A Design Method and System for the Angle of the Oblique and Straight Sections of the Labyrinth Seal Groove of a Turbine Rotor

Abstract

The present invention relates to the field of aero-engine technology, and discloses a method and system for designing the angle of the oblique straight section of the sealing groove of a turbine rotor comb disc. By carrying out deformation simulation analysis of the comb disc and turbine rotor assembly when the throttle lever is quickly pushed up to the test state at an engine slow speed without stopping, the relative sliding distance between the comb disc and the sealing ring and the relative sliding distance between the turbine disc and the sealing ring are obtained; the sealing ring force analysis is carried out to obtain the normal positive pressure load of the sealing ring, and a sealing ring wear analysis model is constructed; finally, the analysis model can be used to analyze and obtain the angle between the oblique straight section of the comb disc sealing groove and the engine axis that meets the sealing ring wear limit value. The analysis model of the present invention comprehensively considers the force and deformation characteristics of the turbine disc and the comb disc during the operation of the aero-engine, and can quickly determine the angle of the oblique straight section of the comb disc sealing groove, effectively avoiding the problem of missing movement wear of the sealing ring during the engine test.

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:

[0006] 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:

[0007] 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;

[0008] Conduct force analysis on the sealing ring under the assessment state to obtain the centrifugal force of the sealing ring under the assessment state;

[0009] 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.

[0010] According to the wear limit value of the seal ring required by the design and the analysis model, the lower limit value of the angle between the straight inclined section of the labyrinth seal groove of the labyrinth disc and the engine axis is obtained through analysis.

[0011] Further, the analysis model is , where is the total wear amount of the seal ring, is the wear coefficient of the seal ring material and the labyrinth disc material, is the first relative sliding distance, is the wear coefficient of the seal ring material and the turbine disc material, is the second relative sliding distance, is the centrifugal force, is the angle between the straight inclined section of the seal groove and the engine axis, is the hardness of the seal ring material.

[0012] Further, the determination methods for the wear coefficient of the seal ring material and the labyrinth disc material and the wear coefficient of the seal ring material and the turbine disc material include:

[0013] Carry out friction and wear tests between the seal ring material and the labyrinth disc material and between the seal ring material and the turbine disc material under different normal positive pressures and different times, and respectively obtain the wear coefficient of the seal ring material and the labyrinth disc material and the wear coefficient of the seal ring material and the turbine disc material.

[0014] Further, the wear limit value of the seal ring is not greater than 50% of the volume of the seal ring.

[0015] To achieve the above technical effects, the present invention also provides a system for designing the angle of the straight inclined section of the labyrinth seal groove of a turbine rotor labyrinth disc, including:

[0016] A simulation analysis module, configured to push the throttle lever of an aeroengine from the idle state to the assessment state within a preset time period, and simulate and analyze to obtain the first relative sliding distance between the labyrinth disc and the seal ring and the second relative sliding distance between the turbine disc and the seal ring;

[0017] A data acquisition module, configured to obtain the centrifugal force of the seal ring in the assessment state according to the force analysis of the seal ring in the assessment state;

[0018] A model construction module, configured to construct an analysis model for the wear amount of the seal ring with the angle between the straight inclined 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;

[0019] A model calculation module, configured to obtain the lower limit value of the angle between the straight inclined section of the labyrinth seal groove of the labyrinth disc and the engine axis through analysis according to the wear limit value of the seal ring required by the design and the analysis model.

[0020] Further, in the model construction module, the constructed analysis model is , where is the total wear amount of the seal ring, is the wear coefficient of the seal ring material and the labyrinth disc material, is the first relative sliding distance, is the wear coefficient of the seal ring material and the turbine disc material, is the second relative sliding distance, is the centrifugal force, is the angle between the inclined straight section of the seal groove and the engine axis, is the hardness of the seal ring material.

[0021] Further, in the model construction module, based on the friction and wear test data between the seal ring material and the labyrinth disc material and between the seal ring material and the turbine disc material under different normal positive pressures and different times, the wear coefficients of the seal ring material and the labyrinth disc material and the wear coefficients of the seal ring material and the turbine disc material are respectively analyzed and obtained.

[0022] Further, in the model calculation module, the limit value of the seal ring wear amount is not greater than 50% of the seal ring volume.

[0023] Compared with the prior art, the beneficial effects of the present invention are as follows: The present invention comprehensively considers the force and deformation characteristics of the turbine disc and the labyrinth disc during the operation of the aeroengine, constructs an analysis model for the wear amount of the seal ring, and can quickly determine the angle of the inclined straight section of the seal groove of the labyrinth disc while satisfying the strength and low-cycle fatigue life of the seal groove of the labyrinth disc, effectively avoiding the problem of missing movement wear of the seal ring during the engine test run. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a flow chart of the design method for the angle of the inclined straight section of the seal groove of the turbine rotor labyrinth disc in Embodiment 1 or 2;

[0025] Figure 2 is a schematic diagram of the positional relationship between the turbine rotor labyrinth disc and the turbine disc in Embodiment 1 or 2;

[0026] Figure 3 is a schematic diagram of the force analysis of the seal ring in Embodiment 1 or 2;

[0027] Figure 4 is a structural block diagram of the design system for the angle of the inclined straight section of the seal groove of the turbine rotor labyrinth disc in Embodiment 1;

[0028] Among them, 1. Seal ring; 2. Labyrinth disc; 3. Turbine disc; 4. Seal groove; 5. Simulation analysis module; 6. Data acquisition module; 7. Model construction module; 8. Model calculation module. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0029] 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.

[0030] Example 1

[0031] See also Figures 1 - 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:

[0032] 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;

[0033] 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;

[0034] 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;

[0035] 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.

[0036] 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.

[0037] Based on the same inventive concept, this embodiment also provides a system for designing the angle of the straight and inclined section of the labyrinth seal groove of a turbine rotor comb tooth disc, including:

[0038] A simulation analysis module 5, configured to push the throttle lever of an aeroengine from the idle state to the assessment state within a preset time period, and perform simulation analysis to obtain the first relative sliding distance between the comb tooth disc 2 and the seal ring 1, and the second relative sliding distance between the turbine disc 3 and the seal ring 1;

[0039] A data acquisition module 6, configured to obtain the centrifugal force of the seal ring 1 in the assessment state according to the force analysis of the seal ring 1 in the assessment state;

[0040] A model construction module 7, configured to construct a wear amount analysis model of the seal ring 1 with the angle between the straight and inclined section of the seal groove 4 and the engine axis, the first relative sliding distance, the second relative sliding distance, and the centrifugal force of the seal ring 1 as independent variables;

[0041] A model calculation module 8, configured to analyze and obtain the lower limit value of the angle between the straight and inclined section of the seal groove 4 of the comb tooth disc 2 and the engine axis according to the wear amount limit value of the seal ring 1 required by the design and the analysis model.

[0042] Embodiment 2

[0043] See Figures 1 - 3 , a method for designing the angle of the straight and inclined section of the labyrinth seal groove of a turbine rotor comb tooth disc, the comb tooth disc 2 and the turbine disc 3 are coaxially arranged, the comb tooth disc 2 is provided with a seal groove 4, and a seal ring 1 is arranged in the seal groove 4; the comb tooth disc 2 and the turbine disc 3 are in clearance fit to press the seal ring 1 in the seal groove 4, and the outer circumferential wall surface of the seal groove 4 in contact with the seal ring 1 is a straight and inclined section; the design method includes:

[0044] Step 1: Push the throttle lever of the aeroengine from the idle state to the assessment state within a preset time period, and perform simulation analysis to obtain the first relative sliding distance between the comb tooth disc 2 and the seal ring 1 , and the second relative sliding distance between the turbine disc 3 and the seal ring 1 ;

[0045] In this embodiment, a deformation simulation analysis of the comb tooth disc 2 and the turbine rotor assembly is carried out when the engine throttle lever is quickly pushed from the idle state to the assessment state without stopping, to obtain the first relative sliding distance between the comb tooth disc 2 and the seal ring 1 and the second relative sliding distance between the turbine disc 3 and the seal ring 1 .

[0046] Step 2: Carry out a force analysis of the seal ring 1 in the assessment state to obtain the centrifugal force of the seal ring 1 in the assessment state;

[0047] In this embodiment, the centrifugal force of the seal ring 1 , where \(m\) is the mass of the seal ring 1, \(r\) is the radius of the centroid of the seal ring 1, and \(n\) is the engine speed under the test condition.

[0048] Step 3: Taking the angle \(\alpha\) between the inclined straight section of the seal groove 4 and the engine axis, the first relative sliding distance \(s_1\), the second relative sliding distance \(s_2\), and the centrifugal force \(F\) of the seal ring 1 as independent variables, construct an analysis model for the wear amount of the seal ring 1;

[0049] In this embodiment, the analysis model is \(W = k_{12}F^{\beta_1}\alpha^{\beta_2} + k_{13}F^{\beta_3}\alpha^{\beta_4} + k_{14}F^{\beta_5}\alpha^{\beta_6}s_1^{\beta_7}s_2^{\beta_8}\), where \(W\) is the total wear amount of the seal ring 1, \(k_{12}\) is the wear coefficient between the material of the seal ring 1 and the material of the labyrinth disc 2, \(k_{13}\) is the wear coefficient between the material of the seal ring 1 and the material of the turbine disc 3, \(F\) is the centrifugal force, \(\alpha\) is the angle between the inclined straight section of the seal groove 4 and the engine axis, and \(H\) is the hardness of the material of the seal ring 1. In this embodiment, the determination methods for the wear coefficient between the material of the seal ring 1 and the material of the labyrinth disc 2 and the wear coefficient between the material of the seal ring 1 and the material of the turbine disc 3 are as follows: By conducting friction and wear tests between the material of the seal ring 1 and the material of the labyrinth disc 2 and between the material of the seal ring 1 and the material of the turbine disc 3 under different normal positive pressures and different times, the wear coefficients between the material of the seal ring 1 and the material of the labyrinth disc 2 and between the material of the seal ring 1 and the material of the turbine disc 3 are obtained respectively.

[0050] Step 4: According to the wear amount limit value of the seal ring 1 required by the design and the above analysis model, analyze and obtain the lower limit value \(\alpha_{min}\) of the angle between the inclined straight section of the seal groove 4 of the labyrinth disc 2 and the engine axis . In this embodiment, in the model calculation module, the wear amount limit value of the seal ring 1 is not greater than 50% of the volume of the seal ring 1.

[0051] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent replacements, and improvements made within the spirit and principles of the present invention shall be included within 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 with 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. ,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, is the hardness of the sealing ring material; 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 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.

3. 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.

4. 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; Model building module, used to build a seal ring wear analysis model with the angle between the 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 ,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, is the hardness of the sealing ring material; 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.

5. The turbine rotor grate plate sealing groove oblique straight section angle design system according to claim 4 is 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.

6. The turbine rotor grate plate sealing groove oblique straight section angle design system according to claim 4, 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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