CN114136266B - Coaxiality detection method for double-rotor aeroengine - Google Patents
Coaxiality detection method for double-rotor aeroengine Download PDFInfo
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- CN114136266B CN114136266B CN202111222106.2A CN202111222106A CN114136266B CN 114136266 B CN114136266 B CN 114136266B CN 202111222106 A CN202111222106 A CN 202111222106A CN 114136266 B CN114136266 B CN 114136266B
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- G01B21/00—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant
- G01B21/22—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapers; for testing the alignment of axes
- G01B21/24—Measuring arrangements or details thereof, where the measuring technique is not covered by the other groups of this subclass, unspecified or not relevant for measuring angles or tapers; for testing the alignment of axes for testing alignment of axes
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Abstract
The invention provides a method for detecting coaxiality of a double-rotor aeroengine, which comprises the steps of dividing an aeroengine casing into a core engine unit body, a fan component and a turbine component, measuring coaxiality of the core engine unit body, the fan component and the turbine component respectively, and finally carrying out vector operation on the coaxiality of each obtained part to obtain the coaxiality of a high-voltage rotor and the coaxiality of a low-voltage rotor of the whole aeroengine. The invention relates to a method for detecting coaxiality of a three-section aeroengine, which is simple, has no change to the original rotary measuring platform, has high measuring efficiency, and can be used for measuring different cases by using a plurality of platforms in parallel.
Description
Technical Field
The disclosure relates to the technical field of aeroengines, in particular to a method for detecting coaxiality of a double-rotor aeroengine.
Background
The vibration fault of the whole aircraft engine is complicated in cause and is often the result of the combined action of a plurality of comprehensive factors. However, a great deal of scientific research and production practice show that many vibrations are often caused by the collision friction of a rotor and a stator due to the out-of-coaxiality of the casing system. Therefore, the accurate measurement of coaxiality has extremely important significance for reducing the vibration probability of the whole engine and improving the reliability of the engine. The existing engine coaxiality measurement technology comprises a rotary platform method, a three-coordinate machine measurement method and a laser displacement sensor measurement method. When the coaxiality of the whole engine is measured, all engine stator cases are required to be assembled and measured step by step, and the method is acceptable for medium and small-sized aeroengines, but the following difficulties are encountered when the coaxiality of large-sized double-rotor engines is measured: 1) Practical difficulties in manufacturing large-size measuring tools, installing testing devices and the like; 2) The efficiency is lower, and the precision is low.
Disclosure of Invention
In view of this, in view of practical difficulties encountered in the large-size, dual-rotor aircraft engine coaxiality measurement process, the disclosed embodiments provide a dual-rotor aircraft engine coaxiality detection method, which is a "three-stage" aircraft engine casing coaxiality detection and analysis method for a fan component (intake casing+fan), a core engine unit body, and a turbine component (low-pressure turbine+turbine support). According to the detection method, an aeroengine is firstly divided into a core engine unit body, a fan component and a turbine component, coaxiality measurement is carried out on a core engine unit body case, a fan component case and a turbine component case respectively, and finally, the coaxiality of a high/low pressure rotor system of the whole engine is calculated by adopting a vector operation algorithm.
In order to achieve the above object, the present invention provides the following technical solutions:
a method for detecting coaxiality of a double-rotor aeroengine comprises the steps of dividing an aeroengine casing into a core engine unit body, a fan component and a turbine component, measuring coaxiality of the core engine unit body, the fan component and the turbine component respectively, and finally carrying out vector operation on the obtained coaxiality of each part to obtain the coaxiality of a high-voltage rotor and the coaxiality of a low-voltage rotor of the whole aeroengine.
Further, when the coaxiality of the core machine unit body, the fan component and the turbine component is measured, the core machine unit body, the fan component and the turbine component are respectively divided into a plurality of sections according to a high-pressure rotor supporting mode and a low-pressure rotor supporting mode, vector offsets of the sections are respectively calculated, and then the coaxiality of the core machine unit body, the fan component and the turbine component is respectively obtained through vector calculation of the vector offsets of the sections.
Further, when vector offset of each section is calculated, aligning and leveling the tested casing, determining an end face reference and a cylindrical surface reference, measuring radial runout of a fulcrum, and calculating circle center coordinates of the tested surface to obtain the vector offset of the section.
Further, the method comprises the steps of:
calculating vector offset BG of center fitting of a supporting point of the core unit body 3 and a rear mounting side of a combustion chamber of the core unit body, calculating vector offset HK of center fitting and a supporting point of the turbine component casing 5 of the front mounting side of the turbine component casing, the coaxiality between the supporting point of the core machine unit body 3 and the supporting point of the turbine component casing 5, namely the coaxiality of the high-pressure rotor, is obtained through vector operation on the offset vector BG and the offset vector HK;
calculating vector offset CB between the supporting point of the intermediate casing 2 of the core unit body and the supporting point of the intermediate casing 3 of the core unit body, calculating vector offset CD between fitting circle centers of the supporting point of the intermediate casing 2 of the core unit body and the front mounting edge of the intermediate casing of the core unit body, calculating offset vector FE between fitting circle centers of the supporting point 1 of the fan component casing and the rear mounting edge of the fan component casing, and obtaining coaxiality between the supporting points 1,2 and 5, namely low-voltage rotor coaxiality, by vector operation on the offset vector BG, the offset vector HK, the offset vector CB, the offset vector CD and the offset vector FE.
Further, the high-pressure rotor is supported in a mode of 1-0-1, and the low-pressure rotor is supported in a mode of 1-1-1.
Further, coaxiality was measured using a turntable method.
Further, when the end face reference and the cylindrical surface reference are determined, neither the end face reference nor the cylindrical surface reference is greater than 0.02mm.
Further, a least square method is adopted to fit the center coordinates of the measured surface.
The method for detecting coaxiality of the double-rotor aeroengine has the beneficial effects that:
(1) The measuring method is simple and has no change to the original rotary measuring platform.
(2) The measuring efficiency is high, and a plurality of platforms can be used for carrying out parallel measurement on different cases.
(3) The whole machine coaxiality evaluation method is simple and practical.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present disclosure, and other drawings may be obtained according to these drawings without inventive effort to a person of ordinary skill in the art.
FIG. 1 is a schematic diagram of a method for detecting coaxiality of a dual-rotor aero-engine;
FIG. 2 is a schematic diagram of a measurement of a casing of a core unit according to an embodiment of the present invention;
FIG. 3 is a schematic illustration of a turbine component case coaxiality measurement in an embodiment of the present disclosure;
FIG. 4 is a schematic diagram illustrating a fan assembly case coaxiality measurement according to an embodiment of the present invention;
fig. 5 is a schematic diagram of a jitter value recording sequence and a center coordinate in an embodiment of the present invention.
Detailed Description
Embodiments of the present disclosure are described in detail below with reference to the accompanying drawings.
Other advantages and effects of the present disclosure will become readily apparent to those skilled in the art from the following disclosure, which describes embodiments of the present disclosure by way of specific examples. It will be apparent that the described embodiments are merely some, but not all embodiments of the present disclosure. The disclosure may be embodied or practiced in other different specific embodiments, and details within the subject specification may be modified or changed from various points of view and applications without departing from the spirit of the disclosure. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art without inventive effort, based on the embodiments in this disclosure are intended to be within the scope of this disclosure.
It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present disclosure, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concepts of the disclosure by way of illustration, and only the components related to the disclosure are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.
As shown in fig. 1, an embodiment of the present disclosure provides a method for detecting coaxiality of a dual-rotor aeroengine, which includes dividing an aeroengine casing into a core unit body, a fan component and a turbine component, measuring coaxiality of the core unit body casing, the fan component casing and the turbine component casing, and performing continuous calculation by using a vector algorithm to calculate and analyze coaxiality of the whole machine.
Taking high pressure rotor support mode 1-0-1 as an example, low pressure rotor support mode 1-1-1.
Coaxiality of 3# and 5# fulcrums: the turntable method is used for measuring coaxiality of a stator casing of the core machine unit body formed by the middle bearing frame unit body, the compressor stator, the combustion chamber and the high conductance. During measurement, a 3# fulcrum inner hole is used as a cylindrical surface reference, an intermediate and gas compressor combined end surface is used as an end surface reference, radial runout and end surface runout (8 points are recorded) of a rear installation side of the combustion chamber are measured, a least square method is used for fitting out the center of an outer cylindrical surface of the rear installation side of the main combustion chamber, an offset projection vector of the outer cylindrical surface of the rear installation side of the main combustion chamber relative to the 3# fulcrum inner hole is obtained, and a least square method is used for fitting out a unit normal vector of the end surface of the rear installation side of the main combustion chamber; measuring turbine coaxiality by a turntable method, wherein an outer cylindrical surface of a front mounting side of a turbine casing is used as a cylindrical surface reference during measurement, an end surface of the front mounting side of the turbine casing is used as an end surface reference, radial runout (8 points are recorded) of an inner hole of a No. 5 fulcrum is measured, and a circle center of the No. 5 fulcrum is fitted by a least square method to obtain an offset projection vector of the No. 5 fulcrum relative to the outer cylindrical surface of the front mounting side of the turbine casing; and vector operation is carried out on the offset projection vector of the inner hole of the outer cylindrical surface of the main combustion mounting side relative to the 3# pivot, the square vector of the end surface of the main combustion mounting side and the offset projection vector of the 5# pivot relative to the outer cylindrical surface of the front mounting side of the turbine casing, so that the offset projection vector of the 5# pivot relative to the 3# pivot is obtained, and 2 times of the model of the offset projection vector of the 5# pivot relative to the 3# pivot is 3# pivot coaxiality.
Coaxiality of 1# fulcrum, 2# fulcrum and 5# fulcrum: measuring the coaxiality of the fan casing, wherein during measurement, the end face of the rear mounting edge of the fan casing and the outer cylindrical surface are taken as references, the radial runout (8 points are recorded) of the inner hole of the No. 1 fulcrum is measured, and the circle center of the inner hole of the No. 1 fulcrum is fitted by a least square method, so that a projection vector of the inner hole of the No. 1 fulcrum relative to the rear mounting edge of the fan is obtained; and then vector calculation is carried out on the offset projection vector of the inner hole of the No. 1 fulcrum relative to the rear mounting side of the fan, the internal coaxiality of the middle bearing frame unit body (namely, the coaxiality of the No. 2 fulcrum relative to the front mounting side of the middle bearing frame unit body) and the offset projection vector of the No. 5 fulcrum relative to the No. 3 fulcrum, so as to obtain the offset projection vector of the No. 5 fulcrum relative to the No. 2 fulcrum, and the offset projection vector of the No. 1 fulcrum relative to the No. 2 fulcrum. The 1# fulcrum and the 2# fulcrum form a common axis 1, the 2# fulcrum and the 5# fulcrum form a common axis 2. The coaxiality of the No. 5 fulcrum relative to the No. 1 fulcrum and the No. 2 fulcrum is equal to 2 times of the distance of the No. 5 fulcrum relative to the coaxial line 1, and the coaxiality of the No. 1 fulcrum relative to the No. 2 fulcrum and the No. 5 fulcrum is equal to 2 times of the distance of the No. 5 fulcrum relative to the coaxial line 2.
In particular, reference is made to fig. 2-5. When the turntable method is used for measuring runout, the tested casing needs to be aligned and leveled, and the end face reference and the cylindrical surface reference are not more than 0.02mm.
The turntable method measures the runout of the measured surface and records the data according to figure 5, and then the circle center of the measured surface is calculated by using the formula least square method. The method comprises the following specific steps:
step one: the intermediate casing with the 3# supporting point 101 and the 2# supporting point 102 is assembled on the rotary platform, and is aligned and leveled by taking the inner hole B surface of the 3# supporting point as a cylindrical surface reference and the combined end surface A of the intermediate casing 103 and the compressor casing 104 as an end surface reference.
Step two: measuring the radial runout TD-C2 of the No. 2 fulcrum, and recording the runout values according to the sequence of FIG. 5; and measuring the outer column radial runout TD-D2 and the end runout TD-D1 of the front mounting side D of the intermediate casing 103, and recording 8 points according to FIG. 5. TD-C2 data calculates the fitting center coordinates (X) of the inner cylindrical surface C of the 2# fulcrum according to the least square method C ，Y C ) The TD-D2 data calculates the outer cylinder fitting center coordinates (X) of the front mounting side D surface of the intermediate case 103 by the least square method D ，Y D ) The TD-D1 data calculates a unit normal vector (X) of the front mounting edge end face of the intermediate case 103 by a least square method Dn ，Y Dn ，Z Dn ) The fitting circle center of the inner cylindrical surface C of the No. 2 fulcrum relative to the inner hole B of the No. 3 fulcrum can use vectors
The fitting circle center of the outer column surface of the front installation edge D surface of the intermediate case 103 relative to the inner hole B of the 3# pivot point can be represented by a vector +.>
And (3) representing.
Step three: the compressor casing 104 and the combustion chamber are assembled to the intermediate casing 103 on the intermediate casing 105.
Step four: cylindrical radial runout TD-G2 and end runout TD-G1 of the mounting side G face behind the combustion chamber 105 are measured and the runout values are recorded sequentially in FIG. 5. TD-G2 calculates the fitting center coordinates (X) of the outer cylindrical surface of the rear mounting side G of the combustion chamber 105 by the least square method G ，Y G ) TD-G1 calculates a unit normal vector (X) of the end face of the rear mounting side of the combustion chamber 105 by the least square method Gn ，Y Gn ，Z Gn ) The fitting circle center of the outer column surface of the rear installation side G surface of the combustion chamber 105 relative to the inner hole B of the 3# pivot can use vectors
And (3) representing.
Step five: and (3) assembling the turbine casing 202 with the No. 5 fulcrum 201 on a rotary platform, and aligning and leveling by taking the H-plane end face of the front mounting edge of the turbine casing 202 as an end face reference and the outer cylindrical surface as a cylindrical surface reference, wherein the end face reference and the cylindrical surface reference are no more than 0.02mm.
Step six: and measuring radial runout TD-K2 of the inner hole cylindrical surface K of the fulcrum 5# and recording runout values according to the sequence of FIG. 5. Calculating the fitting center coordinates (X) of the inner hole cylindrical surface K of the No. 5 fulcrum K ，Y K ) The fitting circle center of the inner hole cylindrical surface K of the No. 5 fulcrum relative to the outer cylindrical surface of the front mounting side H of the turbine casing 202 can use vectors
And (3) representing.
Step seven: the fan casing 302 with the No. 1 fulcrum 301 is assembled on a rotary platform, the end face of the rear installation side E of the fan casing 302 is taken as an end face reference, the outer column face of the rear installation side E of the fan casing 302 is taken as a column face reference, and the alignment and the leveling are carried out, wherein the end face reference and the column face reference are not more than 0.02mm.
Step eight: the radial runout TD-F2 of the inner hole cylindrical surface F of the No. 1 fulcrum 301 is measured and the runout values are recorded in the sequence of FIG. 5. TD-F2 data calculates fitting center coordinates (X) of the inner hole cylindrical surface F of the No. 1 fulcrum 301 according to a least square method F ，Y F ) The fitting circle center of the inner hole cylindrical surface F of the No. 1 fulcrum 301 relative to the rear mounting edge of the fan casing 302 can use vectors
And (3) representing.
Step nine: the rear mounting side G of the combustion chamber 105 coincides with the front mounting side H of the turbine casing 202 during the final assembly of the turbine casing engine, assuming that the distance from the front mounting side of the turbine casing to the 5# fulcrum is L A The vector offset of the rear mounting edge end of the combustion chamber 105 facing the center of the turbine casing 5# pivot is
Through vector superposition operation, the center of a 5# fulcrum relative to a 3# fulcrum is +.>
The circle center of the No. 5 fulcrum relative to the No. 2 fulcrum is as follows: />
Step ten: the end face of the front mounting edge D of the intermediate case 103 coincides with the end face of the rear mounting edge E of the fan case 302 during the final assembly of the engine, assuming that the distance from the rear mounting edge of the fan case to the 1# fulcrum is L B The vector offset of the front mounting edge of the intermediate case facing the center of the fan case 1# pivot is
Through vector superposition operation, the center of a 1# fulcrum relative to a 2# fulcrum is +.>
Step eleven: for a dual rotor engine with intermediate bearings, the axial distances of the # 4 and # 5 fulcrums are very close, and the # 4 fulcrums can be replaced by the # 5 fulcrums when evaluating the high pressure rotor support system. High-pressure rotor supporting system 3# and 4# support point coaxiality is equal to vector
2 times the die, namely: />
Step twelve: coaxiality of the No. 1 fulcrum relative to the No. 2 fulcrum is equal to vector
2 times the die, namely:
the coaxiality of the fulcrum # 5 relative to the fulcrum # 2 is equal to the vector +.>
2 times the die, namely: />
Step thirteen: assuming that the axial distance between the 1# fulcrum and the 2# fulcrum is L1, i.e
The axial distance between the fulcrum # 2 and the fulcrum # 5 is L2, i.e.>
The coaxiality of the No. 1 fulcrum relative to the No. 2 fulcrum and the No. 5 fulcrum is 2 times of the space linear distance between the No. 1 fulcrum and the No. 2 fulcrum and the No. 5 fulcrum, namely +.>
The coaxiality of the 5 fulcrums relative to the 1# and 2# fulcrums is 2 times of the space linear distance between the 5# fulcrum and the 1# and 2# fulcrums, namely +.>
The foregoing is merely specific embodiments of the disclosure, but the protection scope of the disclosure is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the disclosure are intended to be covered by the protection scope of the disclosure. Therefore, the protection scope of the present disclosure shall be subject to the protection scope of the claims.
Claims (5)
1. The method for detecting the coaxiality of the double-rotor aero-engine is characterized by comprising the steps of dividing an aero-engine casing into a core engine unit body, a fan component and a turbine component, measuring the coaxiality of the core engine unit body, the fan component and the turbine component respectively, and finally carrying out vector operation on the obtained coaxiality of each part to obtain the coaxiality of a high-voltage rotor and the coaxiality of a low-voltage rotor of the whole aero-engine;
when the coaxiality of the core machine unit body, the fan component and the turbine component is measured, dividing the core machine unit body, the fan component and the turbine component into a plurality of sections according to a high-pressure rotor supporting mode and a low-pressure rotor supporting mode, respectively calculating vector offset of each section, and respectively obtaining the coaxiality of the core machine unit body, the fan component and the turbine component through vector operation of the vector offset of each section;
when vector offset of each section is calculated, aligning and leveling the tested casing, determining an end face reference and a cylindrical surface reference, measuring radial runout of a fulcrum, and calculating circle center coordinates of the tested surface to obtain the vector offset of the section;
calculating vector offset BG of fitting circle centers of a supporting point of a core machine unit body 3 and a rear mounting side of a combustion chamber of the core machine unit body, calculating vector offset HK of fitting circle centers of a front mounting side of a turbine component casing and a supporting point of a turbine component casing 5, and carrying out vector operation on the vector offset BG and the vector offset HK to obtain coaxiality between the supporting point of the core machine unit body 3 and the supporting point of the turbine component casing 5, namely high-pressure rotor coaxiality;
calculating vector offset CB between the supporting point of the intermediate casing 2 of the core unit body and the supporting point of the intermediate casing 3 of the core unit body, calculating vector offset CD between fitting circle centers of the supporting point of the intermediate casing 2 of the core unit body and the front mounting edge of the intermediate casing of the core unit body, calculating vector offset FE between fitting circle centers of the supporting point 1 of the fan component casing and the rear mounting edge of the fan component casing, and obtaining coaxiality between the supporting points 1,2 and 5, namely low-voltage rotor coaxiality, by vector operation on the vector offset BG, the vector offset HK, the vector offset CB, the vector offset CD and the vector offset FE.
2. The method for detecting coaxiality of a double-rotor aeroengine according to claim 1, wherein the supporting mode of the high-pressure rotor is 1-0-1, and the supporting mode of the low-pressure rotor is 1-1-1.
3. The method for detecting coaxiality of a dual-rotor aero-engine according to claim 1, wherein coaxiality is measured by adopting a turntable method.
4. The method for detecting coaxiality of a dual-rotor aero-engine according to claim 1, wherein when the end face reference and the cylindrical surface reference are determined, the end face reference and the cylindrical surface reference are not more than 0.02mm.
5. The method for detecting coaxiality of a double-rotor aero-engine according to claim 1, wherein a least square method is adopted to fit the center coordinates of the measured surface.
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| GB201704173D0 (en) * | 2017-03-16 | 2017-05-03 | Rolls Royce Plc | Gas turbine engine |
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| CN101699244A (en) * | 2009-09-24 | 2010-04-28 | 北京航空航天大学 | Transonic contra-rotating turbine test rig |
| EP2615410A1 (en) * | 2012-01-16 | 2013-07-17 | General Electric Company | Turbomachine blade monitoring system |
| CN103791814A (en) * | 2014-02-14 | 2014-05-14 | 哈尔滨工业大学 | Double-stand-column aero-engine rotor electric drive assembly method and device based on eddy current sensing |
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