CN106837426B - Method for optimizing eccentricity of mass center of rotor of engine core machine - Google Patents
Method for optimizing eccentricity of mass center of rotor of engine core machine Download PDFInfo
- Publication number
- CN106837426B CN106837426B CN201710084586.8A CN201710084586A CN106837426B CN 106837426 B CN106837426 B CN 106837426B CN 201710084586 A CN201710084586 A CN 201710084586A CN 106837426 B CN106837426 B CN 106837426B
- Authority
- CN
- China
- Prior art keywords
- rotor
- eccentricity
- pressure turbine
- core machine
- cylindrical surface
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/10—Anti- vibration means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/668—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
Abstract
The invention discloses an optimization method for the eccentricity of the mass center of a rotor of an engine core machine. The method for optimizing the eccentricity of the mass center of the rotor of the engine core machine comprises the following steps: step 1: taking the minimum value of the centroid eccentricity OC of the core engine rotor connecting surface as the optimization target of the optimization method of the centroid eccentricity of the engine core engine rotor; step 2: establishing a core machine rotor mass center eccentricity prediction optimization mathematical model; and step 3: and solving a theta value corresponding to the minimum deviation of the fitted centroid O of the labyrinth disc from the actual rotation axis OC of the core machine rotor, and performing angular rotation assembly on the high-pressure turbine rotor and the high-pressure compressor rotor according to the theta value. According to the optimization method for the eccentricity of the mass center of the rotor of the engine core machine, before the rotor is assembled, the rotor of the core machine is guided to be assembled by selecting the corresponding angular phase when the OC value is minimum through optimization calculation, so that the eccentricity of the mass center of the rotor of the core machine is reduced, the unbalance amount of the rotor of the core machine is reduced, and the vibration of a high-pressure rotor is improved.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to an optimization method for the eccentricity of the mass center of a rotor of an engine core machine.
Background
The unbalance amount of the aeroengine core rotor is an important factor for determining the vibration response of the engine rotor, and the root cause of the unbalance amount is that each discrete rotor center of mass deviates from the actual rotation axis. A core machine rotor is formed by assembling a balanced high-pressure compressor rotor (HPC) and a high-pressure turbine rotor (HPT) through self-locking bolts/nuts. Through calculation, when the eccentricity of the mass center of the rotor of the core machine is 0.01mm and the rotating speed is 12000r/min, the centrifugal force of about 400kg can be generated, and the centrifugal force of the order of magnitude breaks the balance state of the rotor, so that the high-pressure rotor vibrates.
Referring to fig. 1, theoretically, the mass center of the balanced high-pressure compressor rotor is distributed on a connecting line AO between a front journal fitting centroid a and a labyrinth plate fitting centroid O, and the mass center of the balanced high-pressure turbine rotor is distributed on a connecting line OB between the labyrinth plate fitting centroid O and a rear journal fitting centroid B. Therefore, in the process of assembling the high-pressure compressor rotor and the high-pressure turbine rotor into the core machine rotor, an effective process method is adopted to control the value OC of the fit centroid O of the labyrinth disc deviating from the actual rotation axis AB to be as small as possible, so that the eccentricity of the mass center of the core machine rotor can be reduced, the unbalance amount of the rotor can be reduced, the distribution of the unbalance amount can be improved, and the frequency of the high-pressure rotor exceeding the vibration limit can be effectively reduced.
Aiming at the core machine rotor with the structure, the existing core machine rotor assembly process mainly comprises the following two schemes: (1) jump cancellation assembly principle. The method is characterized in that the runout of corresponding cylindrical surfaces of a compressor rotor and a high-vortex rotor is measured respectively under the condition of simulating the balance state of the rotor, the highest runout point of the compressor rotor and the high-vortex rotor is exchanged for 180 degrees, and then the rotor is assembled. (2) The amount of unbalance offsets the assembly principle. Namely, the two rotors are respectively balanced, and finally the rotors are assembled after the unbalance measurement phases are exchanged for 180 degrees. After the core machine rotor is assembled by the two methods, a special measuring tool is adopted to measure the value of OC (the measuring tool is fixed with the circumferential installation edge of the stator casing and can simulate an actual rotating shaft AB), the value is used as an important process parameter to be controlled, and if OC is out of tolerance, the two high-pressure rotors are assembled again in a decomposition-rotating phase-trial mode.
Although the core machine rotor assembling process is feasible, the controllability of the OC value serving as a key process parameter is poor, repeated assembly caused by the OC retest out-of-tolerance in the transmission and assembly process is easily caused, high-pressure vibration caused by overlarge eccentricity of the mass center of the core machine rotor is also generated occasionally, the assembling efficiency is low, the manufacturing cost of an engine is indirectly improved, and the problems that the inherent vibration performance of the existing structure of a machine part cannot be dug in place in the process and the like exist.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present invention to provide a method of optimising the eccentricity of the centre of mass of a rotor of an engine core which overcomes or at least mitigates at least one of the above-mentioned disadvantages of the prior art.
In order to achieve the above object, the present invention provides a method for optimizing the eccentricity of the center of mass of a rotor of an engine core, comprising the steps of:
step 1: acquiring the cylindrical surface eccentricity of a rear shaft neck after the high-pressure compressor rotor and the high-pressure turbine rotor are assembled at any rotation angle phase theta, and further solving the BE value; BE is the cylindrical surface eccentricity at the rear journal of the core machine rotor with the front journal as the reference;
step 2: before the core machine rotor is assembled, keeping the high-pressure compressor rotor still, rotating the high-pressure turbine rotor in a unidirectional mode, and enabling the phase position theta of a rotating angle to be an integral multiple value of 360 DEG/n, wherein n is the number of connecting bolts on a connecting surface, calculating the actual rotating axis AB distance OC formed by connecting a cylindrical surface fitting centroid O of a rear spigot of a 9-stage grate disc to a front supporting point and a rear supporting point one by one, and taking the minimum possible value of the OC as the optimization target of the optimization method of the mass center eccentricity of the core machine rotor of the engine;
and step 3: establishing a core machine rotor mass center eccentricity prediction optimization mathematical model;
and 4, step 4: and 3, according to the core machine rotor mass center eccentricity prediction optimization mathematical model in the step 3, calculating a rotation angle phase theta value corresponding to the minimum distance OC between the actual rotation axis AB formed by connecting lines of the centroid O, the front supporting point and the rear supporting point of the cylindrical surface fitting of the rear spigot of the 9-stage labyrinth plate and carrying out angular rotation assembly on the high-pressure turbine rotor and the high-pressure compressor rotor according to the rotation angle phase theta value.
Preferably, the step 1 specifically includes:
step 11: obtaining the axial length AD of the front supporting point section fitting centroids A to 9 stages of grate tooth discs and the corresponding end surface D of the drum shaft matching spigot of the high-pressure turbine rotor assembly;
step 12: obtaining the axial length DE of the end surfaces corresponding to the fit spigot of the section fitting centroids B to 9 of the supporting points and the drum shaft of the high-pressure turbine rotor assembly;
step 13: measuring a jumping parameter of a rotor assembly of the high-pressure compressor;
step 14: measuring a high-pressure turbine rotor runout parameter;
step 15: acquiring a comprehensive eccentric formula at the rear shaft neck of a core machine rotor after a high-pressure compressor rotor assembly and a high-pressure turbine rotor assembly are assembled;
step 16: and (5) taking the parameters obtained in the steps 11 to 14 as input, and calculating to obtain the cylindrical surface eccentricity at the rear shaft neck after the high-pressure compressor rotor and the high-pressure turbine rotor are assembled at any rotation angle phase theta by means of the comprehensive eccentricity formula in the step 15.
Preferably, the step 13 specifically includes: on the stacking optimization equipment, a cylindrical surface and a shaft shoulder end surface at the position of a front pivot bearing inner ring installed on a front shaft neck of a high-pressure compressor rotor assembly are taken as references to measure cylindrical surface eccentricity delta of a matching spigot of a 9-stage labyrinth disc and a high-pressure turbine rotor assembly drum shaftcenter1And the end surface eccentricity delta of the matched spigot of the 9-stage grate toothed disc and the drum shaft of the high-pressure turbine rotor assemblytlit。
Preferably, the step 14 specifically includes: on the stacking optimization equipment, the cylindrical surface S and the end surface T corresponding to the matching seam allowance of the drum shaft of the high-pressure turbine rotor assembly and the 9-stage grate disc are used as references, and the cylindrical surface eccentricity delta at the position of the rear supporting point bearing outer ring arranged on the rear shaft neck is measuredcenter3。
Preferably, the comprehensive eccentricity formula in step 15 is specifically:
δcenterthe comprehensive eccentricity of a rear journal bearing fulcrum is based on a front journal of a rotor of a core machine;
δcenter2＝H*δtilt/(d/2)，δcenter2is deltatiltInfluence on the cylindrical surface eccentricity of a rear journal of the core machine;
h is the axial dimension from the front end surface of a drum shaft of the high-pressure turbine rotor assembly to a rear journal bearing fulcrum;
d is the diameter of the matched cylindrical surface of the rear spigot of the nine-stage labyrinth plate of the high-pressure compressor.
Preferably, the step 16 is specifically: at deltacenter1、δtlitAnd delta measured in step 14center3For input, the cylindrical surface eccentricity at the rear shaft neck after the compressor rotor and the high-pressure turbine rotor are assembled at any rotation angle phase theta can be obtained through calculation.
Preferably, the core machine rotor centroid eccentricity prediction optimization mathematical model in the step 3 is as follows:wherein the content of the first and second substances,
CD (BE) AD/(AD + DE) ACD is similar to △ ABE according to △;
BE: the cylindrical surface eccentricity of the rear journal of the core machine rotor with the front journal as the reference can be obtained according to the method in the step 1;
AD: axial lengths of end faces D corresponding to matched spigots of front support point section fitting centroids A to 9 stages of grate tooth discs and high-pressure turbine rotor assembly drum shafts can be obtained according to the method in the step 11;
DE: axial lengths of end faces corresponding to matched spigots of rear fulcrum section fitting centroids B to 9 stages of grate tooth discs and high-pressure turbine rotor assembly drum shafts can be obtained according to the method in the step 12;
theta is a rotation angle phase of the high-pressure turbine rotor in rotating assembly relative to the high-pressure compressor rotor.
According to the optimization method for the eccentricity of the mass center of the rotor of the engine core machine, before the rotor is assembled, the angular phase with the minimum OC value is selected through optimization calculation to guide the assembly of the rotor of the core machine, so that the purposes of reducing the eccentricity of the mass center of the rotor of the core machine, reducing the unbalance amount of the rotor of the core machine and improving the vibration of a high-pressure rotor are indirectly achieved.
The method realizes the optimization of the fitted centroid eccentricity of the rear spigot of the slotted disk of the core machine rotor before assembly, indirectly controls the centroid eccentricity of the rotor, improves the success rate of one-time assembly and reduces the assembly manufacturing cost;
the method can excavate the maximum value of the internal vibration performance of the existing machine part, and reduce and improve the vibration of the high-pressure rotor;
with the mature application of the method, the retest after assembly can be omitted in the process, and the development cost is effectively reduced.
Drawings
FIG. 1 is a schematic structural diagram of a conventional core engine rotor employing a post-assembly retest technique.
FIG. 2 is a schematic flow chart of a method for optimizing eccentricity of a center of mass of a rotor of an engine core according to an embodiment of the present application.
FIG. 3 is a schematic diagram of a compressor rotor assembly runout parameter measurement of the method for optimizing the eccentricity of the center of mass of the engine core rotor shown in FIG. 2.
FIG. 4 is a schematic diagram of a measurement of a high pressure turbine rotor assembly runout parameter of the method for optimizing eccentricity of a center of mass of an engine core rotor shown in FIG. 2.
FIG. 5 is a schematic illustration of the rotor eccentricity stacking principle of the method for optimizing the eccentricity of the center of mass of the rotor of the engine core shown in FIG. 2.
FIG. 6 is another schematic illustration of the rotor eccentricity stacking principle of the method for optimizing the eccentricity of the center of mass of the rotor of the engine core shown in FIG. 2.
FIG. 7 is a schematic illustration of a mathematical model for core rotor center-of-mass eccentricity prediction optimization of the method for optimizing engine core rotor center-of-mass eccentricity illustrated in FIG. 2.
Reference numerals:
| 1 | high-pressure compressor rotor | 6 | Rear |
| 2 | High-pressure turbine rotor | 7 | |
| 3 | 9-stage grate disc | 8 | |
| 4 | Front pivot mounting position | 9 | |
| 5 | Front axle journal |
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
FIG. 2 is a schematic flow chart of a method for optimizing eccentricity of a center of mass of a rotor of an engine core according to an embodiment of the present application. FIG. 3 is a schematic diagram of a compressor rotor assembly runout parameter measurement of the method for optimizing the eccentricity of the center of mass of the engine core rotor shown in FIG. 2. FIG. 4 is a schematic diagram of a measurement of a high pressure turbine rotor assembly runout parameter of the method for optimizing eccentricity of a center of mass of an engine core rotor shown in FIG. 2. FIG. 5 is a schematic illustration of the rotor eccentricity stacking principle of the method for optimizing the eccentricity of the center of mass of the rotor of the engine core shown in FIG. 2. FIG. 6 is another schematic illustration of the rotor eccentricity stacking principle of the method for optimizing the eccentricity of the center of mass of the rotor of the engine core shown in FIG. 2. FIG. 7 is a schematic illustration of a mathematical model for core rotor center-of-mass eccentricity prediction optimization of the method for optimizing engine core rotor center-of-mass eccentricity illustrated in FIG. 2.
The method for optimizing the eccentricity of the center of mass of the rotor of the engine core machine shown in FIG. 2 comprises the following steps:
step 1: obtaining the cylindrical surface eccentricity of a rear shaft neck after the compressor rotor and the high-pressure turbine rotor are assembled at any rotation angle phase theta, and further solving the BE value; BE is the cylindrical surface eccentricity at the rear journal of the core machine rotor with the front journal as the reference;
step 2: before the core machine rotor is assembled, keeping the compressor rotor still, rotating the high-pressure turbine rotor in a unidirectional mode, and enabling the phase theta of a rotating angle to be an integral multiple value of 360 DEG/n, wherein n is the number of connecting bolts on a connecting surface, calculating the actual rotating axis AB distance OC formed by connecting a cylindrical surface fitting centroid O of a rear spigot of a 9-stage labyrinth disc to a front supporting point and a rear supporting point one by one, and taking the minimum possible value of the OC as the optimization target of the optimization method of the mass center eccentricity of the engine core machine rotor;
and step 3: establishing a core machine rotor mass center eccentricity prediction optimization mathematical model;
and 4, step 4: and 3, according to the core machine rotor mass center eccentricity prediction optimization mathematical model in the step 3, calculating a rotation angle phase theta value corresponding to the minimum distance OC between the actual rotation axis AB formed by connecting lines of the centroid O, the front supporting point and the rear supporting point of the cylindrical surface fitting of the rear spigot of the 9-stage labyrinth plate and carrying out angular rotation assembly on the high-pressure turbine rotor and the high-pressure compressor rotor according to the rotation angle phase theta value.
In this embodiment, step 1 specifically includes: step 11: obtaining the axial length AD of the end face corresponding to the fitting centroids A to 9 of the sections of the front supporting points and the drum shaft matching spigot D of the high-pressure turbine rotor assembly; specifically, the axial length AD of the front-supporting-point section fitting centroids A to 9 stages of grate discs and the corresponding end faces of the drum shaft matching spigot of the high-pressure turbine rotor assembly can be checked by checking a high-pressure compressor rotor assembly diagram provided by design.
Step 12: obtaining the axial length DE of the end face corresponding to the fit spigot of the rear fulcrum section fitting centroids B to 9 stages of grate tooth discs and the high-pressure turbine rotor assembly drum shaft; the axial length DE of the corresponding end face of the rear fulcrum section fitting centroid B to the 9-stage grate disc and the drum shaft matching spigot can be recorded by looking up a high-pressure turbine rotor assembly diagram provided by design.
Step 13: measuring a jumping parameter of a rotor assembly of the high-pressure compressor; referring to fig. 3, on the stacking optimization equipment, the cylindrical surface and the shaft shoulder end surface of the front pivot bearing inner ring mounted on the front journal of the high-pressure compressor rotor assembly are taken as references (corresponding to reference shafts, AD in fig. 3 and AE in fig. 7), and the cylindrical surface eccentricity delta of the matching seam allowance of the 9-stage labyrinth disc and the drum shaft is measuredcenter1And end face eccentricity deltatlit。
Step 14: measuring a high-pressure turbine rotor runout parameter; referring to fig. 4, on the stacking optimization equipment, with the cylindrical surface S and the end surface T corresponding to the drum shaft of the high-pressure turbine rotor assembly and the 9-stage labyrinth plate matching seam allowance as references (the corresponding reference shaft is MN in fig. 4, which is parallel to DE in fig. 6), the cylindrical surface eccentricity delta at the position where the rear fulcrum bearing outer ring is installed on the rear journal is measuredcenter3。
Step 15: acquiring a comprehensive eccentricity formula; refer to FIG. 5 andFIG. 6, eccentricity δ of part1 of the first partcenter1The magnitude of the effect on the eccentricity of the second part2 is deltacenter1The angular phases are consistent; similarly according to the triangle, the end surface eccentricity δ of the first part1tiltThe magnitude of the effect on the eccentricity of the second part2 is deltacenter2H δ tilt/(d/2), angular phase offset 180 □; and the eccentricity delta of the part2center3The magnitude and the phase of the influence on the self eccentricity are not changed.
Step 16: and (5) taking the parameters obtained in the steps (11) to (15) as input, and obtaining the cylindrical surface eccentricity at the rear shaft neck after the compressor rotor and the high-pressure turbine rotor are assembled at any rotation angle phase theta through calculation.
In this embodiment, the step 3 specifically includes: on the stacking optimization equipment, a cylindrical surface S and a shaft shoulder end surface T at the position of a front pivot bearing inner ring arranged on a front journal of a high-pressure compressor rotor assembly are taken as references to measure cylindrical surface eccentricity delta of a 9-stage labyrinth disc and a drum shaft matching spigotcenter1And the end surface eccentricity delta of the matched spigot of the 9-stage grate toothed disc and the drum shaft of the high-pressure turbine rotor assemblytlit。
In this embodiment, the step 14 specifically includes: on the stacking optimization equipment, the cylindrical surface S and the end surface T corresponding to the matching seam allowance of the drum shaft of the high-pressure turbine rotor assembly and the 9-stage grate disc are used as references, and the cylindrical surface eccentricity delta at the position of the rear supporting point bearing outer ring arranged on the rear shaft neck is measuredcenter3。
In this embodiment, the comprehensive eccentricity formula in step 15 is specifically:
wherein the content of the first and second substances,
δcenterthe comprehensive eccentricity of a rear journal bearing fulcrum is based on a front journal of a rotor of a core machine;
δcenter2＝H*δtilt/(d/2)，δcenter2is deltatiltInfluence on the cylindrical surface eccentricity of a rear journal of the core machine;
h is the axial dimension from the front end surface of a drum shaft of the high-pressure turbine rotor assembly to a rear journal bearing fulcrum;
d is the diameter of the matched cylindrical surface of the rear spigot of the nine-stage labyrinth plate of the high-pressure compressor.
In this embodiment, the step 16 specifically includes: at deltacenter1、δtlitAnd delta measured in step 14center3For input, the cylindrical surface eccentricity at the rear shaft neck after the compressor rotor and the high-pressure turbine rotor are assembled at any rotation angle phase theta can be obtained through calculation.
Referring to fig. 7, in the present embodiment, the mathematical model for predicting and optimizing the eccentricity of the center of mass of the rotor of the core machine in step 3 is:
CD (BE) AD/(AD + DE) ACD is similar to △ ABE according to △;
BE: the cylindrical surface eccentricity of the rear journal of the core machine rotor with the front journal as the reference can be obtained according to the method in the step 1;
AD: axial lengths of end faces D corresponding to matched spigots of front support point section fitting centroids A to 9 stages of grate tooth discs and high-pressure turbine rotor assembly drum shafts can be obtained according to the method in the step 11;
DE: axial lengths of end faces corresponding to matched spigots of rear fulcrum section fitting centroids B to 9 stages of grate tooth discs and high-pressure turbine rotor assembly drum shafts can be obtained according to the method in the step 12;
theta is a rotation angle phase of the high-pressure turbine rotor in rotating assembly relative to the high-pressure compressor rotor.
According to the optimization method for the eccentricity of the mass center of the rotor of the engine core machine, before the rotor is assembled, the angular phase with the minimum OC value is selected through optimization calculation to guide the assembly of the rotor of the core machine, so that the purposes of reducing the eccentricity of the mass center of the rotor of the core machine, reducing the unbalance amount of the rotor of the core machine and improving the vibration of a high-pressure rotor are indirectly achieved.
The method realizes the optimization of the fitted centroid eccentricity of the rear spigot of the slotted disk of the core machine rotor before assembly, indirectly controls the centroid eccentricity of the rotor, improves the success rate of one-time assembly and reduces the assembly manufacturing cost;
the method can excavate the maximum value of the internal vibration performance of the existing machine part, and reduce and improve the vibration of the high-pressure rotor;
with the mature application of the method, the retest after assembly can be omitted in the process, and the development cost is effectively reduced.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (6)
1. The method for optimizing the eccentricity of the center of mass of the rotor of the engine core is characterized by comprising the following steps of:
step 1: acquiring the cylindrical surface eccentricity of a rear shaft neck after the high-pressure compressor rotor and the high-pressure turbine rotor are assembled at any rotation angle phase theta, and further solving the BE value; BE is the cylindrical surface eccentricity at the rear journal of the core machine rotor with the front journal as the reference;
step 2: before assembling a core machine rotor, keeping the high-pressure compressor rotor still, rotating the high-pressure turbine rotor in a unidirectional mode, wherein the phase theta of a rotating angle is an integral multiple value of 360 DEG/n, wherein n is the number of connecting bolts on a connecting surface, calculating the actual rotating axis AB distance OC formed by connecting a centroid O to a front supporting point and a rear supporting point of a cylindrical surface fitting cylindrical surface of a rear spigot of a 9-stage labyrinth disc of the high-pressure compressor rotor one by one, and taking the minimum possible value of the OC as the optimization target of the optimization method of the mass center eccentricity of the engine core machine rotor;
and step 3: establishing a core machine rotor mass center eccentricity prediction optimization mathematical model;
and 4, step 4: according to the core machine rotor mass center eccentricity prediction optimization mathematical model in the step 3, a rotation angle phase theta value corresponding to the minimum distance OC between the actual rotation axis AB formed by connecting lines of a cylindrical surface fitting centroid O of the rear spigot of the 9-stage labyrinth disc and the front supporting point and the rear supporting point is solved, and the high-pressure turbine rotor and the high-pressure compressor rotor are assembled in an angular rotation mode according to the rotation angle phase theta value;
the step 1 specifically comprises:
step 11: obtaining the axial length AD of the front supporting point section fitting centroids A to 9 stages of grate tooth discs and the corresponding end surface D of the drum shaft matching spigot of the high-pressure turbine rotor assembly;
step 12: obtaining the axial length DE of the end face corresponding to the fit spigot of the rear fulcrum section fitting centroids B to 9 stages of grate tooth discs and the high-pressure turbine rotor assembly drum shaft;
step 13: measuring a jumping parameter of a rotor assembly of the high-pressure compressor;
step 14: measuring a high-pressure turbine rotor runout parameter;
step 15: acquiring a comprehensive eccentric formula at the rear shaft neck of a core machine rotor after a high-pressure compressor rotor assembly and a high-pressure turbine rotor assembly are assembled;
step 16: and (5) taking the parameters obtained in the steps 11 to 14 as input, and calculating to obtain the cylindrical surface eccentricity at the rear shaft neck after the high-pressure compressor rotor and the high-pressure turbine rotor are assembled at any rotation angle phase theta by means of the comprehensive eccentricity formula in the step 15.
2. The method for optimizing the eccentricity of the center of mass of the rotor of the engine core according to claim 1, wherein the step 13 is specifically as follows: on the stacking optimization equipment, a cylindrical surface and a shaft shoulder end surface at the position of a front pivot bearing inner ring installed on a front shaft neck of a high-pressure compressor rotor assembly are taken as references to measure cylindrical surface eccentricity delta of a matching spigot of a 9-stage labyrinth disc and a high-pressure turbine rotor assembly drum shaftcenter1And the end surface eccentricity delta of the matched spigot of the 9-stage grate toothed disc and the drum shaft of the high-pressure turbine rotor assemblytlit。
3. The method for optimizing the eccentricity of the center of mass of the rotor of the engine core according to claim 2, wherein the step 14 is specifically as follows: on the stacking optimization equipment, the drum shaft of the high-pressure turbine rotor component corresponds to the matching spigot of the 9-stage grate discMeasuring the cylindrical surface eccentricity delta of the outer ring of the rear fulcrum bearing arranged on the rear journal by taking the cylindrical surface S and the end surface T as referencescenter3。
4. The method for optimizing the eccentricity of the center of mass of the rotor of the engine core as recited in claim 3, wherein the comprehensive eccentricity formula in the step 15 is specifically as follows:
δcenter2＝H*δtilt/(d/2)，δcenter2is deltatiltInfluence on the cylindrical surface eccentricity of a rear journal of the core machine;
h is the axial dimension from the front end surface of a drum shaft of the high-pressure turbine rotor assembly to a rear journal bearing fulcrum;
d is the diameter of the matched cylindrical surface of the rear spigot of the nine-stage labyrinth plate of the high-pressure compressor.
5. The method for optimizing the eccentricity of the center of mass of the rotor of the engine core according to claim 4, wherein the step 16 is specifically as follows: at deltacenter1、δtlitAnd deltacenter3For input, the cylindrical surface eccentricity at the rear shaft neck after the high-pressure compressor rotor and the high-pressure turbine rotor are assembled at any rotation angle phase theta can be obtained through calculation.
6. The method for optimizing eccentricity of the center of mass of the rotor of the engine core as claimed in claim 1, wherein the mathematical model for predicting and optimizing the eccentricity of the center of mass of the rotor of the core in the step 3 is as follows:
wherein the content of the first and second substances,
CD (BE) AD/(AD + DE) ACD is similar to △ ABE according to △;
BE: the cylindrical surface eccentricity of the rear journal of the core machine rotor with the front journal as the reference can be obtained according to the method in the step 1;
AD: axial lengths of end faces D corresponding to matched spigots of front support point section fitting centroids A to 9 stages of grate tooth discs and high-pressure turbine rotor assembly drum shafts can be obtained according to the method in the step 11;
DE: axial lengths of end faces corresponding to matched spigots of rear fulcrum section fitting centroids B to 9 stages of grate tooth discs and high-pressure turbine rotor assembly drum shafts can be obtained according to the method in the step 12;
theta is a rotation angle phase of the high-pressure turbine rotor in rotating assembly relative to the high-pressure compressor rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710084586.8A CN106837426B (en) | 2017-02-16 | 2017-02-16 | Method for optimizing eccentricity of mass center of rotor of engine core machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710084586.8A CN106837426B (en) | 2017-02-16 | 2017-02-16 | Method for optimizing eccentricity of mass center of rotor of engine core machine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106837426A CN106837426A (en) | 2017-06-13 |
| CN106837426B true CN106837426B (en) | 2020-01-17 |
Family
ID=59129065
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710084586.8A Active CN106837426B (en) | 2017-02-16 | 2017-02-16 | Method for optimizing eccentricity of mass center of rotor of engine core machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106837426B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109117461B (en) * | 2018-09-12 | 2021-08-20 | 大连理工大学 | Method for calculating rotor assembly axis eccentricity based on radial run-out measurement |
| CN110595690B (en) * | 2019-01-07 | 2020-11-13 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment measurement and intelligent learning assembly method and device based on centroid, gravity center and inertia center vector minimization |
| CN112307426B (en) * | 2020-12-28 | 2021-03-26 | 中国航发上海商用航空发动机制造有限责任公司 | Method and system for determining rotation axis |
| CN114858123B (en) * | 2021-02-04 | 2023-08-11 | 中国航发商用航空发动机有限责任公司 | Method and device for determining concentricity of center of comb plate disk relative to rotation axis |
| CN115826407B (en) * | 2022-11-29 | 2024-04-09 | 中国航发沈阳发动机研究所 | Control method for reducing drum shaft rotation inertia excitation |
| CN115790976B (en) * | 2023-02-07 | 2023-04-14 | 西安航天精密机电研究所 | Method for testing working stability of H-shaped dynamic pressure motor of high-precision gyroscope |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7278819B2 (en) * | 2005-07-05 | 2007-10-09 | General Electric Company | Variable stator vane lever arm assembly and method of assembling same |
| US7912587B2 (en) * | 2007-07-25 | 2011-03-22 | Pratt & Whitney Canada Corp. | Method of balancing a gas turbine engine rotor |
-
2017
- 2017-02-16 CN CN201710084586.8A patent/CN106837426B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN106837426A (en) | 2017-06-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106837426B (en) | Method for optimizing eccentricity of mass center of rotor of engine core machine | |
| US7792600B2 (en) | System and a method for assembling a rotor stack | |
| JP2015068342A (en) | Method of scaling to custom-sized turbomachine airfoil | |
| CN111241609A (en) | Prediction method for blade tip clearance of rotor and stator assembly of aircraft engine | |
| CN109117461B (en) | Method for calculating rotor assembly axis eccentricity based on radial run-out measurement | |
| EP1862698B1 (en) | Rotor unbalance correction | |
| CN111460677B (en) | Method for establishing rotor stacking precision prediction model based on geometric algebraic theory | |
| CN107895077B (en) | Gas turbine pull rod rotor assembly parameter optimization method considering multiple disk and drum manufacturing factors | |
| JP4772594B2 (en) | Low-speed balance method and low-speed balance enforcement device for rotating equipment | |
| EP2803821A1 (en) | Blade device, blade system, and corresponding method of manufacturing a blade system | |
| CN108953130A (en) | A kind of compressor stator blade fan-shaped section Quick Release housing device | |
| CN102680173A (en) | Control method for improving tone quality of single-rotor compressor of inverter air conditioner | |
| CN109684711A (en) | A kind of turboshaft engine is pneumatically connected more rotor coupled vibration analysis methods | |
| CN111022135B (en) | Assembling method for controlling gap between grates of blade tips of engine power turbine | |
| CN104018886A (en) | Turbocharger wheel with sound control | |
| JP4738490B2 (en) | Rotating body balance adjustment method | |
| Zemp et al. | Unsteady CFD investigation on inlet distortion in a centrifugal compressor | |
| CN116557352A (en) | Balance ring and blisk subassembly suitable for adjust blisk subassembly balancing volume | |
| CN103934659B (en) | The multistage video disc of high accuracy is piled up beating of rotor and is controlled and optimize installation method | |
| RU2426014C1 (en) | Calculated-simulation procedure for shaft balancing | |
| JP6773791B2 (en) | Diagonal turbine wheel | |
| JP6716080B2 (en) | Rotating machines and equipment for energy conversion including such machines | |
| Lubell et al. | Identification and correction of rotor instability in an oil-free gas turbine | |
| CN112943699A (en) | Compressor stator blade vibration reduction optimization design method based on corner design | |
| RU2630954C1 (en) | Method of shaft line assembly |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |