, and the first cold air outlet temperature under the corresponding combination conditions is obtained through one-dimensional design calculation. T chuliu1 ; with the second upstream pressure average Second downstream average pressure The combination conditions are taken as input, and the second cold air outlet temperature under the corresponding combination conditions is obtained through one-dimensional design calculation. T chuliu2 ; In this embodiment, for the cold air outflow area, the upstream pressure of the rim seal is... The downstream pressures are respectively and Upstream low pressure Combined with downstream high voltage By combining these parameters and substituting them into the one-dimensional design calculation, the first cold air outlet temperature can be obtained. T chuliu1 ; Upstream low pressure With downstream low voltage By combining these parameters and incorporating them into the one-dimensional design calculation, the outlet temperature of the second cold air can be obtained. T chuliu2 .

[0031] III. Temperature Characterization of Fuel Intrusion and Cold Air Outflow Zones in the Rim Seal Step 3.1: Calculate the percentage of the circumferential angle of all circumferential positions above the average dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 within one blade cycle on the second curve, and the percentage of the circumferential angle of all circumferential positions below the average dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 within one blade cycle on the second curve, and based on the first gas intrusion temperature... T ruqin1 Second gas intrusion temperature T ruqin2 The temperature characterization values ​​of the gas intrusion area in the sealed cavity were obtained through analysis; In this embodiment, the temperature characterization value of the gas intrusion area of ​​the sealed cavity 8 is based on... Analysis yielded, among which This represents the temperature characterization value of the gas intrusion zone in the sealed cavity 8. This represents the percentage of the circumferential angle of all circumferential positions on the second curve that are higher than the average value of the dimensionless pressure coefficient upstream of the sealing cavity 8 within one blade cycle, within the corresponding blade cycle. The circumferential angle percentage of all circumferential positions on the second curve that are below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity 8 within one blade cycle is given within the corresponding blade cycle.

[0032] Step 3.2, according to and and the first cold air outlet temperature T chuliu1 Second cold air outlet temperature T chuliu2 The temperature characterization values ​​of the cold gas outflow area in the sealed cavity were obtained through analysis; In this embodiment, the temperature characterization value of the cold air outlet region of the sealed cavity 8 is based on... The results were obtained through analysis.

[0033] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A method for dimensionality reduction characterization of circumferential non-uniform performance parameters of aero-engine rim seals, characterized in that, include: Based on the local static pressure at multiple circumferential positions upstream and downstream of the sealing cavity at the wheel rim sealing structure of the aero-engine, as well as the total pressure at the inlet of the stator blade upstream and the static pressure at the inlet of the moving blade downstream of the sealing cavity, the dimensionless pressure coefficient at the corresponding circumferential position upstream and downstream of the sealing cavity are calculated respectively. Based on the dimensionless pressure coefficients at the corresponding circumferential positions upstream and downstream of the sealing cavity, a first curve representing the change of the dimensionless pressure coefficient with the relative circumferential angle in the upstream pressure distribution of the sealing cavity, and a second curve representing the change of the dimensionless pressure coefficient with the relative circumferential angle in the downstream pressure distribution are constructed. The local static pressure corresponding to the average value of the dimensionless pressure coefficient within one blade cycle on the first curve is determined as the first circumferential average pressure upstream of the sealing cavity. The first upstream pressure average value of the local static pressure at all circumferential positions above the first circumferential average pressure within the corresponding blade cycle, and the second upstream pressure average value of the local static pressure at all circumferential positions below the first circumferential average pressure are calculated. The local static pressure corresponding to the average value of the dimensionless pressure coefficient within one blade cycle on the second curve is determined as the second circumferential average pressure downstream of the sealing cavity. The first downstream average pressure of the local static pressure at all circumferential positions above the second circumferential average pressure and the second downstream average pressure of the local static pressure at all circumferential positions below the second circumferential average pressure are calculated within the corresponding blade cycle. Using the combined conditions of the first upstream pressure average and the first downstream pressure average as input, the first gas intrusion temperature under the corresponding combined conditions is obtained through one-dimensional design calculation; using the combined conditions of the first upstream pressure average and the second downstream pressure average as input, the second gas intrusion temperature under the corresponding combined conditions is obtained through one-dimensional design calculation. Based on the proportion of the circumferential angle of all circumferential positions above the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, the proportion of the circumferential angle of all circumferential positions below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, as well as the first gas intrusion temperature and the second gas intrusion temperature, the temperature characterization value of the gas intrusion area of ​​the sealing cavity is obtained by analysis. Using the combined conditions of the second upstream pressure average and the first downstream pressure average as input, the first cold air outlet temperature under the corresponding combined conditions is obtained through one-dimensional design calculation; using the combined conditions of the second upstream pressure average and the second downstream pressure average as input, the second cold air outlet temperature under the corresponding combined conditions is obtained through one-dimensional design calculation. Based on the proportion of the circumferential angle of all circumferential positions above the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, the proportion of the circumferential angle of all circumferential positions below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, and the first cold air outlet temperature and the second cold air outlet temperature, the temperature characterization value of the cold air outlet region of the sealing cavity is obtained by analysis.

2. The method for dimensionality reduction characterization of circumferential non-uniform performance parameters of aero-engine rim seals according to claim 1, characterized in that, Dimensionless pressure coefficient at the corresponding circumferential position upstream of the sealing cavity ,in To seal the local static pressure at the corresponding circumferential position upstream of the cavity, The static pressure at the inlet of the moving blade at the corresponding circumferential position downstream of the sealing cavity. The total pressure at the stator inlet at the corresponding circumferential position upstream of the sealing cavity; Dimensionless pressure coefficient at the circumferential position downstream of the sealing cavity , To seal the local static pressure at the corresponding circumferential position downstream of the cavity, The static pressure at the inlet of the moving blade at the corresponding circumferential position downstream of the sealing cavity. The total pressure at the inlet of the stationary vane at the corresponding circumferential position upstream of the sealing cavity.

3. The method for dimensionality reduction characterization of circumferential non-uniform performance parameters of aero-engine rim seals according to claim 1, characterized in that, The methods for constructing a first curve characterizing the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity as a function of the relative circumferential angle, and a second curve characterizing the dimensionless pressure coefficient of the downstream pressure distribution as a function of the relative circumferential angle, include: Fourier curve fitting was performed on the dimensionless pressure coefficient at the corresponding circumferential position upstream and downstream of the sealing cavity to obtain the curves of the dimensionless pressure coefficient as a function of the circumferential angle, which characterize the corresponding pressure distribution.

4. The method for dimensionality reduction characterization of circumferential non-uniform performance parameters of aero-engine rim seals according to claim 1, characterized in that, The weighting coefficients of the first gas intrusion temperature are obtained by weighting the proportion of the circumferential angles of all circumferential positions above the average value of the dimensionless pressure coefficients of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, and the weighting coefficients of the second gas intrusion temperature are obtained by weighting and summing the proportions of the circumferential angles of all circumferential positions below the average value of the dimensionless pressure coefficients of the upstream pressure distribution of the sealing cavity within one blade cycle. The weighting coefficients of the first cold air outlet temperature are obtained by weighting the proportion of the circumferential angles of all circumferential positions above the average value of the dimensionless pressure coefficients of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, and the weighting coefficients of the second cold air outlet temperature are obtained by weighting and summing the weighted values.

5. A system for dimensionality reduction characterization of circumferential non-uniform performance parameters of aero-engine rim seals, used to implement the method for dimensionality reduction characterization of circumferential non-uniform performance parameters of aero-engine rim seals as described in any one of claims 1 to 4, characterized in that, include: The data acquisition module is used to calculate the dimensionless pressure coefficients at the corresponding circumferential positions upstream and downstream of the sealing cavity based on the local static pressure at multiple circumferential positions upstream and downstream of the sealing cavity at the sealing cavity of the aero-engine wheel rim sealing structure, as well as the total pressure at the upstream stator inlet and the static pressure at the downstream moving blade inlet of the sealing cavity. The pressure distribution curve construction module is used to construct a first curve characterizing the change of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity with the relative circumferential angle, and a second curve characterizing the change of the dimensionless pressure coefficient of the downstream pressure distribution with the relative circumferential angle, based on the dimensionless pressure coefficient at the corresponding circumferential position upstream of the sealing cavity and the dimensionless pressure coefficient at the corresponding circumferential position downstream of the sealing cavity. The first curve analysis module is used to determine the local static pressure corresponding to the average value of the dimensionless pressure coefficient within one blade cycle on the first curve as the first circumferential average pressure upstream of the sealing cavity, and to calculate the first upstream pressure average value of the local static pressure at all circumferential positions higher than the first circumferential average pressure within the corresponding blade cycle, and the second upstream pressure average value of the local static pressure at all circumferential positions lower than the first circumferential average pressure. The second curve analysis module is used to determine the local static pressure corresponding to the average value of the dimensionless pressure coefficient within one blade cycle on the second curve as the second circumferential average pressure downstream of the sealing cavity, and to calculate the first downstream average pressure of the local static pressure at all circumferential positions that are higher than the second circumferential average pressure within the corresponding blade cycle, and the second downstream average pressure of the local static pressure at all circumferential positions that are lower than the second circumferential average pressure. The gas intrusion temperature analysis module is used to obtain the first gas intrusion temperature under the corresponding combination conditions by taking the first upstream pressure average value and the first downstream pressure average value as input and through one-dimensional design calculation; and to obtain the second gas intrusion temperature under the corresponding combination conditions by taking the first upstream pressure average value and the second downstream pressure average value as input and through one-dimensional design calculation. The intrusion area temperature characterization module is used to analyze and obtain the temperature characterization value of the gas intrusion area of ​​the sealing cavity by considering the following parameters: the percentage of circumferential angles of all circumferential positions above the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve; the percentage of circumferential angles of all circumferential positions below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve; the first gas intrusion temperature; and the second gas intrusion temperature. The cold air outlet temperature analysis module is used to obtain the first cold air outlet temperature under the corresponding combination conditions by taking the combination of the second upstream pressure average value and the first downstream pressure average value as input and through one-dimensional design calculation; and to obtain the second cold air outlet temperature under the corresponding combination conditions by taking the combination of the second upstream pressure average value and the second downstream pressure average value as input and through one-dimensional design calculation. The outflow region temperature characterization module is used to analyze and obtain the temperature characterization value of the cold air outflow region of the sealing cavity based on the proportion of the circumferential angle of all circumferential positions above the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, the proportion of the circumferential angle of all circumferential positions below the average value of the dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve, as well as the first cold air outflow temperature and the second cold air outflow temperature.

6. The dimensionality reduction characterization system for circumferential non-uniform performance parameters of aero-engine rim seals according to claim 5, characterized in that, In the data acquisition module, the dimensionless pressure coefficient at the corresponding circumferential position upstream of the sealing cavity is... ,in To seal the local static pressure at the corresponding circumferential position upstream of the cavity, The static pressure at the inlet of the moving blade at the corresponding circumferential position downstream of the sealing cavity. The total pressure at the stator inlet at the corresponding circumferential position upstream of the sealing cavity; Dimensionless pressure coefficient at the circumferential position downstream of the sealing cavity , To seal the local static pressure at the corresponding circumferential position downstream of the cavity, The static pressure at the inlet of the moving blade at the corresponding circumferential position downstream of the sealing cavity. The total pressure at the inlet of the stationary vane at the corresponding circumferential position upstream of the sealing cavity.

7. The dimensionality reduction characterization system for circumferential non-uniform performance parameters of aero-engine rim seals according to claim 5, characterized in that, The pressure distribution curve construction module is used to perform Fourier curve fitting on the dimensionless pressure coefficient at the corresponding circumferential position upstream of the sealing cavity and the corresponding circumferential position downstream, respectively, to obtain the curve of the dimensionless pressure coefficient as a function of the circumferential angle, which characterizes the corresponding pressure distribution.

8. The dimensionality reduction characterization system for circumferential non-uniform performance parameters of aero-engine rim seals according to claim 5, characterized in that, In the intrusion area temperature characterization module, the circumferential angle ratio of all circumferential positions above the average dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve is used as the weighting coefficient of the first gas intrusion temperature, and the circumferential angle ratio of all circumferential positions below the average dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve is used as the weighting coefficient of the second gas intrusion temperature. The weighted summation is then performed to obtain the gas intrusion area temperature characterization value of the sealing cavity. In the outflow region temperature characterization module, the circumferential angle ratio of all circumferential positions above the average dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve is used as the weighting coefficient of the first cold air outflow temperature, and the circumferential angle ratio of all circumferential positions below the average dimensionless pressure coefficient of the upstream pressure distribution of the sealing cavity within one blade cycle on the second curve is used as the weighting coefficient of the second cold air outflow temperature. The weighted summation is then performed to obtain the temperature characterization value of the cold air outflow region of the sealing cavity.

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