An aero-engine air system gill heat state relative position relationship analysis method

Abstract

The application provides an aero-engine air system grid heat state relative position relationship analysis method, comprising the following steps: step one, cold state relative position relationship analysis is carried out on the aero-engine air system grid, and the aero-engine air system grid cold state relative position relationship is obtained; step two, the grid rotor-stator deformation analysis point is determined, the aero-engine air system grid rotor-stator deformation analysis is carried out, and the deformation result of the grid rotor-stator deformation analysis point is obtained; step three, heat state relative position relationship analysis is carried out on the aero-engine air system grid, and the grid heat state relative position relationship is obtained according to the grid rotor-stator deformation analysis point and the grid cold state relative position relationship. The method provided by the application not only considers the influence of the grid radial and axial deformation on the grid heat state relative position relationship, but also predicts the grid heat state relative position relationship before engine test, thereby predicting the possible faults caused by the excessive or insufficient grid heat state gap, and higher analysis precision can be obtained.

Description

Technical Field

[0001] This application belongs to the field of aero-engine technology, and specifically relates to a method for analyzing the thermal relative position relationship of the air grates in an aero-engine air system. Background Technology

[0002] The air system of an aero-engine plays a crucial role in ensuring a suitable internal working environment for the engine during operation, making it a vital system for safe engine operation. The grating structure is a commonly used structural form in aero-engine air systems. During engine operation, the relative hot positions of the grating teeth are influenced by various factors and continuously change with the engine's operating conditions, resulting in constant variations in the hot-state clearance of the grating teeth. Excessive hot-state clearance of the air system grating teeth can cause significant gas leakage and reduce sealing effectiveness; insufficient hot-state clearance can lead to wear on the grating teeth and stator components, and in severe cases, cause shaft seizure and other malfunctions. Therefore, accurately analyzing the relative hot-state positions of the grating teeth in an aero-engine air system is a key factor in analyzing the realization of various functions of the air system and ensuring safe engine operation.

[0003] There are two main existing methods for analyzing the relative positional relationship of sieve teeth in the hot state. One method calculates the radial deformation of the rotating and stationary parts of the sieve teeth caused by thermal stress and centrifugal load, and adds the relative deformation to the cold-state clearance of the sieve teeth to obtain the relative positional relationship of the sieve teeth in the hot state. However, this method only considers the radial deformation of the sieve teeth and ignores the influence of the axial deformation of the sieve teeth, resulting in insufficient accuracy of the analysis results. The other method uses X-rays to measure the axial and radial relative displacement of the sieve tooth honeycomb during engine testing, and obtains the relative positional relationship of the sieve teeth in the hot state by locating the sieve teeth in the corresponding state. However, this method cannot predict the relative positional relationship of the sieve teeth in the hot state before engine testing, nor can it predict the possible faults caused by excessively large or small hot-state clearance of the sieve teeth. In addition, this analysis method is costly. Summary of the Invention

[0004] The purpose of this application is to provide a method for analyzing the thermal relative position relationship of the air grates in an aero-engine air system, in order to solve or mitigate at least one of the problems in the background art.

[0005] The technical solution of this application is: a method for analyzing the thermal relative position relationship of the air grates in an aero-engine air system, comprising:

[0006] Step 1: Perform a cold-state relative positional analysis on the air system grate teeth of the aero-engine to obtain the cold-state relative positional relationship of the air system grate teeth;

[0007] Step 2: Determine the deformation analysis points of the grate tooth stator, conduct deformation analysis of the grate tooth stator in the aero-engine air system, and obtain the deformation results at the grate tooth stator deformation analysis points;

[0008] Step 3: Perform a hot-state relative positional analysis on the air system grates of the aero-engine. Based on the analysis points of the grates' deformation and the cold-state relative positional relationship of the grates, obtain the hot-state relative positional relationship of the grates.

[0009] Furthermore, the relative positional relationship of the air system's grate teeth in the cold state includes:

[0010] 1) Parameter A1 represents the negative value of the distance from the front end of the plane of the component containing the cell to the front end of the cell.

[0011] 2) Parameter H represents the honeycomb thickness;

[0012] 3) Parameter L represents the distance between the front and rear ends of the plane of the component containing the cell;

[0013] 4) Parameter h represents the cold radial gap distance between the grating teeth and the honeycomb, determined by the tooth tip diameter d of the grating disc. 转 and the corresponding inner diameter d of the cell 静 , using the formula h=(d 静 -d 转 ) / 2 is obtained by calculation;

[0014] 5) Parameter l represents the cell length;

[0015] 6) Parameter a1 represents the distance from the tip of the first sieve to the front end of the honeycomb.

[0016] 7) The parameter an represents the distance from the tip of the nth sieve to the front end of the honeycomb.

[0017] Furthermore, the deformation analysis points of the comb-tooth stator include:

[0018] The rotor deformation analysis points formed by the tips of the comb teeth; and

[0019] The static deformation analysis points are formed by the two ends of the plane where the honeycomb is located.

[0020] Furthermore, the axial deformation of the deformation analysis point E1 at the front end of the plane where the honeycomb is located is Δqz, and the radial deformation is Δqj;

[0021] The axial deformation of point E2 at the front end of the plane where the honeycomb is located is Δhz, and the radial deformation is Δhj.

[0022] The axial deformation of the first tooth tip e1 is Δe1z, and the radial deformation is Δe1j.

[0023] The axial deformation of the tip of the nth tooth is Δenz, and the radial deformation is Δenj.

[0024] Furthermore, the relative hot positions of the air system grates are determined based on the following factors:

[0025] 1) The parameter Δqz represents the axial deformation at the front end of the plane of the component containing the honeycomb.

[0026] 2) The parameter Δqj represents the radial deformation at the front end of the plane of the component containing the honeycomb.

[0027] 3) The parameter Δhz represents the axial deformation at the rear end of the plane of the component containing the honeycomb.

[0028] 4) The parameter Δhj represents the radial deformation at the rear end of the plane of the component containing the honeycomb.

[0029] 5) The parameter Δa1z represents the axial deformation of the tip of the first tooth;

[0030] 6) The parameter Δa1j represents the radial deformation of the tip of the first tooth;

[0031] 7) The parameter Δanj represents the radial deformation of the tip of the nth tooth.

[0032] Furthermore, the relative positions of the comb teeth in the hot state include:

[0033] The rotation angle of the honeycomb plane under hot conditions, the coordinates of the front end point of the honeycomb plane in the hot relative coordinate system, the position of the honeycomb plane in the hot relative coordinate system, and the coordinates of each tooth tip of the comb in the hot relative coordinate system.

[0034] Furthermore, the rotation angle of the honeycomb plane under hot conditions is obtained through the following process:

[0035] Substituting the deformation values ​​of the air system's pylon stator deformation analysis points into the thermal relative coordinate system, we obtain the coordinates of the front end point (A1+Δqz, H+h+Δqj) and the rear end point (A1+L+Δhz, H+h+Δhj) of the component plane containing the honeycomb.

[0036] The rotation angle θ of the component plane relative to the cold plane under hot conditions is determined by the coordinates of the front and rear endpoints of the component plane where the honeycomb is located. The rotation angle θ is the rotation angle of the honeycomb plane.

[0037] Furthermore, the coordinates of the front end point of the cellular plane in the thermal relative coordinate system are (x1, y1) = (A1 + Δqz + H·sinθ - A1·cosθ, H + h + Δqj - H·cosθ - A1·sinθ).

[0038] Furthermore, the process for determining the position of the honeycomb plane in the thermal relative coordinate system is as follows:

[0039] Based on the coordinates of the front end point of the cellular plane in the thermal relative coordinate system and the slope k = tanθ determined by the rotation angle, the straight line of the cellular plane in the relative coordinate system is determined to be y = y1 - tanθ·x1.

[0040] Furthermore, the coordinates of each tooth tip of the shown comb in the thermal relative coordinate system include:

[0041] The coordinates of the tip of the first tooth are (a1 + △a1z, △a1j), and the coordinates of the tip of the nth tooth are (an + △anz, △anj).

[0042] The method for analyzing the thermal relative position relationship of the air system grates in the aero-engine provided in this application not only considers the influence of radial and axial deformation of the grates on their thermal relative position relationship, but also predicts the thermal relative position relationship of the grates before engine testing, thereby predicting possible faults due to excessive or insufficient thermal clearance of the grates. This method achieves higher analytical accuracy than existing technologies. Furthermore, compared to X-ray measurement, it eliminates the need for X-ray measurement and can predict the thermal relative position relationship of the air system grates during engine testing at a lower cost. Attached Figure Description

[0043] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0044] Figure 1 This is a schematic diagram of the analysis process for the relative positional relationship of the comb teeth in the hot state in this application.

[0045] Figure 2 This is a schematic diagram showing the relative positions of the comb teeth in the cold state according to an embodiment of this application.

[0046] Figure 3 This is a schematic diagram showing the location of deformation analysis points of a caster tooth rotor according to an embodiment of this application.

[0047] Figure 4 This is a schematic diagram showing the relative positions of the comb teeth in the hot state according to an embodiment of this application. Detailed Implementation

[0048] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0049] like Figure 1 As shown, the method for analyzing the relative positional relationship of the air fins in the air system of an aero-engine provided in this application includes the following steps:

[0050] Step 1: Perform a cold-state relative positional analysis on the air grates of the aero-engine to obtain the cold-state relative positional relationship of the grates.

[0051] like Figure 2The diagram shown is a cold-state schematic diagram of the air system grates in a relative coordinate system provided in this embodiment of the application. Based on this cold-state schematic diagram, the relative positional relationship of the air system grates in a cold state can be determined, including:

[0052] 1) Parameter A1 represents the negative value of the distance from the front end of the plane of the component containing cell 2 to the front end of the cell.

[0053] In the aero-engine application examples provided in this application, the results can be obtained through design drawings or physical measurements before engine assembly.

[0054] 2) Parameter H represents the thickness of cell 2;

[0055] In the aero-engine application examples provided in this application, the results can be obtained through design drawings or physical measurements before engine assembly.

[0056] 3) Parameter L represents the distance between the front and rear ends of the plane of the component containing cell 2;

[0057] In the aero-engine application examples provided in this application, the results can be obtained through design drawings or physical measurements before engine assembly.

[0058] 4) Parameter h represents the cold radial gap distance between the grating teeth 1 and the honeycomb 2, which is determined by the tooth tip diameter d of the grating disc. 转 and the corresponding inner diameter d of the cell 静 , using the formula h=(d 静 -d 转 ) / 2 is obtained by calculation;

[0059] In the aero-engine application examples provided in this application, d 转 and d 静 It can be obtained through design drawings or physical measurements before engine assembly.

[0060] 5) Parameter l represents the length of cell 2;

[0061] In the aero-engine application examples provided in this application, the results can be obtained through design drawings or physical measurements before engine assembly.

[0062] 6) Parameter a1 represents the distance from the tip of the first sieve to the front end of the honeycomb.

[0063] In the aero-engine application examples provided in this application, the axial dimension chain of the entire machine can be calculated.

[0064] 7) The parameter an represents the distance from the tip of the nth sieve to the front end of the honeycomb.

[0065] In the aero-engine application examples provided in this application, the axial dimension chain of the entire machine can be calculated.

[0066] Step 2: Conduct deformation analysis of the stator rotating in the aero-engine air system.

[0067] like Figure 3 The diagram shown is a schematic diagram of the deformation analysis of the air system toothed stator provided in this embodiment of the application, wherein:

[0068] 2.1) Determine the deformation analysis point of the toothed stator. The deformation analysis point should be easy to identify and its deformation amount should be accurately extracted under any working condition.

[0069] In the aero-engine application example provided in this application, the analysis points for the deformation of the comb-tooth rotor are selected at the front ends of each tooth tip, and the analysis points for the deformation of the stator are selected at the front and rear ends of the plane containing the honeycomb, such as... Figure 3 As shown.

[0070] 2.2) The air system characteristic analysis provides boundary conditions for calculating the temperature field that affects the deformation analysis of the comb tooth rotor / stator. The accuracy of the analysis affects the accuracy of the deformation analysis results.

[0071] In the aero-engine application example provided in this application, the air system characteristic analysis model adopts the air system model after whole-engine cavity temperature and cavity pressure test calibration, which can significantly improve the analysis accuracy.

[0072] 2.3) Temperature field analysis provides boundary conditions for calculating the thermal loads that affect the deformation analysis of the comb tooth rotor / stator. The accuracy of this analysis affects the accuracy of the deformation analysis results.

[0073] In the aero-engine application example provided in this application, the temperature field analysis model adopts the thermal analysis model after whole-engine wall temperature test calibration, which can significantly improve the analysis accuracy.

[0074] 2.4) Deformation analysis of the comb tooth rotating / stator.

[0075] Deformation analysis of the gear rotor and stator can be performed using either whole-machine deformation analysis or component-level deformation analysis. Generally, whole-machine deformation analysis yields more accurate deformation data. When using component-level deformation analysis, it is necessary to unify the axial deformation references for all rotors and stators.

[0076] In the aero-engine application example provided in this application, component-level deformation analysis is adopted, and all axial deformations of the grate rotor / stator component are relative to the front end face of the intermediate casing.

[0077] in, Figure 3 The deformation analysis results for each analysis point shown are as follows:

[0078] The axial deformation Δqz and radial deformation Δqj are measured at the deformation point E1 at the front end of the plane where cell 2 is located.

[0079] The axial deformation Δhz and radial deformation Δhj of the deformation point E2 at the front end of the plane where cell 2 is located;

[0080] The axial deformation of the first tooth tip e1 is Δe1z, and the radial deformation is Δe1j.

[0081] The axial deformation of the tip of the nth tooth is Δenz, and the radial deformation is Δenj.

[0082] Step 3: Analyze the relative positions of the air system grates in the hot state. Based on the deformation analysis points and the relative positions of the grates in the cold state, obtain the relative positions of the grates in the hot state.

[0083] like Figure 4 The diagram shown illustrates the relative coordinate system of the air system grates in their thermal state. Factors to consider in determining the relative thermal positions of the air system grates include:

[0084] 1) The parameter Δqz represents the axial deformation at the front end of the plane of the component containing the honeycomb.

[0085] 2) The parameter Δqj represents the radial deformation at the front end of the plane of the component containing the honeycomb.

[0086] 3) The parameter Δhz represents the axial deformation at the rear end of the plane of the component containing the honeycomb.

[0087] 4) The parameter Δhj represents the radial deformation at the rear end of the plane of the component containing the honeycomb.

[0088] 5) The parameter Δa1z represents the axial deformation of the tip of the first tooth;

[0089] 6) The parameter Δa1j represents the radial deformation of the tip of the first tooth;

[0090] 7) The parameter Δanj represents the radial deformation of the tip of the nth tooth;

[0091] The above parameters can be obtained through deformation analysis in step two.

[0092] The relative positions of the air system grates in the hot state are obtained based on the deformation analysis points and the cold-state relative positions of the grates. These relative positions include:

[0093] a) Rotation angle of the honeycomb plane under hot state.

[0094] Substituting the deformation values ​​of the air system tooth stator deformation analysis points obtained in step two into the above coordinate system, we can obtain... Figure 4 The coordinates of the front end point (A1+Δqz, H+h+Δqj) and the rear end point (A1+L+Δhz, H+h+Δhj) of the component plane where the honeycomb is located are shown.

[0095] The rotation angle θ between the hot and cold planes of the component containing the honeycomb is determined by the coordinates of these two points. This angle θ is also the rotation angle of the honeycomb plane.

[0096] b) Coordinates of the front end point of the cellular plane in the relative coordinate system.

[0097] exist Figure 4 Using the data obtained in steps one and two, calculate the coordinates of the front end point of the honeycomb plane in the relative coordinate system shown. The coordinates are (x1, y1) = (A1 + Δqz + H·sinθ - A1·cosθ, H + h + Δqj - H·cosθ - A1·sinθ).

[0098] c) The position of the cellular plane in the relative coordinate system.

[0099] Based on the coordinates of the front point of the cellular plane in the relative coordinate system and the slope k = tanθ determined by the rotation angle, the straight line of the cellular plane in the relative coordinate system can be determined as y = kx = y1 - tanθ·x1.

[0100] d) The coordinates of each tooth tip in the relative coordinate system.

[0101] Substituting the deformation values ​​of the air system toothed rotor deformation analysis points obtained in step two into the above coordinate system, we can obtain... Figure 4 The coordinates of the first tooth tip are (a1 + △a1z, △a1j), and the coordinates of the nth tooth tip are (an + △anz, △anj).

[0102] Through the above steps, we obtained Figure 4 The diagram shows the relative positions of the air system grates in their thermal state.

[0103] The method for analyzing the thermal relative position relationship of the air system grates in the aero-engine provided in this application not only considers the influence of radial and axial deformation of the grates on their thermal relative position relationship, but also predicts the thermal relative position relationship of the grates before engine testing, thereby predicting possible faults due to excessive or insufficient thermal clearance of the grates. This method achieves higher analytical accuracy than existing technologies. Furthermore, compared to X-ray measurement, it eliminates the need for X-ray measurement and can predict the thermal relative position relationship of the air system grates during engine testing at a lower cost.

[0104] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method for analyzing the relative positional relationship of the ferrules in the thermal state of an aero-engine air system, characterized in that, include: Step 1: Perform a cold-state relative positional analysis on the air system grate teeth of the aero-engine to obtain the cold-state relative positional relationship of the air system grate teeth. The cold-state relative positional relationship of the air system grate teeth includes: parameter A1, representing the negative value of the distance between the front end of the component plane where the honeycomb is located and the front end of the honeycomb; parameter H, representing the honeycomb thickness; parameter L, representing the distance between the front end and the rear end of the component plane where the honeycomb is located; parameter h, representing the cold-state radial clearance distance between the grate teeth and the honeycomb, which is determined by the tooth tip diameter d of the grate disc. 转 and the corresponding inner diameter d of the cell 静 , using the formula h=(d 静 -d 转 The distance is calculated as ) / 2; parameter l represents the honeycomb length; parameter a1 represents the distance from the tip of the first tooth to the front end of the honeycomb; parameter an represents the distance from the tip of the nth tooth to the front end of the honeycomb. Step 2: Determine the deformation analysis points of the comb tooth rotor. These points include the rotor deformation analysis point formed by the front ends of the comb tooth tips and the stator deformation analysis points formed by the front and rear ends of the honeycomb plane. Conduct deformation analysis of the comb tooth rotor in the aero-engine air system to obtain the deformation results at these points. The deformation results include: axial deformation of point E1 at the front end of the honeycomb plane (Δqz, radial deformation Δqj); axial deformation of point E2 at the rear end of the honeycomb plane (Δhz, radial deformation Δhj); axial deformation of the first comb tooth tip point e1 (Δe1z, radial deformation Δe1j); and axial deformation of the nth comb tooth tip point en (Δenz, radial deformation Δenj). Step 3: Perform a hot-state relative positional analysis on the air system grates of the aero-engine. The hot-state relative positional relationship of the air system grates includes: parameter Δqz, representing the axial deformation at the front end of the plane of the component containing the honeycomb; parameter Δqj, representing the radial deformation at the front end of the plane of the component containing the honeycomb; parameter Δhz, representing the axial deformation at the rear end of the plane of the component containing the honeycomb; parameter Δhj, representing the radial deformation at the rear end of the plane of the component containing the honeycomb; parameter Δa1z, representing the axial deformation of the tip of the first grate; parameter Δa1j, representing the radial deformation of the tip of the first grate; parameter Δanj, representing the radial deformation of the tip of the nth grate. Based on the grate's deformation analysis points and its cold-state relative positional relationship, the hot-state relative positional relationship of the grates is obtained. This hot-state relative positional relationship includes the rotation angle of the honeycomb plane in the hot state, the coordinates of the front end of the honeycomb plane in the hot-state relative coordinate system, the position of the honeycomb plane in the hot-state relative coordinate system, and the coordinates of each grate tip in the hot-state relative coordinate system. Wherein: The rotation angle of the honeycomb plane under hot state is obtained through the following process: Substitute the deformation of the air system tooth stator deformation analysis point into the hot state relative coordinate system to obtain the coordinates of the front end point (A1+Δqz, H+h+Δqj) and the rear end point (A1+L+Δhz, H+h+Δhj) of the honeycomb component plane. Use the coordinates of the front and rear end points of the honeycomb component plane to determine the rotation angle θ of the honeycomb component plane under hot state working conditions relative to the cold state plane. The rotation angle θ is the honeycomb plane rotation angle. The coordinates of the front end point of the cellular plane in the thermal relative coordinate system are (x1, y1) = (A1 + Δqz + H·sinθ - A1·cosθ, H + h + Δqj - H·cosθ - A1·sinθ); The process of determining the position of the honeycomb plane in the thermal relative coordinate system is as follows: Based on the coordinates of the front end point of the honeycomb plane in the thermal relative coordinate system and the slope k=tanθ determined by the rotation angle, the straight line of the honeycomb plane in the relative coordinate system is determined to be y= ​​y1-tanθ·x1; The coordinates of each tooth tip of the comb shown in the thermal relative coordinate system include: the coordinates of the first tooth tip are (a1+△a1z, △a1j), and the coordinates of the nth tooth tip are (an+△anz, △anj).

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