CN112629840B - Double-rotor-support-casing tester for aero-engine and testing method thereof - Google Patents
Double-rotor-support-casing tester for aero-engine and testing method thereof Download PDFInfo
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- CN112629840B CN112629840B CN202011312972.6A CN202011312972A CN112629840B CN 112629840 B CN112629840 B CN 112629840B CN 202011312972 A CN202011312972 A CN 202011312972A CN 112629840 B CN112629840 B CN 112629840B
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- 238000012360 testing method Methods 0.000 title claims abstract description 29
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- 230000008878 coupling Effects 0.000 claims description 20
- 238000010168 coupling process Methods 0.000 claims description 20
- 238000005859 coupling reaction Methods 0.000 claims description 20
- 238000006073 displacement reaction Methods 0.000 claims description 8
- 238000005070 sampling Methods 0.000 claims description 8
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- 238000013135 deep learning Methods 0.000 claims description 5
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H17/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves, not provided for in the preceding groups
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/14—Determining imbalance
- G01M1/16—Determining imbalance by oscillating or rotating the body to be tested
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention belongs to the technical field of aero-engine tests and tests, in particular to a double-rotor-support-casing tester of an aero-engine and a test method thereof, wherein the tester comprises a low-pressure rotor, a central bevel gear system, a high-pressure rotor, a low-pressure casing, an intermediate casing and a high-pressure casing; the low-pressure rotor comprises a low-pressure turbine shaft, and the low-pressure turbine shaft penetrates through the central bevel gear system and is rotationally connected with the high-pressure rotor; the low-voltage rotor is driven by a low-voltage driving motor, the central bevel gear system is connected with a high-voltage driving motor, and the high-voltage rotor is driven by the central bevel gear system. The invention has simple and reasonable structure, adopts a scaled (such as 2:1) reduced scale design according to the structure of the real engine, and the structure of the fan four-stage disc and the structure of the high-pressure nine-stage disc are consistent with the structure of the real engine. The structure of a squirrel cage, a cone shell, a bearing amplitude plate, a flexible casing and the like in the true engine are reserved, the rotor system structure of the engine and the vibration of the rotor system can be truly simulated, and the whole machine vibration research requirement of the aeroengine is met.
Description
Technical Field
The invention belongs to the technical field of aero-engine tests and tests, and particularly relates to an aero-engine double-rotor-support-casing tester and a test method thereof.
Background
With the increase of the thrust-weight ratio of the aero-engine, the structural change of the rotor system is large, and the vibration problem of the aero-engine is more remarkable due to the high rotating speed of the aero-engine. The dynamic coupling characteristic of the rotor of the aeroengine, the transmission of unbalanced vibration of the rotor comprise the transmission rules of vibration in the interior and the exterior of the aeroengine, the influence of hanging points on the transmission of vibration, the influence of disc-drum coupling vibration characteristic, gear meshing excitation and the like on unbalanced vibration of the rotor, the vibration rules of the generator case and the like, and the mechanism and the rules are in many undefined places to be researched. In particular, the unbalanced vector and the unbalanced vibration law of the rotor are unclear after the rotor is assembled or works for a period of time, and the unbalanced vibration among all the supporting points of the rotor and the research requirement of the vibration transmission law of the rotor-supporting-casing are particularly important and urgent because the unbalanced vibration cannot be directly measured on the inner rotor and can only be measured on the aeroengine casing.
The rotor and the supporting structure in the aero-engine are complex, and the existing testing means can not directly obtain the vibration data of the rotor structure body on the real engine; numerical simulation and emulation techniques also cannot accurately determine internal vibration state data of an aeroengine, and it is more difficult to accurately analyze the rule of transmission of internal rotor vibration of the engine to the outside and the final vibration performance at external measuring points.
The aviation real engine has a complex structure and more influence factors, and experimental research by using the aviation engine is limited; most of domestic rotor testers are developed in a disc shaft rigid supporting structure mode, the influence of a disc-drum coupling structure and an elastic support on the vibration characteristics of a rotor is not considered, a simplified model of the rotor tester is greatly different from a true machine structure, and the vibration characteristics of a true engine cannot be well simulated. Therefore, based on the theory of structural similarity and dynamics similarity, the development of the double-rotor-support-casing tester and the testing method for researching the unbalanced vibration transmission rule has innovation and important significance.
Disclosure of Invention
In order to solve the problems in the background art, the invention provides the double-rotor-support-casing tester for the aero-engine and the testing method thereof, which can effectively realize vibration transmission and testing among a rotor, a support structure and a casing.
A first object of the present invention is to provide an aero-engine double rotor-bearing-casing tester comprising a low pressure rotor, a central bevel gear system and a high pressure rotor arranged in transverse succession, wherein: the low-pressure rotor, the central bevel gear system and the high-pressure rotor are fixed on the frame through a supporting structure, a low-pressure box is arranged on the periphery of the low-pressure rotor, an intermediate box is arranged on the periphery of the central bevel gear system, a high-pressure box is arranged on the periphery of the high-pressure rotor, and the low-pressure box, the intermediate box, the high-pressure box, the low-pressure rotor and the high-pressure rotor are all coaxially arranged and supported by the supporting structure;
the low-pressure rotor comprises a low-pressure turbine shaft, and the low-pressure turbine shaft penetrates through the central bevel gear system and is rotationally connected with the high-pressure rotor and the central bevel gear system;
the low-voltage rotor is driven by a low-voltage driving motor, the central bevel gear system is connected with a high-voltage driving motor, and the high-voltage rotor is driven by the central bevel gear system.
Further, the low-pressure rotor comprises a low-pressure fan section rotor and a low-pressure turbine rotor, the low-pressure fan section rotor comprises a fan rotating shaft and a four-stage fan disc sleeved on the fan rotating shaft, the low-pressure turbine rotor comprises a low-pressure turbine shaft, a low-pressure turbine cone shell and a low-pressure turbine disc sleeved on the low-pressure turbine shaft, the low-pressure turbine cone shell is fixedly arranged at the outer end of the low-pressure turbine disc, the fan rotating shaft is connected with the low-pressure turbine shaft through a coupling, and a low-pressure driving motor is connected with the fan rotating shaft.
Further, the high-pressure rotor includes high-pressure front arm axle, high-pressure compressor 9-stage rim plate, high-pressure turbine axle, high-pressure turbine dish, high-pressure turbine cone shell and intermediary bearing, wherein:
the front end of the high-pressure front arm shaft is connected with the central bevel gear system, and the rear end of the high-pressure front arm shaft is connected with the 9-stage wheel disc of the high-pressure compressor; the high-pressure turbine disc is rigidly connected with a part of 9-stage turbine disc of the high-pressure compressor through a high-pressure turbine shaft, and the high-pressure turbine cone shell is fixedly connected to the outer end of the high-pressure turbine disc;
the high-pressure turbine cone shell is connected with the low-pressure turbine shaft through an intermediate bearing.
Further, the central bevel gear system comprises a speed increaser, a long coupler, a central bevel gear box, a driving bevel gear and a driven bevel gear, wherein: the speed increaser is connected with the high-pressure driving motor, and drives the driving bevel gear through the long coupler, the driving bevel gear is meshed with the driven bevel gear, and the driven bevel gear is matched and connected with the high-pressure front arm shaft so as to drive the high-pressure rotor to rotate.
Further, the support structure comprises a first support structure, a second support structure, a third support structure and a fourth support structure, wherein the first support structure and the fourth support structure are used for supporting the low-pressure rotor, the second support structure is used for supporting the low-pressure rotor and the central bevel gear box, the third support structure is used for supporting the high-pressure rotor, and the third support structure is an elastic support structure.
Further, the first supporting structure comprises a No. 1 amplitude plate, a No. 1 bearing cone shell, a No. 1 bearing seat, a No. 1 mouse cage and a No. 1 bearing, and one end of the fan rotating shaft is rotationally connected with the first supporting structure through the No. 1 bearing;
the second supporting structure comprises a No. 2 amplitude plate, a No. 2 bearing seat and a No. 2 bearing, and the other end of the fan rotating shaft is rotationally connected with the second supporting structure through the No. 2 bearing;
the third supporting structure comprises a No. 3 amplitude plate, a No. 3 bearing cone shell, a No. 3 mouse cage, a No. 3 bearing seat and a No. 3 bearing, and the middle part of the high-pressure front axle arm is rotationally connected with the third supporting structure through the No. 3 bearing;
the fourth supporting structure comprises a No. 4 amplitude plate, a No. 4 bearing cone shell, a No. 4 mouse cage, a No. 4 bearing seat and a No. 4 bearing, and the low-pressure turbine shaft is rotationally connected with the fourth supporting structure through the No. 4 bearing.
Further, the low-pressure box is fixed on a No. 1 web and a No. 2 web, the middle box is fixed on a No. 2 web and a No. 3 web, and the high-pressure box is fixed on a No. 3 web and a No. 4 web.
Further, the frame comprises a rotor system frame and a high-voltage transmission system frame, the low-voltage driving motor is fixed on the rotor system frame, and the high-voltage driving motor and the speed increaser are fixed on the high-voltage transmission system frame.
Further, the four-stage fan disc, the 9-stage disc of the high-pressure compressor, the low-pressure turbine disc and the high-pressure turbine disc are provided with a plurality of bolt holes in the circumferential direction of the edges of the discs.
The second object of the invention is to propose a testing method based on any one of the above aeroengine birotor-bearing-casing testers, comprising the steps of:
(1) Sampling by using Latin hypercube groups, and determining the unbalance amount and the phase to be added;
(2) Setting the rotating speed of a low-voltage driving motor, enabling a low-voltage rotor to rotate, enabling a high-voltage rotor not to rotate, and extracting vibration data of each test point;
(3) Setting the rotating speed of a high-voltage driving motor, enabling a high-voltage rotor to rotate, enabling a low-voltage rotor not to rotate, and extracting vibration data of each test point;
(4) Simultaneously setting the rotating speed of the low-voltage driving motor and the rotating speed of the high-voltage driving motor, so that the low-voltage rotor rotates and the high-voltage rotor rotates, and extracting vibration data of each test point;
(5) Repeating the steps (1) - (4) until 100 groups of unbalanced working conditions of sampling are completed;
(6) And (3) carrying out self-adaptive filtering on the measuring point signals to remove interference components, converting the acceleration signals into vibration speeds through numerical integration, converting the displacement signals into vibration displacements through numerical differentiation, and unifying the dimensions of vibration data.
(7) Training the neural network model by using the obtained test data through a deep learning algorithm, and analyzing the vibration transmission coupling rule of the double-rotor-support-casing.
Compared with the prior art, the invention has the following beneficial effects:
(1) The double-rotor-support-casing tester of the aeroengine has a high-low pressure double-rotor coupling structure, and the low-pressure fan, the low-pressure turbine, the high-pressure compressor 9-stage wheel disc and the high-pressure turbine disc are mutually coupled through the intermediate bearing, so that the coupling characteristic of the double-rotor aeroengine can be reflected well.
(2) The double-rotor-support-casing tester for the aero-engine is simple and reasonable in structure and comprehensive in consideration. According to the structure of the real engine, a fixed-proportion (such as 2:1) scale design is adopted, and the structure of a fan four-stage disc and a high-pressure compressor 9-stage disc is consistent with that of the real engine. The structures of a squirrel cage, a cone shell, a bearing amplitude plate, a flexible casing and the like in the true machine are reserved. Compared with most domestic rotor testers, the structure form of rigid support of the disc shaft is adopted, the influence of the disc-drum coupling structure, double-rotor high-low-pressure coupling and elastic support on the rotor vibration characteristics is not considered, the structure and the vibration of an engine rotor system can be truly simulated, and the whole machine vibration research requirement of an aeroengine is met.
(3) The double-rotor-support-casing tester of the aero-engine adopts a central bevel gear system, and a real high-voltage rotor of the aero-engine is taken as a power output end, and the central bevel gear is driven by a motor so as to drive the high-voltage rotor to operate. The high-pressure rotor is driven to operate, and the operation of a central bevel gear system is simulated.
(4) The aeroengine double-rotor-bearing-casing tester provided by the invention has a supporting structure of a squirrel cage, a conical shell and a web plate, is similar to a real engine supporting structure, comprises an elastic squirrel cage with a vibration damping effect, simplifies the conical shell and the web plate structure in a real engine, and is consistent with a real engine vibration transmission path.
(5) The dual rotor-bearing-case tester of the aeroengine of the present invention facilitates the application of unbalance. A plurality of bolt holes are circumferentially formed in the edges of the four-stage fan disc, the 9-stage disc of the high-pressure compressor, the low-pressure turbine disc and the high-pressure turbine disc in the tester, and unbalanced mass can be conveniently applied.
(6) According to the double-rotor-support-casing tester for the aero-engine and the testing method thereof, vibration data of a plurality of positions can be measured relative to a true engine.
Drawings
For a clearer description of embodiments of the invention or of solutions in the prior art, the drawings which are used in the description of the embodiments or of the prior art will be briefly described, it being obvious that the drawings in the description below are only some embodiments of the invention, and that other drawings can be obtained from them without inventive effort for a person skilled in the art.
FIG. 1 is an isometric view of an aircraft engine dual rotor-support-case tester of the present invention (inorganic case);
FIG. 2 is a general block diagram (inorganic box) of an aircraft engine dual rotor-support-case tester of the present invention;
FIG. 3 is a top view of the dual rotor-support-case tester (inorganic case) of the aero-engine of the present invention;
FIG. 4 is a cross-sectional view of the dual rotor-bearing-case tester of the aero-engine of the present invention;
FIG. 5 is a schematic view of the low pressure rotor configuration of the dual rotor-bearing-case tester of the aero-engine of the present invention;
FIG. 6 is a schematic view of the high pressure rotor configuration of the dual rotor-bearing-case tester of the aero-engine of the present invention;
FIG. 7 is a schematic diagram of the central bevel gear system of the dual rotor-bearing-case tester of the aero-engine of the present invention;
FIG. 8 is a schematic view of a first support structure of the dual rotor-bearing-case tester of the aero-engine of the present invention;
FIG. 9 is a schematic view of a second support structure of the dual rotor-bearing-case tester of the aero-engine of the present invention;
FIG. 10 is a schematic view of a third support structure of the dual rotor-bearing-case tester of the aero-engine of the present invention;
FIG. 11 is a schematic view of a fourth support structure of the dual rotor-bearing-case tester of the aero-engine of the present invention;
FIG. 12 is a schematic view of a low pressure case of the dual rotor-support-case tester of the aero-engine of the present invention;
FIG. 13 is a schematic view of an intermediate casing structure of the dual rotor-support-casing tester of the aero-engine of the present invention;
FIG. 14 is a schematic view of the high-pressure casing of the dual rotor-support-casing tester of the aero-engine of the present invention;
FIG. 15 is a schematic diagram of a frame structure of an aircraft engine dual rotor-bearing-case tester of the present invention;
wherein: 1-low pressure rotor, 11-fan rotating shaft, 12-fan four-stage disc, 13-low pressure turbine shaft, 14-low pressure turbine cone, 15-low pressure turbine disc, 16-low pressure driving motor, 17-set gear coupling, 2-high pressure rotor, 21-high pressure front arm shaft, 22-high pressure compressor 9-stage disc, 221-1-stage seal disc, 23-high pressure turbine shaft, 24-high pressure turbine disc, 25-high pressure turbine cone, 26-intermediate bearing, 3-central bevel gear system, 31-speed increaser, 32-long coupling, 33-central bevel gear box, 34-driving bevel gear, 35-driven bevel gear, 4-support mechanism, 41-first structure, 411-1 # web, 412-1 bearing cone, 413-1 bearing block, 414-1 squirrel cage, 415-1 bearing, 416-1 mount, 42-second support structure, 421-2 web, 422-2 bearing block, 423-2 bearing, 424-2 mount, 43-third support structure, 431-3 web, 432-3 bearing cone, 433-3 squirrel cage, 434-3 bearing block, 435-3 bearing, 436-3 mount, 44-fourth support structure, 441-4 web, 442-4 bearing cone, 443-4 squirrel cage, 444-4 bearing block, 445-4 bearing, 446-4 mount, 5-frame, 51-rotor system frame, 511-caster, 512-piezoelectric mount, 52-high-voltage transmission system frame, 521-high-voltage motor seat, 522-speed increaser seat, 6-low-voltage casing, 7-intermediate casing, 8-high-voltage casing and 9-high-voltage driving motor.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to fall within the scope of the invention.
As shown in fig. 1 to 3, the present invention provides an aeroengine twin rotor-support-case tester comprising a low pressure rotor 1, a central bevel gear system 3 and a high pressure rotor 2 arranged in transverse succession, wherein: the low-pressure rotor 1, the central bevel gear system 3 and the high-pressure rotor 2 are fixed on a frame 5 through a supporting structure 4, a low-pressure casing 6 is arranged on the periphery of the low-pressure rotor 1, an intermediate casing 7 is arranged on the periphery of the central bevel gear system 3, a high-pressure casing 8 is arranged on the periphery of the high-pressure rotor 2, and the low-pressure casing 6, the intermediate casing 7, the high-pressure casing 8, the low-pressure rotor 1 and the high-pressure rotor 2 are all coaxially arranged and supported by the supporting structure 4; the low-pressure rotor 1 comprises a low-pressure turbine shaft 13, and the low-pressure turbine shaft 13 penetrates through the central bevel gear system 3 and is rotationally connected with the high-pressure rotor 2 and the central bevel gear system 3, so that a 5# fulcrum and a 3# fulcrum are formed; the low-voltage rotor 1 is driven by a low-voltage drive motor 16, the central bevel gear system 3 is connected to a high-voltage drive motor 9, and the high-voltage rotor 2 is driven by the central bevel gear system 3. The low-pressure rotor 1 and the high-pressure rotor 2 are mutually coupled, so that the coupling characteristic of the double-rotor aeroengine can be better reflected.
Specifically, as shown in fig. 5, the low-pressure rotor 1 of the present invention comprises a low-pressure fan section rotor and a low-pressure turbine rotor, the low-pressure fan section rotor comprises a fan rotating shaft 11 and a four-stage fan disc 12 sleeved on the fan rotating shaft 11, similar to a fan section of a prototype machine, the low-pressure fan section rotor of a tester is also called a low-pressure compressor, and is mainly characterized in that a 1-stage disc and a 1-stage drum are combined with each other to form a 1-stage disc drum of the fan, a 2-stage disc drum and a 3-stage disc drum are the same, the disc is a hollow disc, and the drum is a thin-wall cylinder. The four-stage fan disc 12 comprises three sections, wherein the first section comprises a fan 1-stage disc drum and a fan 2-stage disc drum, the second section comprises a 3-stage disc drum, the third section comprises a 4-stage disc, the first section disc drum is integrally welded to form a structural member, the second section disc drum is identical to the first section disc drum, and the first section disc drum, the second section disc drum and the third section disc drum are all connected through bolts; the low-pressure turbine rotor comprises a low-pressure turbine shaft 13, a low-pressure turbine cone shell 14 and a low-pressure turbine disc 15, wherein the low-pressure turbine cone shell 14 and the low-pressure turbine disc 15 are sleeved on the low-pressure turbine shaft 13, the low-pressure turbine cone shell 14 is fixedly arranged at the outer end of the low-pressure turbine disc 15, the fan rotating shaft 11 is connected with the low-pressure turbine shaft 13 through a sleeve gear coupler 17, and the low-pressure driving motor 16 is connected with the fan rotating shaft 11 through a diaphragm coupler and drives the low-pressure rotor 1 to operate.
Specifically, as shown in fig. 6, the high-pressure rotor 2 of the present invention includes a high-pressure front arm shaft 21, a high-pressure compressor 9-stage disk 22, a high-pressure turbine shaft 23, a high-pressure turbine disk 24, a high-pressure turbine cone shell 25, and an intermediate bearing 26, wherein: the high-pressure front arm shaft 21 is a hollow shaft, the front section of the shaft is provided with a spline, the spline is connected with the central gear system 3, and the rear section of the shaft is connected with the 9-stage wheel disc 22 of the high-pressure compressor through a bolt; the 9-stage wheel disc 22 of the high-pressure compressor is divided into three sections, wherein the first section comprises a front three-stage disc drum, the third-stage disc drum comprises cone shell structures similar to the original model, the second section comprises 4, 5 and 6-stage disc drums, the drum barrel of the 6-stage disc drum comprises cone shell structures similar to the original model, and the third section consists of 7, 8, 9-stage disc drums and a 1-stage sealing disc 221; the first section of the disc drum is integrally welded to form a structural member, the second section is identical to the first section, the first section is connected with the second section in a bolt mode, and the second section is connected with the third section in a long bolt mode; the high-pressure turbine disc 24 is rigidly connected with a part of the high-pressure compressor 9-stage wheel disc 22 through a high-pressure turbine shaft 23, and a high-pressure turbine cone shell 25 is fixedly connected with the high-pressure turbine disc 24; the high-pressure turbine cone 25 and the low-pressure turbine shaft 13 are connected by an intermediate bearing 26, where a 5# fulcrum is formed, the 5# fulcrum is an intermediate fulcrum, and the intermediate bearing 26 is preferably a roller bearing. It will be appreciated that the low pressure turbine shaft 13 is coaxial with the high pressure rotor 2 and extends through the high pressure rotor 2 and is coupled to the high pressure rotor via the intermediate bearing 26, which better reflects the coupling characteristics of a dual rotor aero-engine.
Specifically, as shown in fig. 7, the central bevel gear system 3 of the present invention utilizes a central bevel gear structure to realize power driving of a high-pressure rotor, and mainly includes a speed increaser 31, a long coupling 32, a central bevel gear box 33, a driving bevel gear 34 and a driven bevel gear 35, wherein the driving direction is opposite to that of a prototype, but the central bevel gear structure is similar to the prototype, and the transmission ratio of the central bevel gear is consistent with that of the prototype, so as to ensure consistent stress of the high-pressure front arm shaft 21 and the high-pressure turbine shaft 23. Meanwhile, considering the problem of limited structure of the tester, the midspan form of the drive bevel gear 34 of the prototype is changed into a cantilever form, the stability of the drive bevel gear 34 is ensured by using a two-point support long span shaft, and the central bevel gear box 33 is fixed on the support structure 4 through bolts and is fixed on the frame 5 at the same time. The speed increaser 31 is connected with the high-voltage driving motor 9 through a coupler, the speed increaser 31 drives the driving bevel gear 34 through the long coupler 32, the driving bevel gear 34 is in meshed connection with the driven bevel gear 35, and the driven bevel gear 35 is in matched connection with the high-voltage front arm shaft 21 through a spline so as to drive the high-voltage rotor 2 to rotate, so that power transmission of a high-voltage part is completed. The design of the central bevel gear system is consistent with the real engine power transmission path, and the directions of the central bevel gear system and the real engine power transmission path are opposite.
Specifically, as shown in fig. 8 to 14, the support structure 4 mainly provides a fulcrum for the fan rotation shaft 11, the low-pressure turbine shaft 13, the high-pressure front arm shaft 21, and the like, while providing a hanging point for the low-pressure casing 6, the intermediate casing 7, the high-pressure casing 8, and the center cone gear box 33 to fix the casing and the center cone gear box. The support structure 4 comprises a first support structure 41, a second support structure 42, a third support structure 43 and a fourth support structure 44, the first support structure 41 and the fourth support structure 44 being for supporting the low pressure rotor 1, the second support structure 42 being for supporting the low pressure rotor 1 and the central bevel gear box 33, the third support structure 43 being for supporting the high pressure rotor 2, the third support structure 43 being an elastic support structure. The machine case is a stator machine case and is mainly used for simulating a thin-wall machine case in a real engine.
Specifically, as shown in fig. 8 to 11, the first supporting structure 41 of the present invention includes a No. 1 web 411, a No. 1 bearing cone 412, a No. 1 bearing seat 413, a No. 1 squirrel cage 414, a No. 1 bearing 415, and a No. 1 hanging point 416, where one end of the fan rotating shaft 11 is rotatably connected to the first supporting structure 41 through the No. 1 bearing 415, here, a No. 1 fulcrum; the second support structure 42 includes a number 2 web 421, a number 2 bearing block 422, a number 2 bearing 423, and a number 2 hanging point 424, and the other end of the fan rotating shaft 11 is rotationally connected with the second support structure 42 through the number 2 bearing 422, which is a number 2 fulcrum here; the third supporting structure 43 comprises a number 3 amplitude plate 431, a number 3 bearing cone shell 432, a number 3 squirrel cage 433, a number 3 bearing seat 434, a number 3 bearing 435 and a number 3 hanging point 436, and the high-pressure front axle arm 21 is rotatably connected with the third supporting structure 43 through the number 3 bearing 435, wherein the high-pressure front axle arm is a number 4 fulcrum; the preferred number 3 bearing is a ball bearing; the fourth support structure 44 includes a number 4 web 441, a number 4 force bearing cone 442, a number 4 squirrel cage 443, a number 4 bearing housing 444, a number 4 bearing 445, and a number 4 hitch point 446, and the low pressure turbine shaft 13 is rotatably connected to the fourth support structure 44 by a number 4 bearing 445, here a number 6 fulcrum. The first supporting structure 41 is fixed on the frame 5 through a No. 1 hanging point 416, and the fixing mode can be selected as bolt fixing; the second support structure 42 is fixed on the frame 5 through a hanging point 424 of number 2, and the fixing mode is preferably bolt fixing; the third supporting structure 43 is fixed on the frame 5 through a hanging point 436, and the fixing mode is preferably bolt fixing; the fourth support structure 44 is fastened to the frame 5 by means of a number 4 suspension point 446, preferably by means of bolts. According to the invention, the No. 1 spoke 411, the No. 2 spoke 421, the No. 3 spoke 431 and the No. 4 spoke 441 are large discs with hollowed-out middle parts, so that the rigidity is high, and the deformation is difficult; the bearing cone shell 412, the bearing cone shell 432 and the bearing cone shell 442 are of conical hollow structures, the rigidity is low, one larger end of the bearing cone shell is fixed on a web through bolts, the smaller end of the bearing cone shell is fixed with a squirrel cage through bolts, and the squirrel cage is of a cylindrical structure, the hollow part of the bearing cone shell is designed to be changed into ribs, so that the squirrel cage is low in rigidity and good in elasticity; the other end of the squirrel cage is connected with the bearing seat through a bolt, and the elastic squirrel cage can play a role in damping vibration from the bearing seat. The supporting structure of the squirrel cage, the cone shell and the web plate is similar to a supporting structure of a real engine, comprises the elastic squirrel cage with a vibration damping effect, simplifies cone shell and web plate structures in the real engine, is consistent with a vibration transmission path of the real engine, and can better simulate the vibration condition of the aeroengine.
Specifically, as shown in fig. 4, the low-pressure casing 6 of the present invention is fixed on the No. 1 and No. 2 webs 411 and 421, the middle casing 7 is fixed on the No. 2 and No. 3 webs 421 and 431, the high-pressure casing is fixed on the No. 3 and No. 4 webs 431 and 441, and the casing of the tester is convenient for measuring vibration signals for comparing the internal vibration signals of the rotors and researching the vibration transmission law of the dual-rotor-support-casing.
Specifically, as shown in fig. 15, the frame 5 of the present invention includes a rotor system frame 51 and a high-pressure transmission system frame 52, and the frame 5 mainly provides mounting references and platforms for the high-pressure rotor 2, the low-pressure rotor 1 and transmission systems thereof; the frame 5 is fixed to the ground by means of expansion bolts via a frame leg 511, the low-voltage drive motor 16 is fixed to the low-voltage motor mount 512 of the rotor system frame 51 by means of bolts, the support structure 4 is fixed to the rotor system frame 51 by means of bolts, the high-voltage drive motor 9 is fixed to the high-voltage motor mount 521 of the high-voltage transmission system frame 52 by means of bolts, and the speed increaser 31 is fixed to the speed increaser mount 522 of the high-voltage transmission system frame 52 by means of bolts. The frame 5 is of a frame structure, the inside of the frame is hollow, the weight is light, the frame has certain rigidity, and the frame is convenient to install.
Specifically, the four-stage fan disc 12, the high-pressure compressor 9-stage wheel disc 22, the low-pressure turbine disc 15 and the high-pressure turbine disc 24 are provided with a plurality of bolt holes in the circumferential direction of the wheel disc edges, so that unbalanced mass can be conveniently applied, and the phase and the magnitude of the unbalanced mass can be adjusted according to the positions of the added screws and the mass of the screws.
The double-rotor-support-casing tester for the aero-engine is simple and reasonable in structure and comprehensive in consideration. According to the real engine structure, a fixed-proportion (such as 2:1) scale design is adopted, and the fan four-stage disc and high-pressure nine-stage disc structures are consistent with the real engine. The structures of a squirrel cage, a cone shell, a bearing amplitude plate, a flexible casing and the like in the true machine are reserved. Compared with most domestic rotor testers, the structure form of rigid support of the disc shaft is adopted, the influence of the disc-drum coupling structure, double-rotor high-low-pressure coupling and elastic support on the rotor vibration characteristics is not considered, the structure and the vibration of an engine rotor system can be truly simulated, and the whole machine vibration research requirement of an aeroengine is met.
The double-rotor-support-casing tester for the aero-engine can effectively realize vibration transmission and test among the rotor, the support structure and the casing, and has similarity with the structure of a real engine and similarity with dynamic characteristics compared with the prior tester.
The invention also provides a testing method which is mainly used for researching the vibration transmission coupling rule of the double-rotor-support-casing and comprises the steps of pulling Ding Chao cubic group sampling, self-adaptive filtering, numerical calculus, a deep learning algorithm and a neural network model. The Latin hypercube group sampling is mainly adopted, 100 groups of unbalance and unbalance phase combinations are randomly extracted, the positions of a four-stage fan disc 12, a high-pressure compressor 9-stage wheel disc 22, a high-pressure turbine disc 24 and a low-pressure turbine disc 15 are respectively arranged for testing, vibration displacement from a No. 1 supporting point to a position near a No. 6 supporting point is extracted under different rotating speeds, vibration acceleration at positions of a No. 1 amplitude plate 411, a No. 1 bearing cone shell 412, a No. 1 bearing seat 413, a No. 1 squirrel cage 414, a No. 2 amplitude plate 421, a No. 3 amplitude plate 431, a No. 3 bearing cone shell 432, a No. 3 squirrel cage 433, a No. 3 bearing seat 434, a No. 4 amplitude plate 441, a No. 4 bearing cone shell 442, a No. 4 squirrel cage 443 and a No. 4 bearing seat 444 is extracted, and vibration acceleration at positions of a low-pressure box 6, an intermediate box 7 and a high-pressure box 8 is extracted. The vibration sensor is in the same dimension, is convenient to analyze, and can be used for carrying out numerical integration conversion on the tested acceleration signal to obtain a vibration speed, and carrying out numerical differentiation conversion on the vibration displacement signal to obtain a vibration speed signal. Training the neural network model by using the obtained 100 groups of test data by using a deep learning algorithm, and analyzing the vibration transmission coupling rule of the double-rotor-support-casing.
The test method of the invention comprises the following steps:
(1) Sampling by using Latin hypercube groups, and determining the unbalance amount and the phase to be added;
(2) Setting the rotating speed of a low-voltage driving motor, enabling a low-voltage rotor to rotate, enabling a high-voltage rotor not to rotate, and extracting vibration data of each test point;
(3) Setting the rotating speed of a high-voltage driving motor, enabling a high-voltage rotor to rotate, enabling a low-voltage rotor not to rotate, and extracting vibration data of each test point;
(4) Simultaneously setting the rotating speed of the low-voltage driving motor and the rotating speed of the high-voltage driving motor, so that the low-voltage rotor rotates and the high-voltage rotor rotates, and extracting vibration data of each test point;
(5) Repeating the steps (1) - (4) until 100 groups of unbalanced working conditions of sampling are completed;
(6) And (3) carrying out self-adaptive filtering on the measuring point signals to remove interference components, converting the acceleration signals into vibration speeds through numerical integration, converting the displacement signals into vibration displacements through numerical differentiation, and unifying the dimensions of vibration data.
(7) Training the neural network model by using the obtained test data through a deep learning algorithm, and analyzing the vibration transmission coupling rule of the double-rotor-support-casing.
The test method provided by the invention can measure vibration data of a plurality of positions relative to a true machine.
The invention has been further described with reference to specific embodiments, but it should be understood that the detailed description is not to be construed as limiting the spirit and scope of the invention, but rather as providing those skilled in the art with the benefit of this disclosure with the benefit of their various modifications to the described embodiments.
Claims (4)
1. An aeroengine twin rotor-support-case tester comprising a low pressure rotor, a central bevel gear system and a high pressure rotor arranged in transverse succession, wherein:
the low-pressure rotor, the central bevel gear system and the high-pressure rotor are fixed on the frame through a supporting structure, a low-pressure box is arranged on the periphery of the low-pressure rotor, an intermediate box is arranged on the periphery of the central bevel gear system, a high-pressure box is arranged on the periphery of the high-pressure rotor, and the low-pressure box, the intermediate box, the high-pressure box, the low-pressure rotor and the high-pressure rotor are all coaxially arranged and supported by the supporting structure;
the low-pressure rotor comprises a low-pressure turbine shaft, and the low-pressure turbine shaft penetrates through the central bevel gear system and is rotationally connected with the high-pressure rotor and the central bevel gear system;
the low-voltage rotor is driven by a low-voltage driving motor, the central bevel gear system is connected with a high-voltage driving motor, and the high-voltage rotor is driven by the central bevel gear system;
the low-pressure rotor comprises a low-pressure fan section rotor and a low-pressure turbine rotor, the low-pressure fan section rotor comprises a fan rotating shaft and a four-stage fan disc sleeved on the fan rotating shaft, the four-stage fan disc comprises a 1-stage disc drum, a 2-stage disc drum, a 3-stage disc drum and a 4-stage disc which are sequentially arranged, and the disc drum is formed by combining a 1-stage disc and a 1-stage drum; the low-pressure turbine rotor comprises a low-pressure turbine shaft, a low-pressure turbine cone shell and a low-pressure turbine disc, wherein the low-pressure turbine cone shell and the low-pressure turbine disc are sleeved on the low-pressure turbine shaft, the low-pressure turbine cone shell is fixedly arranged at the outer end of the low-pressure turbine disc, the fan rotating shaft is connected with the low-pressure turbine shaft through a coupler, and the low-pressure driving motor is connected with the fan rotating shaft;
the high-pressure rotor comprises a high-pressure front arm shaft, a high-pressure compressor 9-stage wheel disc, a high-pressure turbine shaft, a high-pressure turbine disc, a high-pressure turbine cone shell and an intermediate bearing, wherein:
the high-pressure front arm shaft is a hollow shaft, the front end of the high-pressure front arm shaft is connected with the central bevel gear system, and the rear end of the high-pressure front arm shaft is connected with the 9-stage wheel disc of the high-pressure compressor; the high-pressure turbine disc is rigidly connected with a part of the high-pressure compressor 9-stage disc through the high-pressure turbine shaft, and the high-pressure turbine cone shell is fixedly connected to the outer end of the high-pressure turbine disc;
the high-pressure turbine cone shell is connected with the low-pressure turbine shaft through the intermediate bearing;
the central bevel gear system comprises a speed increaser, a long coupler, a central bevel gear box, a driving bevel gear and a driven bevel gear, wherein:
the speed increaser is connected with the high-voltage driving motor, the speed increaser drives the driving bevel gear through the long coupler, the driving bevel gear is meshed with the driven bevel gear, and the driven bevel gear is matched and connected with the high-voltage front arm shaft so as to drive the high-voltage rotor to rotate;
the support structure comprises a first support structure, a second support structure, a third support structure and a fourth support structure, wherein the first support structure and the fourth support structure are used for supporting the low-pressure rotor, the second support structure is used for supporting the low-pressure rotor and the central bevel gear box, the third support structure is used for supporting the high-pressure rotor, and the third support structure is an elastic support structure;
the first supporting structure comprises a No. 1 amplitude plate, a No. 1 bearing cone shell, a No. 1 bearing seat, a No. 1 mouse cage and a No. 1 bearing, and one end of the fan rotating shaft is rotationally connected with the first supporting structure through the No. 1 bearing;
the second supporting structure comprises a No. 2 amplitude plate, a No. 2 bearing seat and a No. 2 bearing, and the other end of the fan rotating shaft is rotationally connected with the second supporting structure through the No. 2 bearing;
the third supporting structure comprises a No. 3 amplitude plate, a No. 3 bearing cone shell, a No. 3 mouse cage, a No. 3 bearing seat and a No. 3 bearing, and the middle part of the high-pressure front axle arm is rotationally connected with the third supporting structure through the No. 3 bearing;
the fourth supporting structure comprises a No. 4 amplitude plate, a No. 4 bearing cone shell, a No. 4 mouse cage, a No. 4 bearing seat and a No. 4 bearing, and the low-pressure turbine shaft is rotationally connected with the fourth supporting structure through the No. 4 bearing;
the low-pressure box is fixed on the No. 1 web and the No. 2 web, the middle box is fixed on the No. 2 web and the No. 3 web, and the high-pressure box is fixed on the No. 3 web and the No. 4 web.
2. The aircraft engine twin rotor-support-case tester according to claim 1, wherein the frame comprises a rotor system frame and a high-voltage transmission system frame, the low-voltage drive motor being fixed to the rotor system frame, the high-voltage drive motor and the speed increaser being fixed to the high-voltage transmission system frame.
3. The aircraft engine double rotor-bearing-casing tester according to claim 1, wherein the four-stage fan disc, the 9-stage disc of the high-pressure compressor, the low-pressure turbine disc and the high-pressure turbine disc are provided with a plurality of bolt holes in the circumferential direction of the disc edges.
4. A testing method based on the aeroengine double rotor-support-casing tester according to any one of claims 1-3, characterized by comprising the steps of:
(1) Sampling by using Latin hypercube groups, and determining the unbalance amount and the phase to be added;
(2) Setting the rotating speed of a low-voltage driving motor, enabling a low-voltage rotor to rotate, enabling a high-voltage rotor not to rotate, and extracting vibration data of each test point;
(3) Setting the rotating speed of a high-voltage driving motor, enabling a high-voltage rotor to rotate, enabling a low-voltage rotor not to rotate, and extracting vibration data of each test point;
(4) Simultaneously setting the rotating speed of the low-voltage driving motor and the rotating speed of the high-voltage driving motor, so that the low-voltage rotor rotates and the high-voltage rotor rotates, and extracting vibration data of each test point;
(5) Repeating the steps (1) - (4) until 100 groups of unbalanced working conditions of sampling are completed;
(6) The measuring point signals are subjected to self-adaptive filtering, interference components are removed, the acceleration signals are converted into vibration speeds through numerical integration, the displacement signals are converted into vibration displacements through numerical differentiation, and the dimensions of vibration data are unified;
(7) Training the neural network model by using the obtained test data through a deep learning algorithm, and analyzing the vibration transmission coupling rule of the double-rotor-support-casing.
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