Temperature measurement lead shaft with axially distributed supporting claws

Abstract

The invention provides a temperature measurement lead shaft with axially-distributed supporting claws, and belongs to the technical field of aero-engines, the temperature measurement lead shaft is fixedly connected with a compressor front journal, the compressor front journal is connected with a compressor first-stage disc, at least one supporting claw is arranged on the temperature measurement lead shaft in the axial direction, a plurality of supporting claws are evenly distributed in the circumferential direction of each supporting claw, and the supporting claws are connected with the compressor first-stage disc. The supporting claws correspond to the centers of the corresponding compressor wheel discs in position, gaps are formed between the supporting claws and the centers of the compressor wheel discs, and during working, under the action of centrifugal force, the outer wall faces of the supporting claws are tightly attached to the centers of the compressor wheel discs. The tail end of the temperature measuring lead shaft is provided with a plurality of wire blocking plates which are evenly distributed in the circumferential direction, the supporting claw corresponds to the center of a last-stage disc of the air compressor in position, and the temperature measuring lead is led out of the tail end of the temperature measuring lead shaft and fixed to the wire blocking plates. According to the processing scheme, the resonance risk of the rotor is effectively avoided, and a powerful guarantee is provided for safe and reliable operation of the test piece.

Description

Technical Field

[0001] The present application relates to the technical field of aerospace engines, and in particular to a temperature measuring lead shaft with axially distributed support claws. Background Art

[0002] Currently, advanced aircraft engines have a large number of compressor stages. The operating temperature of the rotors of the last few stages of compressors is high and their service life is long. Due to the combined effects of the centrifugal force, Coriolis force and inertial force induced by rotation, there are often axial, radial and even multi-directional inflows and outflows, which makes the flow and heat exchange inside the disc cavity extremely complex. Therefore, it is necessary to carry out temperature measurement research on the rotor disc cavity of the last few stages of the compressor.

[0003] When measuring the temperature of the rotor disc cavity in the rear stages of the compressor, thermocouples need to be attached to the rotor disc body of the rear stages. The thermocouple leads need to be led out from the front end of the compressor. In order to secure the leads and ensure effective data transmission, a hollow shaft needs to be inserted and fixed to the hollow shaft. Due to the limitations of the test bench structure, the hollow lead shaft cannot be designed as a simply supported structure with stoppers at both ends. It can only be radially positioned by the stoppers on the front shaft neck of the front compressor stage. The rotor of this structural layout has a long axial dimension and low bending stiffness. It is very easy to bend and deform at high speeds, and there are critical speeds of overall bending or local bending vibration modes within the operating speed range. In rotor dynamics design, it is required that no harmful critical speeds should exist within the operating range. When a critical speed exists within the rotor's operating speed range, there should be at least a certain margin threshold between the operating speed and the critical speed. In the shafting design described above, if it's impossible to move all critical speeds beyond the operating speed, the critical speeds remaining within the operating speed range should be adjusted to the transition speed region, ensuring sufficient margin between each critical speed and the operating speed. Furthermore, the rotor's strain energy must be limited, with the ratio of the rotor's strain energy to the total strain energy not exceeding a certain threshold. Therefore, a new lead shaft structure is needed to ensure that the critical speed and strain energy of the test specimen rotor within the operating speed range meet the requirements, thereby avoiding the risk of rotor resonance that could hinder testing. Summary of the Invention

[0004] In view of this, an embodiment of the present application provides a temperature measurement lead shaft with axially distributed support claws, which at least partially solves the problem of strong vibration caused by over-criticality of the working speed process of the rotor system in the temperature measurement test in the prior art.

[0005] An embodiment of the present application provides a temperature measuring lead shaft with axially distributed support claws, the temperature measuring lead shaft is fixedly connected to the front shaft neck of the compressor, the front shaft neck of the compressor is connected to the first-stage disk of the compressor, at least one support claw is provided in the axial direction of the temperature measuring lead shaft, and a plurality of support claws are evenly distributed in the circumference of each location, the support claws correspond to the positions of the corresponding compressor wheel center, and a gap is provided between the support claws and the compressor wheel center. When working, under the action of centrifugal force, the outer wall surface of the support claw is tightly attached to the wheel center of the compressor; the tail end of the temperature measuring lead shaft is provided with a plurality of wire blocking plates evenly distributed along the circumference, the support claws correspond to the positions of the last-stage disk center of the compressor, and the temperature measuring lead is led out from the tail end of the temperature measuring lead shaft and fixed on the wire blocking plate.

[0006] According to a specific implementation of the embodiment of the present application, the claw body of the supporting claw is arranged at an acute angle to the axial direction of the temperature measuring lead shaft.

[0007] According to a specific implementation method of an embodiment of the present application, a U-shaped groove is opened on the side wall of the tail end of the temperature measuring lead shaft, the axial direction of the U-shaped groove is the same as the axial direction of the temperature measuring lead shaft, and the wire baffle is located on the side of the U-shaped groove.

[0008] According to a specific implementation method of an embodiment of the present application, the support claw is configured as an L-shaped structure, the movable end of the vertical side of the L-shaped structure is connected to the temperature measuring lead shaft, and the horizontal side of the L-shaped structure corresponds to the center of the compressor wheel.

[0009] According to a specific implementation of the embodiment of the present application, the horizontal side of the L-shaped structure is set to be an arc shape.

[0010] According to a specific implementation of an embodiment of the present application, the temperature measuring lead shaft is radially positioned with respect to the front journal of the compressor through two stoppers.

[0011] According to a specific implementation method of an embodiment of the present application, a plurality of positioning pin holes cooperating with radial pins are provided on the circumference of the temperature measuring lead shaft, and the lead shaft is circumferentially positioned with the front shaft neck of the compressor through the radial pins.

[0012] According to a specific implementation method of an embodiment of the present application, a threaded structure is provided at the front end of the temperature measuring lead shaft, and the temperature measuring lead shaft is axially positioned with the shoulder of the front journal of the compressor and is tightened by the cooperation of the nut and the threaded structure.

[0013] According to a specific implementation of the embodiment of the present application, the structural parameters of the support claws are obtained by performing rotor dynamics modeling analysis on the entire rotor system using SAMCEF software.

[0014] According to a specific implementation method of an embodiment of the present application, the structural parameters of the support claw include the arc diameter of the support claw, the vertical edge thickness of the support claw, the horizontal edge thickness of the support claw, the fillet radius of the connection between the vertical edge and the temperature measuring lead axis, the circumferential thickness of the support claw, and the angle of the circumferential distribution of the support claw.

[0015] Beneficial effects:

[0016] The temperature measurement lead shaft with axially distributed support claws in the embodiments of this application is designed without changing the test bench's structural layout. The structural parameters of the support claws can be designed to optimize the dynamic characteristics of the rotor system. By optimizing the support claw stiffness and axial distribution, the critical speed and margin, primarily due to test lead shaft vibration, within the rotor system's operating speed range can meet design requirements, avoiding the risk of rotor resonance and providing a strong guarantee for the safe and reliable operation of the test piece. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without any creative work.

[0018] Figure 1 Schematic diagram of the entire rotor system structure consisting of a temperature measuring lead shaft and other rotor components according to an embodiment of the present invention;

[0019] Figure 2 Schematic diagram of the positioning structure of the temperature measuring lead shaft and the front journal of the compressor according to one embodiment of the present invention;

[0020] Figure 3 A three-dimensional schematic diagram of a circumferential positioning pin hole of a temperature measuring lead shaft according to an embodiment of the present invention;

[0021] Figure 4 A three-dimensional structural diagram of the tail end of a temperature measuring lead shaft according to an embodiment of the present invention;

[0022] Figure 5 A partial cross-sectional view of the tail end of a temperature measuring lead shaft according to an embodiment of the present invention;

[0023] Figure 6 A three-dimensional structural diagram of a supporting claw of a temperature measuring lead shaft according to an embodiment of the present invention;

[0024] Figure 7 for Figure 1 Partial cross-sectional view at point B.

[0025] In the figure: 1-temperature measuring lead shaft, 2-front journal, 3-radial pin, 4-nut, 5-first-level disk, 6-second-level disk, 7-third-level disk, 8-fourth-level disk, 9-fifth-level disk, 10-sixth-level disk, 11-seventh-level disk, 12-eighth-level disk, 13-ninth-level disk, 14-first grate disk, 15-second grate disk, 16-equipment shaft, 111-wire baffle, 112-support claw A, 113-support claw B, 114-support claw C. DETAILED DESCRIPTION

[0026] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0027] The following describes the embodiments of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the features in the following embodiments and embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without making creative work are within the scope of protection of this application.

[0028] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on this application, it should be understood by those skilled in the art that an aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement an apparatus and / or practice a method. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this apparatus and / or practice this method.

[0029] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present application. The illustrations only show components related to the present application and are not drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component can be changed at will, and the component layout type may also be more complicated.

[0030] Additionally, in the following description, specific details are provided to provide a thorough understanding of the examples. However, one skilled in the art will appreciate that the aspects described can be practiced without these specific details.

[0031] The embodiment of the present application provides a temperature measuring lead shaft with axially distributed support claws. Figures 1 to 7 Provide a detailed description.

[0032] In one embodiment, referring to Figure 1 , provides a temperature measuring lead shaft with axially distributed support claws, the temperature measuring lead shaft 1 is fixedly connected to the front shaft neck 2 of the compressor, the front shaft neck 2 of the compressor is connected to the first-stage disk 5 of the compressor, and the temperature measuring lead shaft 1 is provided with at least one support claw in the axial direction, and each support claw is provided with multiple support claws evenly distributed in the circumference, the support claws correspond to the position of the corresponding compressor wheel center, and a gap is provided between the support claws and the compressor wheel center. When working, under the action of centrifugal force, the outer wall surface of the support claw is in close contact with the wheel center of the compressor; the tail end of the temperature measuring lead shaft 1 is provided with multiple wire blocking plates 111 evenly distributed along the circumference, the support claws correspond to the position of the last-stage disk center of the compressor, and the temperature measuring lead is led out from the tail end of the temperature measuring lead shaft 1 and fixed on the wire blocking plate 111.

[0033] This embodiment primarily relates to a connection structure between a temperature-sensing lead shaft 1 with axially distributed support claws and a multi-stage compressor rotor. The temperature-sensing lead shaft 1, the multi-stage compressor rotor, and the equipment shaft 16 constitute the entire rotor system. The entire rotor system includes the temperature-sensing lead shaft 1, a front journal 2, a first-stage disc 5, a second-stage disc 6, a third-stage disc 7, a fourth-stage disc 8, a fifth-stage disc 9, a sixth-stage disc 10, a seventh-stage disc 11, an eighth-stage disc 12, a ninth-stage disc 13, a first grate disc 14, a second grate disc 15, and the equipment shaft 16. The rotor system is supported by three bearings: bearings at the front and rear ends of the compressor rotor and bearings on the equipment shaft 16. The lead shaft is securely assembled by providing support claws below the disc center at the rear end of the lead shaft and the compressor rotor, and by providing a clearance fit between the support claws and the disc center of the compressor rotor. Support claws are evenly distributed along the axial direction of the lead shaft. When the support claws are working, under the action of centrifugal force, the outer wall surface of the support claws is in close contact with the center of the compressor wheel, which can provide radial support for the lead shaft.

[0034] During the specific implementation, SAMCEF software is used to perform rotor dynamics modeling of the entire rotor system, simulate the support stiffness of different support claw structures, obtain the influence of support claws of different structures on the bending stiffness sensitivity of the rotor system, and optimize the dynamic characteristics of the rotor system.

[0035] The lead shaft support scheme was optimized by installing support claws beneath the lead shaft and different compressor wheel centers and adjusting the axial spans of the different support claws. The rotor dynamics modeling of the entire rotor system was performed using SAMCEF software to simulate the support stiffness of different support claw structures. The impact of different support claw structures and axial distributions on the bending stiffness sensitivity of the rotor system was determined, and the optimal support claw structure and distribution were determined.

[0036] In one embodiment, the claw body of the support claw is arranged at an acute angle to the axis of the temperature measuring lead shaft 1. The claw body of the support claw is arranged at an acute angle to the axis of the temperature measuring lead shaft 1, thereby reducing the support stiffness between the support claw and the center of the compressor wheel.

[0037] In one embodiment, referring to Figure 4 and Figure 5 A U-shaped groove is defined on the sidewall of the rear end of the temperature measuring lead shaft 1. The axis of the U-shaped groove is aligned with the axis of the temperature measuring lead shaft 1. A wire blocking plate 111 is located on the side of the U-shaped groove. The circumferential U-shaped groove must have a certain width to ensure the cooling air flow capacity of the entire rotor system.

[0038] In practice, the wire block 111 is used to adhere and secure the temperature measuring lead extending from the front end of the rotor to its surface, preventing the lead from being broken when the rotor rotates. This facilitates extending the thermocouple with the temperature measuring lead into the disk cavity between the eighth-level disk 12 and the ninth-level disk 13 to measure the disk cavity temperature. The temperature measuring lead can be led out through the U-shaped groove.

[0039] Furthermore, in this embodiment, a total of nine-stage disks 13 are provided, the wire blocking plate 111 is provided at a position corresponding to the center of the nine-stage disk, and a support claw A 112 is provided at a position corresponding to the center of the eight-stage disk 12 on the temperature measuring lead shaft 1. Figure 1 As shown in A, the specific structure refers to Figure 4 and Figure 5 The supporting claw A 112 is grooved in the circumferential direction to lead out the temperature measuring lead and stick it on the surface of the supporting claw A 112 to prevent the lead from being broken when the rotor rotates, so as to facilitate extending the thermocouple lead with the temperature measuring lead into the disk cavity between the seventh-level disk 11 and the eighth-level disk 12 to measure the temperature of the disk cavity.

[0040] In this embodiment, the bottom of the U-shaped groove extends to the position where the supporting claw A 112 is located to form the groove structure, so as to facilitate the leading out of the temperature measuring lead.

[0041] In one embodiment, the support claw is configured as an L-shaped structure, the movable end of the vertical side of the L-shaped structure is connected to the temperature measuring lead shaft 1, and the horizontal side of the L-shaped structure corresponds to the center of the compressor wheel.

[0042] When implementing it, refer to Figure 6 The supporting claws can also be set at multiple axial positions of the temperature measuring lead shaft 1 (such as Figure 1A support claw B 113 is provided at position B, and a support claw C 114 is provided at position C. The support claws at each position are evenly distributed along the circumference. The support claws can be configured as an L-shaped structure. To reduce the bearing stiffness between the support claws and the center of the compressor wheel, the L-shaped structure is tilted relative to the temperature measurement lead shaft 1, i.e., the claws are arranged at an acute angle to the axis of the temperature measurement lead shaft 1.

[0043] Preferably, the horizontal side of the L-shaped structure is configured as an arc shape so as to be compatible with the compressor wheel center structure.

[0044] In one embodiment, referring to Figure 2 The temperature measuring lead shaft 1 is radially positioned with the compressor front journal 2 through two stoppers.

[0045] Further, refer to Figure 2 and Figure 3 The temperature measuring lead shaft 1 is provided with a plurality of positioning pin holes which cooperate with the radial pins 3 in the circumferential direction. The lead shaft is positioned circumferentially with the compressor front journal 2 through the radial pins 3 .

[0046] Furthermore, a threaded structure is provided at the front end of the temperature measuring lead shaft 1, and the temperature measuring lead shaft 1 is axially positioned with the shoulder of the compressor front journal 2 and is tightened by the cooperation of the nut 4 and the threaded structure.

[0047] In one embodiment, the structural parameters of the support claws are obtained by performing rotor dynamics modeling analysis on the entire rotor system using SAMCEF software.

[0048] Furthermore, the structural parameters of the support claw include the arc diameter of the support claw, the vertical edge thickness of the support claw, the horizontal edge thickness of the support claw, the fillet radius of the connection between the vertical edge and the temperature measuring lead shaft 1, the circumferential thickness of the support claw, and the circumferential angle of the support claw.

[0049] During the specific implementation, SAMCEF software was used to perform dynamic modeling and analysis on the above-mentioned rotor system. By simulating the support stiffness of different support claw structures, the modal vibration shape, strain energy distribution and critical speed of the rotor system under different support stiffness were obtained. The relationship between different support claw structure parameters and the rotor bending stiffness sensitivity was analyzed to optimize the dynamic characteristics of the rotor system.

[0050] In specific implementation, the structure of the support claw A 112 of the temperature measuring lead shaft 1 is as follows: Figure 5As shown, the supporting claw A 112 has six structural parameters: the claw tip diameter D1 (the diameter of the supporting claw's arc), the claw body thickness t1 (the thickness of the vertical edge of the supporting claw), the claw top thickness h1 (the thickness of the horizontal edge of the supporting claw), the claw base radius R1 (the radius of the radius where the vertical edge connects to the temperature measuring lead shaft 1), the claw circumferential thickness H1, and the angle a1 between the supporting claws. The larger the parameters t1, h1, R1, and H1, and the smaller the parameter a1, the greater the radial stiffness of the supporting claw A 112. By adjusting the values of these five parameters, appropriate support stiffness can be achieved. The basic dimension of parameter D1 is determined by the minimum diameter of the wheel hub to ensure the assemblability of the temperature measuring lead shaft 1.

[0051] The temperature measuring lead shaft 1 is provided with support claws B 113 and support claws C 114 at the center of the other wheel discs. The structure of support claws C 114 is similar to that of support claws B 113. Support claws B 113 (or support claws C 114) are claw-shaped structures uniformly distributed on the outer surface of the temperature measuring lead shaft 1 in the circumferential direction. Figure 6 shown.

[0052] Furthermore, the structure of the support claw B 113 on the temperature measuring lead shaft 1 is as follows: Figure 7 As shown. There are seven structural parameters for support claw B 113: the diameter D2 of the top of the support claw (the diameter of the arc line of the support claw), the thickness t2 of the support claw body (the thickness of the vertical side of the support claw), the thickness h2 of the top of the support claw (the thickness of the horizontal side of the support claw), the fillet R2 at the base of the support claw (the fillet radius at the connection between the vertical side and the temperature measuring lead shaft 1), the angle a2 between the support claw and the centerline of the shaft, the circumferential thickness H2 of the support claw, and the angle b2 between the circumferential distribution of the support claws. The larger the parameters t2, h2, R2, a2, and H2, and the smaller the parameter b2, the greater the radial stiffness of support claw B 113. By adjusting the values of the above six parameters, appropriate support stiffness can be provided. The basic size of parameter D2 is determined by the minimum diameter of the wheel hub to ensure the assemblability of the temperature measuring lead shaft 1. The structural parameter design of support claw C 114 is the same as that of support claw B 113 and will not be repeated here.

[0053] The embodiments provided by this invention design a lead shaft with supporting claws without changing the test bench's structural layout. By designing the structural parameters of the supporting claws, the dynamic characteristics of the rotor system can be optimized. By optimizing the support stiffness and axial distribution of the supporting claws, the critical speed and margin, primarily due to test lead shaft vibration, within the rotor system's operating speed range can be ensured to meet design requirements, thereby avoiding the risk of rotor resonance and providing a strong guarantee for the safe and reliable operation of the test piece.

[0054] The above description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A temperature measuring lead shaft with axially distributed support claws, characterized in that: The temperature measuring lead shaft (1) is fixedly connected to the front shaft neck (2) of the compressor, and the front shaft neck (2) of the compressor is connected to the first stage disk (5) of the compressor. At least one supporting claw is provided in the axial direction of the temperature measuring lead shaft (1), and a plurality of supporting claws are evenly distributed in the circumferential direction of each location. The supporting claws correspond to the positions of the corresponding compressor wheel disc centers, and a gap is provided between the supporting claws and the compressor wheel disc centers. When working, under the action of centrifugal force, the outer wall surface of the supporting claws is tightly attached to the compressor wheel disc center; the tail end of the temperature measuring lead shaft (1) is provided with a plurality of blocking plates (111) evenly distributed along the circumferential direction, and the supporting claws correspond to the positions of the last stage disk center of the compressor. The temperature measuring lead is led out from the tail end of the temperature measuring lead shaft (1) and fixed on the blocking plate (111).

2. The temperature measuring lead shaft with axially distributed support claws according to claim 1, characterized in that: The claw body of the supporting claw is arranged at an acute angle to the axial direction of the temperature measuring lead shaft (1).

3. The temperature measuring lead shaft (1) with axially distributed support claws according to claim 1 is characterized in that: A U-shaped groove is provided on the side wall of the tail end of the temperature measuring lead shaft (1), the axial direction of the U-shaped groove is the same as the axial direction of the temperature measuring lead shaft (1), and the wire blocking plate (111) is located on the side of the U-shaped groove.

4. The temperature measuring lead shaft with axially distributed support claws according to claim 1, characterized in that: The support claw is configured as an L-shaped structure, the movable end of the vertical side of the L-shaped structure is connected to the temperature measuring lead shaft (1), and the horizontal side of the L-shaped structure corresponds to the center of the compressor wheel.

5. The temperature measuring lead shaft (1) with axially distributed support claws according to claim 4 is characterized in that: The horizontal side of the L-shaped structure is set to an arc shape.

6. The temperature measuring lead shaft with axially distributed support claws according to claim 1, characterized in that: The temperature measuring lead shaft (1) is radially positioned with the compressor front journal (2) via two stoppers.

7. The temperature measuring lead shaft with axially distributed support claws according to claim 6, characterized in that: The temperature measuring lead shaft (1) is provided with a plurality of positioning pin holes matched with radial pins (3) in the circumference thereof, and the lead shaft is positioned circumferentially with the compressor front journal (2) through the radial pins (3).

8. The temperature measuring lead shaft with axially distributed support claws according to claim 7, characterized in that: The front end of the temperature measuring lead shaft (1) is provided with a thread structure, and the temperature measuring lead shaft (1) is axially positioned with the shoulder of the compressor front journal (2) and is tightened by the cooperation of the nut (4) and the thread structure.

9. The temperature measuring lead shaft with axially distributed support claws according to claim 5, characterized in that: The structural parameters of the support claws are obtained by performing rotor dynamics modeling analysis on the entire rotor system using SAMCEF software.

10. The temperature measuring lead shaft with axially distributed support claws according to claim 9, characterized in that: The structural parameters of the support claw include the arc diameter of the support claw, the thickness of the vertical side of the support claw, the thickness of the horizontal side of the support claw, the fillet radius of the connection between the vertical side and the temperature measuring lead shaft (1), the circumferential thickness of the support claw, and the angle of the circumferential uniform distribution of the support claw.

Images