Turbine rotor labyrinth disc sealing groove inclined straight section angle design method and system

Abstract

The invention relates to the technical field of aero-engines, and discloses a turbine rotor labyrinth disc sealing groove inclined straight section angle design method and a turbine rotor labyrinth disc sealing groove inclined straight section angle design system. The relative sliding distance between the labyrinth disc and the sealing ring and the relative sliding distance between the turbine disc and the sealing ring are obtained; stress analysis of the sealing ring is carried out, the normal positive pressure load of the sealing ring is obtained, and a sealing ring abrasion loss analysis model is constructed; and finally, the analysis model can be used for analyzing to obtain an included angle between the inclined straight section of the labyrinth disc sealing groove and the axis of the engine, which meets the wear loss limit value of the sealing ring. According to the analysis model, the stress and deformation characteristics of the turbine disc and the labyrinth disc in the working process of the aero-engine are comprehensively considered, the angle of the inclined straight section of the labyrinth disc sealing groove can be rapidly determined, and the problem that in the engine test run process, movement abrasion of a sealing ring is lost is effectively solved.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines and discloses a method and a system for designing the angle of an inclined straight section of a sealing groove of a comb toothed disc of a turbine rotor. Background Art

[0002] The comb disc is a common structural form used in domestic and foreign aircraft engine turbine rotors. It plays a role in guiding cooling air into the inner cavity of the turbine blades and adjusting the axial force of the rotor. In order to prevent cooling air leakage, a sealing groove is usually set at the axial matching surface between the comb disc and the turbine disc rim to install a sealing ring.

[0003] The problem of missing movement wear of the sealing ring was exposed during the engine test. The reason is that the movement wear of the sealing ring mainly depends on the normal positive pressure of the sealing ring and the sliding distance of the contact surface. During the engine test, due to the inconsistent thermal response of the comb disc and the turbine disc, there is radial reciprocating motion, and the sliding distance of the contact surface cannot be avoided. Therefore, how to reduce the normal positive pressure of the sealing ring becomes the key to the problem. In the prior art, it is often achieved by adjusting the angle of the oblique straight section of the comb disc sealing groove, but there is no method for determining the oblique straight section angle. Summary of the invention

[0004] The purpose of the present invention is to provide a method and system for designing the oblique straight section angle of the comb disc sealing groove of a turbine rotor, which can quickly determine the oblique straight section angle of the comb disc sealing groove that meets the comb disc sealing groove strength and low cycle fatigue life, and effectively avoid the problem of sealing ring movement wear and tear during engine testing.

[0005] In order to achieve the above technical effects, the technical solution adopted by the present invention is: A method for designing the angle of the oblique straight section of the sealing groove of a turbine rotor grate disc, wherein the grate disc is coaxially arranged with a turbine disc, a sealing groove is provided on the grate disc, and a sealing ring is arranged in the sealing groove; the grate disc and the turbine disc are clearance-matched to press the sealing ring in the sealing groove, and the outer circumferential wall surface of the sealing groove in contact with the sealing ring is an oblique straight section; the design method comprises: Push the throttle lever of the aircraft engine from the slow-speed state to the test state within a preset time period, and obtain the first relative sliding distance between the comb plate and the sealing ring, and the second relative sliding distance between the turbine plate and the sealing ring through simulation analysis; Conduct force analysis on the sealing ring under the assessment state to obtain the centrifugal force of the sealing ring under the assessment state; The wear analysis model of the sealing ring is constructed by taking the angle between the oblique straight section of the sealing groove and the engine axis, the first relative sliding distance, the second relative sliding distance and the centrifugal force of the sealing ring as independent variables. According to the sealing ring wear limit value required by the design and the analysis model, the lower limit value of the angle between the oblique straight section of the comb tooth plate sealing groove and the engine axis is analyzed and obtained.

[0006] Furthermore, the analysis model is ,in is the total wear of the sealing ring, is the wear coefficient of the sealing ring material and the comb disc material, is the first relative sliding distance, is the wear coefficient of the sealing ring material and the turbine disk material, is the second relative sliding distance, is the centrifugal force, is the angle between the oblique straight section of the sealing groove and the engine axis, It is the hardness of the sealing ring material.

[0007] Furthermore, the method for determining the wear coefficient of the sealing ring material and the comb disc material, and the wear coefficient of the sealing ring material and the turbine disc material includes: Friction and wear tests were carried out between the sealing ring material and the comb disk material, as well as between the sealing ring material and the turbine disk material under different normal positive pressures and at different times, and the wear coefficients of the sealing ring material and the comb disk material, as well as the wear coefficients of the sealing ring material and the turbine disk material were obtained respectively.

[0008] Furthermore, the wear limit value of the sealing ring is no more than 50% of the volume of the sealing ring.

[0009] In order to achieve the above technical effects, the present invention also provides a turbine rotor grate disc sealing groove oblique straight section angle design system, comprising: A simulation analysis module is used to push the throttle lever of the aircraft engine from the slow-speed state to the test state within a preset time period, and to obtain the first relative sliding distance between the comb tooth plate and the sealing ring, and the second relative sliding distance between the turbine plate and the sealing ring through simulation analysis; A data acquisition module is used to obtain the centrifugal force of the sealing ring under the assessment state according to the force analysis of the sealing ring under the assessment state; A model building module is used to build a seal ring wear analysis model using the angle between the oblique straight section of the seal groove and the engine axis, the first relative sliding distance, the second relative sliding distance, and the centrifugal force of the seal ring as independent variables; The model calculation module is used to analyze and obtain the lower limit value of the angle between the oblique straight section of the comb tooth plate sealing groove and the engine axis according to the sealing ring wear limit value required by the design and the analysis model.

[0010] Furthermore, in the model building module, the analysis model constructed is ,in is the total wear of the sealing ring, is the wear coefficient of the sealing ring material and the comb disc material, is the first relative sliding distance, is the wear coefficient of the sealing ring material and the turbine disk material, is the second relative sliding distance, is the centrifugal force, is the angle between the oblique straight section of the sealing groove and the engine axis, It is the hardness of the sealing ring material.

[0011] Furthermore, in the model building module, based on the friction and wear test data between the sealing ring material and the comb disk material and between the sealing ring material and the turbine disk material under different normal positive pressures and at different times, the wear coefficients of the sealing ring material and the comb disk material and the wear coefficients of the sealing ring material and the turbine disk material are respectively analyzed and obtained.

[0012] Furthermore, in the model calculation module, the wear limit value of the sealing ring is no more than 50% of the volume of the sealing ring.

[0013] Compared with the prior art, the beneficial effects of the present invention are as follows: the present invention comprehensively considers the stress and deformation characteristics of the turbine disc and the comb disc during the operation of the aircraft engine, constructs a sealing ring wear analysis model, and can quickly determine the angle of the oblique straight section of the comb disc sealing groove while meeting the strength and low cycle fatigue life of the comb disc sealing groove, thereby effectively avoiding the problem of sealing ring movement wear and loss during engine testing. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 The flowchart of the method for designing the angle of the oblique straight section of the sealing groove of the turbine rotor grate disc in Example 1 or 2; Figure 2 Schematic diagram of the positional relationship between the turbine rotor grate disc and the turbine disc in Example 1 or 2; Figure 3 It is a schematic diagram of the force analysis of the sealing ring in Example 1 or 2; Figure 4 The structural block diagram of the system for designing the angle of the straight section of the sealing groove of the turbine rotor grate disc in Example 1; Among them, 1. Sealing ring; 2. Comb disc; 3. Turbine disc; 4. Sealing groove; 5. Simulation analysis module; 6. Data acquisition module; 7. Model construction module; 8. Model calculation module. DETAILED DESCRIPTION

[0015] 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.

[0016] Example 1 See also Figure 1-Figure 4, a method for designing the angle of the oblique straight section of the sealing groove of a turbine rotor comb disc, wherein the comb disc 2 is coaxially arranged with a turbine disc 3, a sealing groove 4 is provided on the comb disc 2, and a sealing ring 1 is arranged in the sealing groove 4; the comb disc 2 and the turbine disc 3 are clearance-matched to press the sealing ring 1 into the sealing groove 4, and the outer circumferential wall surface of the sealing groove 4 in contact with the sealing ring 1 is an oblique straight section; the design method comprises: The throttle lever of the aircraft engine is pushed from the slow-speed state to the test state within a preset time period, and the first relative sliding distance between the comb plate 2 and the sealing ring 1, and the second relative sliding distance between the turbine plate 3 and the sealing ring 1 are obtained by simulation analysis; Conduct force analysis on the sealing ring 1 under the assessment state to obtain the centrifugal force of the sealing ring 1 under the assessment state; The wear analysis model of the sealing ring 1 is constructed by taking the angle between the oblique straight section of the sealing groove 4 and the engine axis, the first relative sliding distance, the second relative sliding distance and the centrifugal force of the sealing ring 1 as independent variables; According to the design requirement of the wear limit value of the sealing ring 1 and the analysis model, the lower limit value of the angle between the oblique straight section of the sealing groove 4 of the comb tooth plate 2 and the engine axis is analyzed and obtained.

[0017] In this embodiment, by carrying out deformation simulation analysis of the comb disc 2 and the turbine rotor assembly when the throttle lever is quickly pushed up to the test state at slow engine speed without stopping, the first relative sliding distance between the comb disc 2 and the sealing ring 1, and the second relative sliding distance between the turbine disc 3 and the sealing ring 1 are obtained; the force analysis of the sealing ring 1 is carried out to obtain the normal positive pressure load of the sealing ring 1, and the wear analysis model of the sealing ring 1 based on the first relative sliding distance, the second relative sliding distance, and the centrifugal force of the sealing ring 1 is constructed; finally, the angle between the oblique straight section of the sealing groove 4 of the comb disc 2 and the engine axis that meets the wear limit value of the sealing ring 1 can be obtained by analyzing the analysis model. The present invention comprehensively considers the force and deformation characteristics of the turbine disc 3 and the comb disc 2 during the operation of the aircraft engine, and constructs the wear analysis model of the sealing ring 1. While meeting the strength and low cycle fatigue life of the sealing groove 4 of the comb disc 2, the oblique straight section angle of the sealing groove 4 of the comb disc 2 can be quickly determined, effectively avoiding the problem of missing movement wear of the sealing ring 1 during the engine test.

[0018] Based on the same inventive concept, this embodiment also provides a turbine rotor grate disc sealing groove oblique straight section angle design system, including: The simulation analysis module 5 is used to push the throttle lever of the aircraft engine from the slow-speed state to the test state within a preset time period, and to obtain the first relative sliding distance between the comb tooth plate 2 and the sealing ring 1 and the second relative sliding distance between the turbine plate 3 and the sealing ring 1 through simulation analysis; The data acquisition module 6 is used to obtain the centrifugal force of the sealing ring 1 under the assessment state according to the force analysis of the sealing ring 1 under the assessment state; The model building module 7 is used to build a wear analysis model of the sealing ring 1 by taking the angle between the oblique straight section of the sealing groove 4 and the engine axis, the first relative sliding distance, the second relative sliding distance and the centrifugal force of the sealing ring 1 as independent variables; The model calculation module 8 is used to analyze and obtain the lower limit of the angle between the oblique straight section of the sealing groove 4 of the comb tooth plate 2 and the engine axis according to the wear limit value of the sealing ring 1 required by the design and the analysis model.

[0019] Example 2 See also Figure 1-Figure 3 , a method for designing the angle of the oblique straight section of the sealing groove of a turbine rotor comb disc, wherein the comb disc 2 is coaxially arranged with a turbine disc 3, a sealing groove 4 is provided on the comb disc 2, and a sealing ring 1 is arranged in the sealing groove 4; the comb disc 2 and the turbine disc 3 are clearance-matched to press the sealing ring 1 into the sealing groove 4, and the outer circumferential wall surface of the sealing groove 4 in contact with the sealing ring 1 is an oblique straight section; the design method comprises: Step 1: Push the throttle lever of the aircraft engine from the slow-speed state to the test state within the preset time period, and obtain the first relative sliding distance between the comb tooth plate 2 and the sealing ring 1 through simulation analysis. , and the second relative sliding distance between the turbine disk 3 and the sealing ring 1 ; In this embodiment, a deformation simulation analysis of the comb disc 2 and the turbine rotor assembly is carried out when the throttle lever is quickly pushed up to the test state at an engine slow speed without stopping, and the first relative sliding distance between the comb disc 2 and the sealing ring 1 is obtained. The second relative sliding distance between the turbine disk 3 and the sealing ring 1 .

[0020] Step 2: Conduct force analysis on the sealing ring 1 under the assessment state to obtain the centrifugal force of the sealing ring 1 under the assessment state; In this embodiment, the centrifugal force of the sealing ring 1 , is the mass of sealing ring 1, is the centroid radius of sealing circle 1, It is the engine speed under the test status.

[0021] Step 3: The angle between the oblique straight section of the sealing groove 4 and the engine axis , the first relative sliding distance , the second relative sliding distance And the centrifugal force of the sealing ring 1 As the independent variable, the wear analysis model of sealing ring 1 is constructed; In this embodiment, the analysis model is ,in is the total wear of sealing ring 1, is the wear coefficient of the sealing ring 1 material and the comb tooth plate 2 material, is the wear coefficient of the sealing ring 1 material and the turbine disk 3 material, is the centrifugal force, is the angle between the oblique straight section of the sealing groove 4 and the engine axis, is the hardness of the material of the sealing ring 1. In this embodiment, the wear coefficient of the sealing ring 1 material and the comb tooth disk 2 material, and the wear coefficient of the sealing ring 1 material and the turbine disk 3 material are determined by conducting friction and wear tests between the sealing ring 1 material and the comb tooth disk 2 material and between the sealing ring 1 material and the turbine disk 3 material under different normal positive pressures and different times, and obtaining the wear coefficient of the sealing ring 1 material and the comb tooth disk 2 material and the wear coefficient of the sealing ring 1 material and the turbine disk 3 material respectively.

[0022] Step 4: According to the design requirements of the wear limit value of the sealing ring 1 and the analysis model, the lower limit value of the angle between the oblique straight section of the sealing groove 4 of the comb tooth plate 2 and the engine axis is obtained by analysis. In this embodiment, in the model calculation module, the wear limit value of the sealing ring 1 is no more than 50% of the volume of the sealing ring 1.

[0023] 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. A method for designing the angle of the oblique straight section of the sealing groove of a turbine rotor comb disc, wherein the comb disc is coaxially arranged with the turbine disc, a sealing groove is provided on the comb disc, and a sealing ring is arranged in the sealing groove; the comb disc and the turbine disc are clearance-matched to press the sealing ring into the sealing groove, and the outer circumferential wall surface of the sealing groove in contact with the sealing ring is an oblique straight section; characterized in that, The design method comprises: Push the throttle lever of the aircraft engine from the slow-speed state to the test state within a preset time period, and obtain the first relative sliding distance between the comb plate and the sealing ring, and the second relative sliding distance between the turbine plate and the sealing ring through simulation analysis; Conduct force analysis on the sealing ring under the assessment state to obtain the centrifugal force of the sealing ring under the assessment state; The wear analysis model of the sealing ring is constructed by taking the angle between the oblique straight section of the sealing groove and the engine axis, the first relative sliding distance, the second relative sliding distance and the centrifugal force of the sealing ring as independent variables. According to the sealing ring wear limit value required by the design and the analysis model, the lower limit value of the angle between the oblique straight section of the comb tooth plate sealing groove and the engine axis is analyzed and obtained.

2. The method for designing the angle of the straight section of the sealing groove of the turbine rotor grate disc according to claim 1 is characterized in that: The analysis model is ,in is the total wear of the sealing ring, is the wear coefficient of the sealing ring material and the comb disc material, is the first relative sliding distance, is the wear coefficient of the sealing ring material and the turbine disk material, is the second relative sliding distance, is the centrifugal force, is the angle between the oblique straight section of the sealing groove and the engine axis, It is the hardness of the sealing ring material.

3. The method for designing the angle of the straight section of the sealing groove of the turbine rotor grate disc according to claim 2 is characterized in that: The method for determining the wear coefficient of the sealing ring material and the comb disc material, and the wear coefficient of the sealing ring material and the turbine disc material includes: Friction and wear tests were carried out between the sealing ring material and the comb disk material, as well as between the sealing ring material and the turbine disk material under different normal positive pressures and at different times, and the wear coefficients of the sealing ring material and the comb disk material, as well as the wear coefficients of the sealing ring material and the turbine disk material were obtained respectively.

4. The method for designing the angle of the straight section of the sealing groove of the turbine rotor grate disc according to claim 1 is characterized in that: The wear limit of the sealing ring is no more than 50% of the volume of the sealing ring.

5. A turbine rotor grate disc sealing groove straight section angle design system, characterized in that: include: A simulation analysis module is used to push the throttle lever of the aircraft engine from the slow-speed state to the test state within a preset time period, and to obtain the first relative sliding distance between the comb tooth plate and the sealing ring, and the second relative sliding distance between the turbine plate and the sealing ring through simulation analysis; A data acquisition module is used to obtain the centrifugal force of the sealing ring under the assessment state according to the force analysis of the sealing ring under the assessment state; A model building module is used to build a seal ring wear analysis model using the angle between the oblique straight section of the seal groove and the engine axis, the first relative sliding distance, the second relative sliding distance, and the centrifugal force of the seal ring as independent variables; The model calculation module is used to analyze and obtain the lower limit value of the angle between the oblique straight section of the comb tooth plate sealing groove and the engine axis according to the sealing ring wear limit value required by the design and the analysis model.

6. The turbine rotor grate plate sealing groove oblique straight section angle design system according to claim 5, characterized in that: In the model building module, the analysis model constructed is ,in is the total wear of the sealing ring, is the wear coefficient of the sealing ring material and the comb disc material, is the first relative sliding distance, is the wear coefficient of the sealing ring material and the turbine disk material, is the second relative sliding distance, is the centrifugal force, is the angle between the oblique straight section of the sealing groove and the engine axis, It is the hardness of the sealing ring material.

7. The turbine rotor grate plate sealing groove oblique straight section angle design system according to claim 6, characterized in that: In the model building module, according to the friction and wear test data between the sealing ring material and the comb disk material and between the sealing ring material and the turbine disk material under different normal positive pressures and different times, the wear coefficients of the sealing ring material and the comb disk material and the wear coefficients of the sealing ring material and the turbine disk material are respectively analyzed and obtained.

8. The turbine rotor grate plate sealing groove oblique straight section angle design system according to claim 6, characterized in that: In the model calculation module, the wear limit value of the sealing ring is no more than 50% of the volume of the sealing ring.

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