A centering structure of a synchronizer ring of an aero-engine and a design method thereof

Abstract

The present invention relates to the field of design of fan / compressor regulating mechanism of aircraft engines, and discloses an aircraft engine synchronizer ring centering structure and design method thereof. By designing a limit screw on the synchronizer ring and controlling the radial clearance between the limit screw and the limit bracket, the radial deformation difference of the synchronizer ring during operation can be controlled. While improving the radial stiffness of the synchronizer ring, the deformation of the synchronizer ring can be reduced, and the problem of outward deformation of the synchronizer ring can be effectively solved, thereby improving the synchronizer ring working centering ability and synchronization adjustment accuracy. Compared with the traditional solution, the aircraft engine synchronizer ring centering structure of the present invention can reduce the size of the synchronizer ring structure, and the processing and installation are simple and easy to implement, thereby realizing the weight reduction design of the synchronizer ring; in addition, the position of the external support is set in a targeted manner according to the result of the deformation distribution of the synchronizer ring stiffness, further improving the synchronizer ring working centering ability and synchronization adjustment accuracy.

Description

Technical Field

[0001] The invention relates to the field of design of an aero-engine fan / compressor regulating mechanism, and discloses an aero-engine synchronous ring centering structure and a design method thereof. Background Art

[0002] Aircraft engines use fan / compressor stator blade adjustment mechanisms to adjust the working angle of adjustable blades, expand the stable working range, and avoid surge, which is an effective measure to ensure the stable operation of fans / compressors under various flight conditions. The synchronizer ring is one of the important components of the fan / compressor stator blade adjustment mechanism. Its function is to connect the adjustable stator blades and rotate them to the designed target angle.

[0003] Due to the deformation of the synchronizer ring during operation, the motion signal emitted by the actuating mechanism cannot be effectively and consistently transmitted to each stator blade, causing the adjustable stator blades to work "out of synchronization". The "out of synchronization" of the stator blades can cause the compressor to experience abnormal excitation, stall, surge, etc., affecting the safety and reliability of the engine operation.

[0004] In order to reduce the working deformation of the synchronous ring of the adjusting mechanism and the angular asynchronism within the stage, the traditional design method mainly adopts the method of increasing the cross-sectional area of ​​the synchronous ring and adding limit supports to the linkage ring and the receiver bracket. This method has the following problems: 1) The synchronous ring has a large diameter and limited installation space. Increasing the cross-sectional area has limited effect on improving the bending stiffness and significantly increases the weight; 2) Adding limit supports to the linkage ring and the receiver bracket can reduce the deformation of the linkage ring close to the movement direction of the receiver, increase the friction resistance between the synchronizer ring and the receiver, and cannot effectively reduce the asynchronism caused by the deformation of the linkage ring away from the receiver. Summary of the invention

[0005] The purpose of the present invention is to provide an aircraft engine synchronizer ring centering structure and a design method thereof, which can effectively improve the synchronizer ring stiffness, reduce the synchronizer ring working deformation, thereby improving the synchronizer ring centering ability and the adjustment accuracy of the adjustment mechanism, and can reduce the movement resistance of the adjustment structure and achieve weight reduction.

[0006] In order to achieve the above technical effects, the technical solution adopted by the present invention is:

[0007] An aircraft engine synchronizer ring centering structure, comprising:

[0008] A limit screw, wherein the limit screws are multiple in number, the multiple limit screws are installed on the synchronizer ring through screw holes, the limit screws are arranged radially along the synchronizer ring, and the limit screws are provided with a stop section;

[0009] A limit block, the limit block is arranged on the outer end surface of the synchronization ring, the limit block is provided with a stop assembly matched with the stop section, and the stop assembly is used to restrict the rotation of the limit screw;

[0010] A limiting groove, wherein the limiting groove is arranged on the outer end surface of the synchronization ring, and the circumferential wall surface of the limiting groove is in contact with the limiting block;

[0011] A limit bracket is installed on the receiver, and the limit bracket extends to a position where it can radially contact the outer end surface of the limit screw.

[0012] Furthermore, at least two pin holes are provided on the limiting block, and the pin holes are respectively located on both sides of the limiting groove, and pins for limiting the limiting groove are provided in the pin holes.

[0013] Furthermore, the stop segment is a regular polygonal structure, and the stop component is a regular polygonal hole matched with the stop segment.

[0014] Furthermore, the radial clearance adjustment accuracy between the limiting screw and the limiting bracket is ,in is the pitch of the limit screw, is the number of polygonal edges of the stop segment of the limit groove.

[0015] Furthermore, the limit bracket is composed of a second friction section, a supporting section and a second mounting section; wherein the second friction section is arc-shaped, and the arc of the second friction section is concentrically arranged with the synchronous ring for contacting and cooperating with the limit screw; a positioning step pin is arranged between the second mounting section of the limit bracket and the casing.

[0016] Furthermore, an inner support component is disposed inside the synchronizer ring and is in radial contact with the inner side of the synchronizer ring.

[0017] In order to achieve the above technical effects, the present invention also provides a method for designing an aircraft engine synchronizer ring centering structure, which is used to obtain the aircraft engine synchronizer ring centering structure, comprising:

[0018] According to the design structure of the adjustable stator blade and synchronizer ring of the aircraft engine, the motion resistance of a single adjustable stator blade connected to the synchronizer ring and the distance between the rotation center of the adjustable stator blade and the center of the limit screw of the synchronizer ring are analyzed and obtained;

[0019] According to the number of adjustable stator blades connected to the synchronizer ring, the motion resistance of a single adjustable stator blade, and the distance between the rotation center of the adjustable stator blade and the center of the limit screw of the synchronizer ring, the driving load under the configuration of the adjustable stator blade and the synchronizer ring is analyzed and obtained;

[0020] Constructing a finite element analysis model including an adjustable stator blade and a synchronizer ring, and using the finite element analysis model to analyze and obtain a maximum radial deformation position of the synchronizer ring after the drive load is applied;

[0021] A limit bracket and a limit screw cooperating with the limit bracket are arranged near the maximum radial deformation position, and the maximum radial deformation amount and the new maximum radial deformation position of the synchronizer ring after the driving load is applied are updated by using the finite element analysis model. The stiffness evaluation coefficient of the synchronizer ring under the driving load is obtained according to the maximum radial deformation analysis. If the stiffness evaluation coefficient is greater than or equal to a preset threshold value, it is judged that the stiffness of the synchronizer ring meets the design requirements; otherwise, a limit bracket and a limit screw are added at the new maximum radial deformation position until the stiffness evaluation coefficient of the synchronizer ring under the driving load is greater than or equal to the preset threshold value.

[0022] Furthermore, the drive load under the adjustable stator and synchronizer ring configuration ,in, is the number of adjustable stator blades connected to the synchronizer ring, is the motion resistance of a single adjustable stator blade, is the distance between the rotation center of the adjustable stator blade and the center of the limit screw of the synchronizer ring, is the number of driven loads.

[0023] Furthermore, the stiffness evaluation coefficient of the synchronizer ring under the driving load is ,in is the synchronizer ring diameter, The maximum radial deformation of the updated synchronizer ring after the driving load is applied.

[0024] Compared with the prior art, the present invention has the following beneficial effects:

[0025] 1. The present invention designs a limit screw on the synchronizer ring and controls the radial clearance between the limit screw and the limit bracket to control the difference in radial deformation of the synchronizer ring during operation. While improving the radial stiffness of the synchronizer ring, the deformation of the synchronizer ring can be reduced, effectively solving the problem of outward deformation of the synchronizer ring, thereby improving the centering ability of the synchronizer ring and the synchronization adjustment accuracy. The centering structure of the synchronizer ring of the aircraft engine of the present invention can reduce the size of the synchronizer ring structure compared with the traditional solution, and is simple and easy to manufacture and install, thereby realizing the weight reduction design of the synchronizer ring.

[0026] 2. The position of the external support of the present invention is specifically set according to the results of the stiffness and deformation distribution of the synchronizer ring, so as to further improve the centering ability and synchronization adjustment accuracy of the synchronizer ring. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of the centering structure of the synchronization ring of the aircraft engine in Example 1 or 2;

[0028] Figure 2 It is a schematic diagram of the structure of the limit screw in Example 1 or 2;

[0029] Figure 3 It is a schematic diagram of the structure of the limit block in Example 1 or 2;

[0030] Figure 4 It is a schematic diagram of the installation of the limit block and the upper limit groove of the synchronization ring in Example 1 or 2;

[0031] Figure 5 It is a schematic diagram of the deformation of the synchronization ring in Example 2;

[0032] Figure 6 Schematic diagram of the distribution of the limit screws on the synchronization ring in Example 2;

[0033] Figure 7 It is a schematic diagram of the structure of the limiting bracket in the embodiment;

[0034] Among them, 1. limit screw; 101. stop section; 102. threaded section; 103. first friction section; 104. installation section; 2. synchronization ring; 3. limit block; 301. regular polygon hole; 4. limit groove; 5. limit bracket; 501. second friction section; 502. support section; 503. second installation section; 6. pin hole; 7. positioning step pin; 8. casing. DETAILED DESCRIPTION

[0035] The present invention is further described in detail below in conjunction with the embodiments and drawings. However, it should not be understood that the scope of the above subject matter of the present invention is limited to the following embodiments, and all technologies realized based on the content of the present invention belong to the scope of the present invention.

[0036] Example 1

[0037] See also Figure 1-Figure 4 as well as Figure 7 , an aircraft engine synchronizer ring centering structure, comprising:

[0038] A limit screw 1, wherein the limit screws 1 are multiple in number, and the multiple limit screws 1 are installed on the synchronizer ring 2 through screw holes, the limit screws 1 are arranged radially along the synchronizer ring 2, and a stopper section 101 is arranged on the limit screw 1;

[0039] A limit block 3, the limit block 3 is arranged on the outer end surface of the synchronization ring 2, and a stop assembly cooperating with the stop segment 101 is provided on the limit block 3, and the stop assembly is used to restrict the rotation of the limit screw 1;

[0040] A limiting groove 4, wherein the limiting groove 4 is arranged on the outer end surface of the synchronizer ring 2, and the circumferential wall surface of the limiting groove 4 is in contact with the limiting block 3;

[0041] The limiting bracket 5 is installed on the casing 8, and the limiting bracket 5 extends to a position where it can radially contact the outer end surface of the limiting screw 1.

[0042] In this embodiment, by designing a limit screw 1 on the synchronizer ring 2 and controlling the radial clearance between the limit screw 1 and the limit bracket 5, the radial deformation difference of the synchronizer ring 2 during operation is controlled, and the deformation of the synchronizer ring 2 can be reduced while the radial stiffness of the synchronizer ring 2 is improved, and the problem of outward deformation of the synchronizer ring 2 is effectively solved, thereby improving the centering ability and synchronization adjustment accuracy of the synchronizer ring 2. The centering structure of the synchronizer ring 2 of the aircraft engine in this embodiment can reduce the structural size of the synchronizer ring 2 compared with the traditional solution, and the processing and installation are simple and easy to implement, thereby realizing the weight reduction design of the synchronizer ring 2.

[0043] In this embodiment, at least two pin holes 6 are provided on the limit block 3, and the pin holes 6 are respectively located on both sides of the limit slot 4. Pins that can limit the limit slot 4 are provided in the pin holes 6. It is convenient to set the limit block 3 according to the design position, and the pin is installed in the pin hole 6 by insertion, ensuring that the limit block 3 will not generate circumferential displacement during the operation of the synchronizer ring 2.

[0044] In this embodiment, the stopper section 101 is a regular polygon structure, and the stopper assembly is a regular polygon hole 301 that cooperates with the stopper section 101, which plays a role in preventing the limit screw 1 from rotating. The radial clearance adjustment accuracy of the limit screw 1 and the limit bracket 5 in this embodiment is ,in is the pitch of the limit screw 1, is the number of polygonal sides of the stop section 101 of the limiting groove 4.

[0045] In this embodiment, an inner support assembly is further provided in the synchronizer ring 2 and is in radial contact with the inner side of the synchronizer ring 2. In this embodiment, by adding support in the synchronizer ring 2, the deformation difference of the synchronizer ring 2 along the radial direction and the component of the driving force in the radial direction can be effectively reduced, thereby reducing the movement resistance of the mechanism.

[0046] In this embodiment, the limit screw 1 is composed of a threaded section 102, a stop section 101, a first friction section 103 and a mounting section 104. The limit bracket 5 is composed of a second friction section 501, a support section 502 and a second mounting section 503; wherein the second friction section 501 is in an arc shape, and the arc of the second friction section 501 is concentrically arranged with the synchronizer ring 2, and is used to contact and cooperate with the first friction section 103 of the limit screw 1; a positioning step pin 7 is arranged between the second mounting section 503 of the limit bracket 5 and the casing 8, and is connected by a connecting piece, so as to improve the overall stability of the limit bracket 5 and prevent the problem of circumferential sliding.

[0047] Example 2

[0048] See also Figure 1-Figure 6 A method for designing a centering structure of an aircraft engine synchronizer ring 2 is used to obtain the centering structure of the aircraft engine synchronizer ring 2, wherein the centering structure of the aircraft engine synchronizer ring 2 comprises:

[0049] A limit screw 1, wherein the limit screws 1 are multiple in number, and the multiple limit screws 1 are installed on the synchronizer ring 2 through screw holes, and the limit screw 1 is radially arranged along the synchronizer ring 2, and a stop section 101 is arranged on the limit screw 1; a limit block 3, wherein the limit block 3 is arranged on the outer end surface of the synchronizer ring 2; a limit groove 4, wherein the limit groove 4 is arranged on the outer end surface of the synchronizer ring 2, and the circumferential wall surface of the limit groove 4 contacts the limit block 3, and a stop assembly cooperating with the stop section 101 is provided on the limit groove 4, and the stop assembly is used to constrain the self-rotation of the limit screw 1; a limit bracket 5, wherein the limit bracket 5 is installed on the casing 8, and the limit bracket 5 extends to a position where it can radially contact the outer end surface of the limit screw 1. The design method steps include:

[0050] Step 1: According to the design structure of the adjustable stator blade and the synchronizer ring 2 of the aircraft engine, the motion resistance of a single adjustable stator blade connected to the synchronizer ring 2 and the distance between the rotation center of the adjustable stator blade and the center of the upper limit screw 1 of the synchronizer ring 2 are analyzed and obtained.

[0051] Step 2: Analyze and obtain the driving load under the configuration of the adjustable stator blade and the synchronizer ring 2 according to the number of adjustable stator blades connected to the synchronizer ring 2, the motion resistance of a single adjustable stator blade, and the distance between the rotation center of the adjustable stator blade and the center of the upper limit screw 1 of the synchronizer ring 2;

[0052] In this embodiment, the drive load under the configuration of adjustable stator blades and synchronizer ring 2 ,in, is the number of adjustable stator blades connected to the synchronizer ring 2, is the motion resistance of a single adjustable stator blade, is the distance between the rotation center of the adjustable stator blade and the center of the upper limit screw 1 of the synchronizer ring 2, is the number of driven loads.

[0053] Step 3: construct a finite element analysis model including the adjustable stator blade and the synchronizer ring 2, and use the finite element analysis model to analyze and obtain the maximum radial deformation position of the synchronizer ring 2 after the driving load is applied;

[0054] Step 4: a limit bracket 5 and a limit screw 1 matched with the limit bracket 5 are arranged near the maximum radial deformation position, and the maximum radial deformation amount and the new maximum radial deformation position of the synchronizer ring 2 after the driving load is applied are updated by using the finite element analysis model; a stiffness evaluation coefficient of the synchronizer ring 2 under the driving load is obtained according to the maximum radial deformation analysis; if the stiffness evaluation coefficient is greater than or equal to a preset threshold value, it is judged that the stiffness of the synchronizer ring 2 meets the design requirements; otherwise, a limit bracket 5 and a limit screw 1 are added at the new maximum radial deformation position until the stiffness evaluation coefficient of the synchronizer ring 2 under the driving load is greater than or equal to the preset threshold value;

[0055] In this embodiment, the stiffness evaluation coefficient of the synchronizer ring 2 under the driving load is ,in is the diameter of synchronizer ring 2, is the maximum radial deformation of the updated synchronizer ring 2 after the driving load is applied. Carry out structural optimization for the target and define the maximum deformation of synchronizer ring 2 , is the radius of synchronizer ring 2, is the radial dimension of the maximum deformation position; by increasing the external support and carrying out the synchronous ring 2 stiffness assessment, until the synchronous ring 2 stiffness In this embodiment, the number of external supports of the engine synchronizer ring 2 is increased from 0 to 6 (eg Figure 6 As shown in the figure), the stiffness reaches the design target.

[0056] In the present embodiment, by performing stiffness analysis on the synchronizer ring 2 of the aircraft engine adjustment mechanism, the circumferential deformation distribution of the synchronizer ring 2 is obtained, and according to the stiffness deformation distribution result of the synchronizer ring 2, the limit screws 1 can be specifically designed as external supports in the circumference of the synchronizer ring 2, which can reduce the deformation of the synchronizer ring 2 while improving the radial stiffness of the synchronizer ring 2, effectively solve the problem of outward deformation of the synchronizer ring 2, thereby improving the working centering ability and synchronization adjustment accuracy of the synchronizer ring 2.

[0057] The above are only 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 in the protection scope of the present invention.

Claims

1. An aircraft engine synchronizer ring centering structure, characterized in that: include: A limit screw, wherein the number of the limit screws is multiple, and the multiple limit screws are installed on the synchronizer ring through screw holes, the limit screws are arranged along the radial direction of the synchronizer ring, and the limit screws are provided with a stop section; the limit screws are arranged at the maximum radial deformation position of the synchronizer ring with or without the limit screws at other circumferential positions, so that when the number of the limit screws abutting against the synchronizer ring is minimum, the stiffness evaluation coefficient of the synchronizer ring under the driving load is greater than or equal to a preset threshold value; wherein the stiffness evaluation coefficient of the synchronizer ring under the driving load , is the synchronizer ring diameter, is the maximum radial deformation of the synchronizer ring after the driving load is applied; A limit block, the limit block is arranged on the outer end surface of the synchronization ring, the limit block is provided with a stop assembly matched with the stop section, and the stop assembly is used to restrict the rotation of the limit screw; A limiting groove, wherein the limiting groove is arranged on the outer end surface of the synchronization ring, and the circumferential wall surface of the limiting groove is in contact with the limiting block; A limit bracket is installed on the receiver, and the limit bracket extends to a position where it can radially contact the outer end surface of the limit screw.

2. The aircraft engine synchronizer ring centering structure according to claim 1, characterized in that: At least two pin holes are arranged on the limiting block, and the pin holes are respectively located on both sides of the limiting groove, and pins capable of limiting the limiting groove are arranged in the pin holes.

3. The aircraft engine synchronizer ring centering structure according to claim 1, characterized in that: The stop segment is a regular polygonal structure, and the stop component is a regular polygonal hole matched with the stop segment.

4. The aircraft engine synchronizer ring centering structure according to claim 3, characterized in that: The radial clearance adjustment accuracy between the limiting screw and the limiting bracket ,in is the pitch of the limit screw, is the number of polygonal edges of the stop segment of the limit groove.

5. The aircraft engine synchronizer ring centering structure according to claim 1, characterized in that: The limit bracket consists of a second friction section, a support section and a second mounting section; the second friction section is arc-shaped, and the arc of the second friction section is concentrically arranged with the synchronous ring for contacting and cooperating with the limit screw; a positioning step pin is arranged between the second mounting section of the limit bracket and the casing.

6. The aircraft engine synchronizer ring centering structure according to claim 1, characterized in that: An inner support component is also arranged inside the synchronizer ring and is in radial contact with the inner side of the synchronizer ring.

7. A method for designing an aircraft engine synchronizer ring centering structure, used to obtain the aircraft engine synchronizer ring centering structure according to claim 1, characterized in that: include: According to the design structure of the adjustable stator blade and synchronizer ring of the aircraft engine, the motion resistance of a single adjustable stator blade connected to the synchronizer ring and the distance between the rotation center of the adjustable stator blade and the center of the limit screw of the synchronizer ring are analyzed and obtained; According to the number of adjustable stator blades connected to the synchronizer ring, the motion resistance of a single adjustable stator blade, and the distance between the rotation center of the adjustable stator blade and the center of the limit screw of the synchronizer ring, the driving load under the configuration of the adjustable stator blade and the synchronizer ring is analyzed and obtained; Constructing a finite element analysis model including an adjustable stator blade and a synchronizer ring, and using the finite element analysis model to analyze and obtain a maximum radial deformation position of the synchronizer ring after the drive load is applied; A limit bracket and a limit screw cooperating with the limit bracket are arranged near the maximum radial deformation position, and the maximum radial deformation amount and the new maximum radial deformation position of the synchronizer ring after the driving load is applied are updated by using the finite element analysis model. The stiffness evaluation coefficient of the synchronizer ring under the driving load is obtained according to the maximum radial deformation analysis. If the stiffness evaluation coefficient is greater than or equal to a preset threshold value, it is judged that the stiffness of the synchronizer ring meets the design requirements; otherwise, a limit bracket and a limit screw are added at the new maximum radial deformation position until the stiffness evaluation coefficient of the synchronizer ring under the driving load is greater than or equal to the preset threshold value; wherein the stiffness evaluation coefficient of the synchronizer ring under the driving load , is the synchronizer ring diameter, It is the maximum radial deformation of the synchronizer ring after the driving load is applied.

8. The method for designing the centering structure of the synchronizer ring of an aircraft engine according to claim 7, characterized in that: Driving load under adjustable stator blade and synchronizer ring configuration ,in, is the number of adjustable stator blades connected to the synchronizer ring, is the motion resistance of a single adjustable stator blade, is the distance between the rotation center of the adjustable stator blade and the center of the limit screw of the synchronizer ring, is the number of driven loads.

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