CN113295425B - Experimental device for simulating motor flight aeroengine rotor and using method - Google Patents

Experimental device for simulating motor flight aeroengine rotor and using method Download PDF

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Publication number
CN113295425B
CN113295425B CN202110570638.9A CN202110570638A CN113295425B CN 113295425 B CN113295425 B CN 113295425B CN 202110570638 A CN202110570638 A CN 202110570638A CN 113295425 B CN113295425 B CN 113295425B
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rotor
motor
bearing
shaft
drum
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CN113295425A (en
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潘五九
郝军凯
曲浩永
苓亮鱼
王明海
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Shenyang Aerospace University
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Shenyang Aerospace University
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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
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • 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
    • G01M13/02—Gearings; Transmission mechanisms
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M7/00—Vibration-testing of structures; Shock-testing of structures
    • G01M7/02—Vibration-testing by means of a shake table
    • G01M7/022—Vibration control arrangements, e.g. for generating random vibrations

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  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

An experimental device for simulating a maneuvering aeroengine rotor and a using method thereof comprise a base; two bearing frame I on the base are connected with total supporting shaft one end respectively, the other end rotates the installation with bearing frame II on the swing arm, bearing frame III and the rocker back shaft that the swing arm top set up are connected, first motor and first reduction gear are fixed through first cushion, first reduction gear output shaft passes through the crank and is connected with a supporting beam one end, supporting beam other end suit is on the rocker back shaft, a supporting beam is connected with the resin protection shield, the bottom plate upper surface of resin protection shield has set gradually installation second motor and second reduction gear second cushion, the bearing frame I of spiro union bearing frame V and the bearing frame cushion II of spiro union bearing frame VI, second reduction gear output shaft passes through elastic coupling and is connected with drum-type rotor. The whole rotor system is driven to move by the action of two motors in the adjusting disc drum type rotor mounting base, and the vibration response condition of the rotor system is simulated when the airplane does different maneuvering actions.

Description

Experimental device for simulating motor flight aeroengine rotor and using method
Technical Field
The invention belongs to the technical field of rotor vibration, and particularly relates to an experimental device for simulating a motor flight aeroengine rotor and a using method thereof.
Background
The drum rotor in the two major rotor systems has good bending rigidity and good disc rotor strength, and the disc-drum rotor combines the advantages of the two rotors, has good bending rigidity and higher strength, and is widely applied to aeroengines. The disc drum type rotor consists of a disc, a drum and a shaft, wherein the disc and the drum at each stage are connected or welded together.
In the classical rotor dynamics theory, the rotating shaft is regarded as a slender beam, and the rotating shaft in a single shaft section is of a continuous structure. Correspondingly, the rotor test bed mostly adopts a solid slender beam with a circular section as a rotating shaft, and a disc is fixed on the rotating shaft to form a rotor system. The document "MatIsa, A.A., Penny, J.E.T.and Garvey, S.D.dynamics of thinned and extended rotors. proceedings of the International Analysis Conference-IMAC, san Antonio, Texas,2000,1, 867. other than 872 ] modifies a disk at the center of the rotor axis of a Jeffcott rotor into two half disks connected by circumferentially evenly distributed bolts to construct a bolted rotor system. The literature [ Liu, S.G., Ma, Y.H., Zhang, D.Y., Hong, J.Studies on dynamic characteristics of the joint in the aero-engine System, mechanical System and Signal Processing,2012,29:120-136 ] carries out theoretical and experimental research on the dynamic characteristics of a bolt-connected rotor System, and the related rotor test bed connects two shaft sections together through a flange. The two documents research the influence of bolt connection on the dynamic characteristics of the rotor, but the research only shows that the mechanical characteristics in the rotor system under the condition that the rotor rotates as the main motion cannot accurately simulate the internal mechanical characteristics of the rotor and the external load when the airplane does maneuvering action, and meanwhile, most of the existing experimental devices cannot represent the problems of thin-wall cylindrical shells of drum drums in drum-type rotors and the flange-bolt connection structural characteristics between the drum drums and wheel discs.
Disclosure of Invention
The invention aims to provide an experimental device for simulating a maneuvering flight aircraft engine rotor and a using method thereof, and solves the problems that in the prior art, mechanical characteristics in a subsystem are only under the condition that the rotor rotates as a main motion, the mechanical characteristics in the rotor and the internal part of an airplane under the action of external load cannot be accurately simulated, and meanwhile, most of the existing experimental devices cannot represent the structural characteristics of a drum barrel thin-wall cylindrical shell drum in a drum-type rotor and the flange-bolt connection between the drum barrel and a wheel disc.
In order to achieve the purpose, the invention adopts the following technical scheme:
an experimental device for simulating a maneuvering flight aircraft engine rotor comprises a base, a swing arm, a supporting beam, a main supporting shaft, a resin protecting plate and a bearing seat I; the top parts of two beams which are arranged in parallel are respectively provided with a bearing seat I through bolts, one ends of two main supporting shafts are respectively rotatably arranged with the bearing seats I, the other ends of the two main supporting shafts are rotatably arranged with the bearing seats II, the bearing seats II are arranged at the bottom parts of the side walls of the swing arms through bolts, the top parts of the side walls of the swing arms are provided with bearing seats III, a rocker supporting shaft is rotatably arranged between the two bearing seats III, the first motor and a first speed reducer connected with the first motor are respectively fixed through a first cushion block, the output shaft of the first speed reducer is connected with one end of a crank through an elastic coupling, the two ends of the lower surface of the supporting beam are respectively provided with a bearing seat IV, the bearing seat IV at one end of the supporting beam is connected with the other end of the crank, the bearing seat IV at the other end of the supporting beam is sleeved on the rocker supporting shaft, the middle part of the upper surface of the supporting beam is connected with one end of the supporting beam through a thick angle code, the other end of the supporting column is connected with the resin protection plate through a thick angle code, a second cushion block, a bearing block cushion block I and a bearing block cushion block II are sequentially arranged on the upper surface of a bottom plate of the resin protection plate, a second motor and a second speed reducer connected with the second motor are arranged on the second cushion block, a bearing block V is connected on the bearing block cushion block I through a bolt, a bearing block VI is connected on the bearing block cushion block II through a bolt, an output shaft of the second speed reducer is connected with one end of an optical shaft I through an elastic coupling and the bearing block V, the other end of the optical shaft I is connected with a central hole of a thin-wall flange I, the bearing block VI is connected with one end of an optical shaft II, the other end of the optical shaft II is connected with a central hole of the thin-wall flange II, the thin-wall flange I is connected with the thin-wall flange II through an aviation bolt, the thin-wall flange I, the thin-wall flange II, the optical shaft I and the optical shaft II form a drum rotor, acceleration sensors are arranged on the bearing block V and the bearing block VI, and the acceleration sensor, the first motor and the second motor are all connected with the vibration testing system.
The resin protection board comprises bottom plate, long curb plate and short curb plate, two the lug that long curb plate set up through its long limit is pegged graft with the recess of the long limit department of bottom plate respectively, and two short curb plates are pegged graft with the recess of bottom plate minor face department respectively through the lug that sets up on it, and the lug of long curb plate minor face department is pegged graft with the recess on the short curb plate.
The base is formed by connecting five equal-length aluminum profiles into a whole through bolts and corner connectors.
The thin-wall flange I, the thin-wall flange II, the optical axis I and the optical axis II are all made of the same material.
At least one disc drum rotor is arranged on the resin protection plate.
The use method of the experimental device for simulating the rotor of the maneuvering flight aeroengine comprises the following steps:
step 1, installing a drum rotor, screwing bolts on a bearing seat V and a bearing seat VI, fixing the drum rotor on a bottom plate of a resin protection plate through the bearing seat V and the bearing seat VI, adjusting the pretightening force of an aviation bolt on the drum rotor, connecting a first motor, a second motor and an acceleration sensor with a computer in a vibration test system, starting the second motor, driving the drum rotor to rotate at a high speed through a second speed reducer and an elastic coupling when the second motor works, measuring the rotating speed through a handheld non-contact rotating speed measuring instrument, and when the rotating speed reaches an experimental set rotating speed, enabling the internal mechanical characteristics of the drum rotor to be consistent with the mechanical characteristics of the drum rotor in the aero-engine;
and 2, starting a first motor, driving a crank to rotate axially by the first speed reducer and an elastic coupling when the first motor works, pulling a supporting beam by the circumferential rotation of the crank, pulling a rocker supporting shaft to swing by the supporting beam, starting the disc-drum type rotor to periodically and reciprocally swing at the moment, enabling the internal mechanical characteristics of the disc-drum type rotor to be consistent with the internal mechanical characteristics of an aircraft engine when the aircraft does maneuvering action, closing the first motor firstly after the set time is not more than two flight periods after the experimental device runs to the set time measured by a computer, closing a second motor after the supporting beam and the rocker supporting shaft stop working, finishing the experiment data fed back by an acceleration sensor through the computer in a vibration test system, and analyzing and arguing the acquired experiment data.
The invention has the technical effects that:
1. the experimental device drives the whole rotor system to move by the action of the two motors in the adjusting disc drum type rotor mounting base, and the vibration response condition of the rotor system when the airplane does different maneuvering actions is simulated.
2. In the experimental device, the middle wheel disc is connected with the drum drums on the two sides through the flange, so that the real connection boundary condition of the drum-type rotor can be reflected, the vibration of the rotor under different bolt pretightening force conditions can be measured, and the influence of bolt connection on the dynamic characteristics of the drum-type rotor can be explored.
3. The whole structure of the device has great flexibility, and the stress condition and the vibration characteristic of the internal structure of the single-shot, double-shot or even multiple-shot warplane in different engines during maneuvering flight can be respectively simulated by properly adjusting the number and the positions of the rotor systems.
4. Any two parts in the device are connected in an adjustable and detachable mode, the geometric characteristics of the four-bar mechanism on the test bed can be changed by adjusting the position of the fixing bolt in the supporting mechanism, and therefore the vibration amplitude and strength of the supported part are changed under the condition that the rotating speed of the motor is not changed.
Drawings
FIG. 1 is a schematic view of an experimental apparatus for a bolted rotor system of an aircraft engine for simulating maneuvering flight according to the invention from a first perspective;
FIG. 2 is a schematic view of an experimental apparatus for a bolted rotor system of an aircraft engine for simulating maneuvering flight according to the invention from a second perspective;
FIG. 3 is a sectional view of a part of the structure of an aircraft bolt of an aircraft engine bolt connection rotor system experimental device for simulating maneuvering flight according to the invention;
the method comprises the following steps of 1-base, 2-first motor, 3-first cushion block, 4-bearing block I, 5-total support shaft, 6-bearing block II, 7-swing arm, 8-bearing block III, 9-rocker support shaft, 10-elastic coupling I, 11-crank, 12-support beam, 13-bearing block IV, 14-support column, 15-thick corner brace, 16-resin protection plate, 17-second cushion block, 18-bearing block I, 19-bearing block II, 20-second motor, 21-bearing block V, 22-bearing block VI, 23-optical axis I, 24-optical axis II, 25-thin-wall flange I, 26-thin-wall flange II and 27-aviation bolt.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples.
As shown in fig. 1 to 3, an experimental device for simulating a rotor of a maneuvering flight aircraft engine comprises a base 1, a swing arm 7, a support beam 12, a general support shaft 5, a resin protection plate 16 and a bearing seat i 4; the top of one group of two beams which are arranged in parallel on the base 1 is provided with a bearing seat I4 through a bolt, one end of each of two main supporting shafts 5 is rotatably arranged with the bearing seat I4, the other end of each main supporting shaft is rotatably arranged with the bearing seat II 6, the bearing seat II 6 is arranged at the bottom of the side wall of the swing arm 7 through a bolt, the top of the side wall of the swing arm 7 is provided with a bearing seat III 8, a rocker supporting shaft 9 is rotatably arranged between the two bearing seats III 8, the first motor 2 and a first speed reducer connected with the first motor 2 are fixed through a first cushion block 3, the output shaft of the first speed reducer is connected with one end of a crank 11 through an elastic coupling I10, the two ends of the lower surface of the supporting beam 12 are respectively provided with a bearing seat IV 13, the bearing seat IV 13 at one end of the supporting beam 12 is connected with the other end of the crank 11, and the bearing seat IV 13 at the other end of the supporting beam 12 is sleeved on the rocker supporting shaft 9, the middle of the upper surface of the support beam 12 is connected with one end of a support column 14 through a thick corner connector 15, the other end of the support column 14 is connected with a resin protection plate 16 through the thick corner connector 15, the upper surface of the bottom plate of the resin protection plate 16 is sequentially provided with a second cushion block 17, a bearing block I18 and a bearing block II 19, the bearing block I18 and the bearing block II 19 are matched with a long hole in the bottom plate of the resin protection plate 16 through bolts, the bearing block I18 and the bearing block II 19 are fixed on the bottom plate of the resin protection plate 16, the positions of the bearing block I18 and the bearing block II 19 relative to the bottom plate are adjustable due to the arrangement of the long hole, the second cushion block 17 is provided with a second motor 20 and a second speed reducer connected with the second motor 20, the bearing block V21 is connected on the bearing block I18 through bolts, and a bearing block VI 22 is connected on the bearing block II 19 through bolts, the output shaft of the second reducer is connected with one end of an optical shaft I23 through an elastic coupling II and a bearing seat V21, the other end of the optical shaft I23 is connected with an integrally formed round sleeve at the center of a thin-wall flange I25 in a welding mode, a bearing seat VI 22 is connected with one end of an optical shaft II 24, the other end of the optical shaft II 24 is connected with an integrally formed round sleeve at the center of a thin-wall flange II 26 in a welding mode, the thin-wall flange I25 is connected with a thin-wall flange II 26 through an aviation bolt 27, different pretightening forces under different states are researched through adjusting the pretightening force required by the aviation bolt 27, the aviation bolt 27 can simulate the fastening condition of a connecting piece in an aircraft engine rotating at high speed when the aircraft rolls transversely, the thin-wall flange I25, the thin-wall flange II 26, the optical shaft I23 and the optical shaft II 24 form a drum rotor, the drum rotor is consistent with the real structure of the aircraft engine rotor, and acceleration sensors are installed on the bearing seat V21 and the bearing seat VI 22, and the acceleration sensor, the first motor 2 and the second motor 20 are all connected with a computer in the vibration test system, the model of the acceleration sensor is 1A102E, and the model of the vibration test system is DH 5922D.
The resin protection board 16 comprises bottom plate, long curb plate and short curb plate, two the lug that long curb plate set up through its long limit is pegged graft with the recess of the long limit department of bottom plate respectively, and two short curb plates are pegged graft with the recess of bottom plate minor face department respectively through the lug that sets up on it, and the lug of long curb plate minor face department is pegged graft with the recess on the short curb plate.
The base 1 is formed by connecting five equal-length aluminum profiles into a whole through bolts and corner connectors.
The thin-wall flange I25, the thin-wall flange II 26, the optical axis I23 and the optical axis II 24 are all made of the same material, and the mechanical characteristics of the disc drum type rotor thin-wall part in the aero-engine can be simulated to the maximum extent by adopting the mode.
At least one disc drum rotor is arranged on the resin protection plate 16, and the stress condition and the vibration characteristic of the internal structure of different aircraft engines of a single-engine or multi-engine airplane during maneuvering flight can be simulated by adjusting the number and the positions of the disc drum rotors.
All components of the experimental device are standard parts, and if the parts are damaged during the extreme maneuver of the simulated airplane, the parts can be repaired or rebuilt in a very short time, so that the stability of the research progress is ensured to the maximum extent.
The use method of the experimental device for simulating the rotor of the maneuvering flight aeroengine comprises the following steps:
step 1, installing a disc-drum rotor, screwing bolts on a bearing seat V21 and a bearing seat VI 22, fixing the disc-drum rotor on a bottom plate of a resin protection plate 16 through the bearing seat V21 and the bearing seat VI 22, then adjusting the pretightening force of an aviation bolt 27 on the disc-drum rotor, connecting a first motor 2, a second motor 20 and an acceleration sensor with a computer in a vibration test system, starting the second motor 20, driving the disc-drum rotor to rotate at a high speed through a second speed reducer and an elastic coupling when the second motor 20 works, measuring the rotating speed through a handheld non-contact rotating speed measuring instrument, and when the rotating speed reaches an experimental set rotating speed, enabling the internal mechanical characteristics of the disc-drum rotor to be consistent with the mechanical characteristics of the disc-drum rotor in the aero-engine;
step 2, starting the first motor 2, driving a crank 11 to axially rotate through a first speed reducer and an elastic coupling when the first motor 2 works, pulling a supporting beam 12 through circumferential rotation of the crank 11, pulling a rocker supporting shaft 9 to swing through the supporting beam 12, starting periodic reciprocating swing of a drum rotor at the moment, enabling internal mechanical characteristics of the drum rotor to be consistent with internal mechanical characteristics of an aircraft engine when the aircraft does maneuvering action, when a computer detects that the experimental device runs to a set time, the set time does not exceed two flight periods, firstly closing the first motor 2, after the supporting beam 12 and the rocker supporting shaft 9 stop working, closing the second motor 20, finishing the experiment, arranging experimental data fed back by an acceleration sensor through a computer in a vibration testing system, and analyzing and arguing the acquired experimental data.

Claims (5)

1. The use method of the experimental device for simulating the motor flight aeroengine rotor comprises a base, a swing arm, a support beam, a main support shaft, a resin protection plate and a bearing seat I; the top parts of two beams which are arranged in parallel are respectively provided with a bearing seat I through bolts, one ends of two main supporting shafts are respectively rotatably arranged with the bearing seats I, the other ends of the two main supporting shafts are rotatably arranged with the bearing seats II, the bearing seats II are arranged at the bottom parts of the side walls of the swing arms through bolts, the top parts of the side walls of the swing arms are provided with bearing seats III, a rocker supporting shaft is rotatably arranged between the two bearing seats III, a first motor and a first speed reducer connected with the first motor are respectively fixed through a first cushion block, the output shaft of the first speed reducer is connected with one end of a crank through an elastic coupling, the two ends of the lower surface of the supporting beam are respectively provided with a bearing seat IV, the bearing seat IV at one end of the supporting beam is connected with the other end of the crank, the bearing seat IV at the other end of the rocker supporting beam is sleeved on the rocker supporting shaft, the middle part of the upper surface of the supporting beam is connected with one end of the supporting beam through a thick angle code, the other end of the supporting column is connected with the resin protection plate through a thick angle code, a second cushion block, a bearing block cushion block I and a bearing block cushion block II are sequentially arranged on the upper surface of a bottom plate of the resin protection plate, a second motor and a second speed reducer connected with the second motor are arranged on the second cushion block, a bearing block V is connected on the bearing block cushion block I through a bolt, a bearing block VI is connected on the bearing block cushion block II through a bolt, an output shaft of the second speed reducer is connected with one end of an optical shaft I through an elastic coupling and the bearing block V, the other end of the optical shaft I is connected with a central hole of a thin-wall flange I, the bearing block VI is connected with one end of an optical shaft II, the other end of the optical shaft II is connected with a central hole of the thin-wall flange II, the thin-wall flange I is connected with the thin-wall flange II through an aviation bolt, the thin-wall flange I, the thin-wall flange II, the optical shaft I and the optical shaft II form a drum rotor, acceleration sensors are arranged on the bearing block V and the bearing block VI, and acceleration sensor, first motor and second motor all link to each other with the vibration test system, its characterized in that includes following step:
step 1, mounting a drum rotor, screwing bolts on a bearing seat V and a bearing seat VI, fixing the drum rotor on a bottom plate of a resin protection plate through the bearing seat V and the bearing seat VI, adjusting the pretightening force of an aviation bolt on the drum rotor, connecting a first motor, a second motor and an acceleration sensor with a vibration test system, starting the second motor, driving the drum rotor to rotate at a high speed through a second speed reducer and an elastic coupling when the second motor works, measuring the rotating speed through a handheld non-contact rotating speed measuring instrument, and when the rotating speed reaches an experimentally set rotating speed, enabling the mechanical characteristics in the drum rotor to be consistent with the mechanical characteristics of the drum rotor in the aero-engine;
and 2, starting a first motor, driving a crank to rotate axially by the first speed reducer and an elastic coupling when the first motor works, pulling a supporting beam by the circumferential rotation of the crank, pulling a rocker supporting shaft to swing by the supporting beam, starting the disc-drum type rotor to periodically and reciprocally swing at the moment, enabling the internal mechanical characteristics of the disc-drum type rotor to be consistent with the internal mechanical characteristics of an aircraft engine when the aircraft does maneuvering action, closing the first motor firstly after the set time is not more than two flight periods after the experimental device runs to the set time measured by a computer, closing a second motor after the supporting beam and the rocker supporting shaft stop working, finishing the experiment data fed back by an acceleration sensor through the computer in a vibration test system, and analyzing and arguing the acquired experiment data.
2. The use method of the experimental device for simulating the rotor of the maneuvering flight aeroengine according to the claim 1, characterized in that: the resin protection board comprises bottom plate, long curb plate and short curb plate, two the lug that long curb plate set up through its long limit is pegged graft with the recess of the long limit department of bottom plate respectively, and two short curb plates are pegged graft with the recess of bottom plate minor face department respectively through the lug that sets up on it and are expanded, and the lug of long curb plate minor face department is pegged graft with the recess on the short curb plate.
3. The use method of the experimental device for simulating the rotor of the maneuvering flight aeroengine according to the claim 1, characterized in that: the base is formed by connecting five equal-length aluminum profiles into a whole through bolts and corner connectors.
4. The use method of the experimental device for simulating the rotor of the maneuvering flight aeroengine according to the claim 1, characterized in that: the thin-wall flange I, the thin-wall flange II, the optical axis I and the optical axis II are all made of the same material.
5. The use method of the experimental device for simulating the rotor of the maneuvering aviation engine according to the claim 1, is characterized in that: at least one disc drum rotor is arranged on the resin protection plate.
CN202110570638.9A 2021-05-25 2021-05-25 Experimental device for simulating motor flight aeroengine rotor and using method Active CN113295425B (en)

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Publication number Priority date Publication date Assignee Title
US4089211A (en) * 1976-11-01 1978-05-16 United Technologies Corporation Elastomeric bearing test machine
CN108776734A (en) * 2018-06-06 2018-11-09 东北大学 A kind of Analysis of response method being bolted drum barrel rotor structure
CN109163898A (en) * 2018-10-10 2019-01-08 哈尔滨电气股份有限公司 A kind of experimental rig and method for simulating rotating machinery Rolling peculiar to vessel

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