CN113295425B - An experimental device for simulating maneuvering flight aero-engine rotor and using method - Google Patents

Abstract

An experimental device for simulating a motorized flight aero-engine rotor and a method of using the same, comprising a base; two bearing seats I on the base are respectively connected with one end of a general support shaft, the other end is rotatably installed with a bearing seat II on a swing arm, and the top of the swing arm is rotatably installed. The set bearing seat III is connected with the rocker support shaft, the first motor and the first reducer are fixed by the first pad, the output shaft of the first reducer is connected with one end of the support beam through the crank, and the other end of the support beam is sleeved on the rocker support On the shaft, the support beam is connected with the resin protection plate, and the upper surface of the bottom plate of the resin protection plate is sequentially provided with the second pad for installing the second motor and the second reducer, the bearing pad pad I for screwing the bearing seat V, and the screw bearing. The bearing seat block II of seat VI, the output shaft of the second reducer is connected with the disc drum rotor through an elastic coupling. By adjusting the movements of the two motors in the drum-type rotor installation base, the overall rotor system is driven to move, simulating the vibration response of the rotor system when the aircraft performs different maneuvering actions.

Description

An experimental device for simulating a motorized flight aero-engine rotor and its use method

technical field

The invention belongs to the technical field of rotor vibration, and in particular relates to an experimental device for simulating a motorized flight aero-engine rotor and a method for using the same.

Background technique

Among the two types of rotor systems, the drum rotor has good bending rigidity and disc rotor strength, while the disc drum rotor combines the advantages of both and has good bending resistance and high strength. This structure is widely used in aero-engines. The disc drum rotor consists of a disc, a drum and a shaft, and the discs and drums at all levels are assembled by bolting or welding.

In classical rotordynamics theory, the shaft is regarded as a slender beam, and the shaft is a continuous structure within a single shaft segment. Correspondingly, most of the rotor test benches use a solid circular section slender beam as the rotating shaft, and the disc is fixed on the rotating shaft to form a rotor system. The literature [MatIsa, A.A., Penny, J.E.T. and Garvey, S.D. Dynamics of bolted and laminated rotors. Proceedings of the International Modal Analysis Conference-IMAC, San Antonio, Texas, 2000, 1, 867-872.] put the disc at the center of the Jeffcott rotor shaft It is transformed into two semi-discs connected by bolts evenly distributed in the circumferential direction, and a rotor system with bolted connection is built. Literature [Liu, S.G., Ma, Y.H., Zhang, D.Y., Hong, J. Studies on dynamic characteristics of the joint in the aero-engine rotor system. Mechanical System and Signal Processing, 2012, 29: 120-136.] on the bolted connection The dynamic characteristics of the rotor system are studied theoretically and experimentally, and the involved rotor test bench connects the two shaft segments together through flanges. The above two literatures have studied the influence of bolted connection on the dynamic characteristics of the rotor, but they only study the mechanical characteristics of the rotor system when the rotor rotates as the main motion, and cannot accurately simulate the interior of the rotor when the aircraft is maneuvering. In addition to the internal mechanical characteristics under external load, most of the existing experimental devices cannot characterize the thin-walled cylindrical shell of the drum and the structural characteristics of the flange-bolt connection between the drum and the disk.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide an experimental device and method for simulating the rotor of an aero-engine for maneuvering flight, which solves the problem that the existing technology only has mechanical characteristics in the rotor system when the rotor rotates as the main motion, and cannot accurately simulate the aircraft The internal mechanical characteristics of the rotor when an external load is added to the rotor during maneuvering. At the same time, most of the existing experimental devices cannot characterize the thin-walled cylindrical shell of the drum and the inner flange-bolt of the drum and the drum in the disk-drum rotor. Problems connecting structural features.

In order to achieve the above object, the present invention adopts the following technical solutions:

An experimental device for simulating a motorized flight aero-engine rotor, including a base, a swing arm, a support beam, a total support shaft, a resin protection plate and a bearing seat I; The bearing seat I is installed with the bolts, one end of the two general support shafts is respectively rotatably installed with the bearing seat I, and the other end is rotatably installed with the bearing seat II. A bearing seat III is arranged on the top, and a rocker support shaft is rotatably installed between the two bearing seats III. The first motor and the first reducer connected to the first motor are fixed by the first spacer, and the first speed The output shaft of the crankshaft is connected with one end of the crank through an elastic coupling, bearing seats IV are respectively installed on both ends of the lower surface of the support beam, the bearing seat IV at one end of the support beam is connected with the other end of the crank, and the bearing seat IV at the other end of the support beam is set On the rocker support shaft, the middle of the upper surface of the support beam is connected to one end of the support column through a thick corner code, and the other end of the support column is connected to a resin protection board through a thick corner code. Two spacers, bearing seat spacer I and bearing seat spacer II, a second motor and a second reducer connected to the second motor are installed on the second spacer block, and the bearing seat spacer block I is connected by bolts with Bearing seat Ⅴ, bearing seat pad Ⅱ is connected with bearing seat Ⅵ through bolts, the output shaft of the second reducer is connected with one end of optical axis Ⅰ through elastic coupling and bearing seat Ⅴ, and the other end of optical axis Ⅰ is connected with the center of thin-walled flange Ⅰ Hole connection, bearing seat VI is connected to one end of optical axis II, the other end of optical axis II is connected to the center hole of thin-walled flange II, thin-walled flange I and thin-walled flange II are connected by aviation bolts, the thin-walled flange I, thin-walled flange II, optical axis I and the optical axis II constitute a drum-type rotor, an acceleration sensor is installed on the bearing seat V and the bearing seat VI, and the acceleration sensor, the first motor and the second motor are all connected with the vibration testing system.

The resin protection plate is composed of a bottom plate, a long side plate and a short side plate. The two long side plates are respectively inserted into the grooves on the long sides of the bottom plate through the protrusions arranged on the long sides thereof, and the two short side plates pass through The protruding blocks provided on it are respectively inserted into the grooves on the short sides of the bottom plate, and the protruding blocks on the short sides of the long side plates are inserted into the grooves on the short side plates.

The base is formed by five equal-length aluminum profiles connected by bolts and corner codes.

The thin-walled flange I, the thin-walled flange II, the optical axis I and the optical axis II are all made of the same material.

There is at least one disc drum rotor on the resin protection plate.

A method for using an experimental device for simulating a motorized flight aero-engine rotor, comprising the following steps:

Step 1, install the disc drum rotor and tighten the bolts on the bearing seat V and bearing seat Ⅵ, fix the disc drum rotor on the bottom plate of the resin protection plate through the bearing seat V and bearing seat Ⅵ, and then adjust the disc drum rotor The pre-tightening force of the aviation bolt is connected, and the first motor, the second motor and the acceleration sensor are connected to the computer in the vibration test system, and the second motor is started, and the second motor works through the second reducer and the elastic coupling to drive the disk The drum rotor rotates at high speed, and the rotational speed is measured by a hand-held non-contact rotational speed measuring instrument. When the rotational speed reaches the experimental set speed, the internal mechanical characteristics of the disc-drum rotor are consistent with those of the aero-engine disc-drum rotor;

Step 2, start the first motor, the first motor drives the crank to rotate axially through the first reducer and the elastic coupling, pulls the support beam through the circumferential rotation of the crank, and the support beam pulls the rocker support shaft to swing. The rotor begins to swing back and forth periodically. At this time, the internal mechanical characteristics of the disc drum rotor are consistent with the internal mechanical characteristics of the aero-engine when the aircraft is maneuvering. When the computer measures that the experimental device runs to the set time, the set time does not exceed For two flight cycles, first turn off the first motor, and after the support beam and rocker support shaft stop working, turn off the second motor, and the test is over. Data analysis and demonstration.

The technical effect of the present invention is:

1. The experimental device drives the movement of the overall rotor system by adjusting the movements of the two motors in the installation foundation of the disc-drum rotor, simulating the vibration response of the rotor system when the aircraft performs different maneuvering actions.

2. In this experimental device, the middle wheel disc and the drums on both sides are connected by flanges, which can reflect the real connection boundary conditions of the disc-drum rotor, and can measure the vibration of the rotor under different bolt preload conditions, and explore the bolt connection. Influence on the dynamic characteristics of a disc drum rotor.

3. The whole structure of the device has great flexibility. By adjusting the number and position of the rotor system appropriately, it can simulate the stress and vibration characteristics of the internal structure of different engines in single-engine, double-engine or even multi-engine fighter aircraft during maneuvering flight. .

4. There are adjustable and detachable links between any two parts in the device. By adjusting the position of the fixing bolts in the support mechanism, the geometric characteristics of the four-bar mechanism on the test bench can be changed, so that the speed of the motor can be changed. The vibration amplitude and strength of the support.

Description of drawings

1 is a schematic diagram of a first perspective of an aero-engine bolted rotor system experimental device for simulating maneuvering flight according to the present invention;

2 is a schematic diagram of a second perspective of an aero-engine bolted rotor system experimental device for simulating maneuvering flight according to the present invention;

3 is a sectional view of the structure of the aviation bolt part of the aero-engine bolted rotor system experimental device for simulating maneuvering flight of the present invention;

1- base, 2- first motor, 3- first spacer, 4- bearing seat I, 5- total support shaft, 6- bearing seat II, 7- swing arm, 8- bearing seat III, 9- rocker Support shaft, 10- Elastic coupling I, 11- Crank, 12- Support beam, 13- Bearing seat IV, 14- Support column, 15- Thick angle code, 16- Resin protection plate, 17- Second spacer, 18- Bearing block I, 19- Bearing block II, 20- Second motor, 21- Bearing V, 22- Bearing VI, 23- Optical axis I, 24- Optical axis II, 25- Thin-wall flange Ⅰ, 26-thin-wall flange Ⅱ, 27- aviation bolt.

Detailed ways

The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.

As shown in Figures 1 to 3, an experimental device for simulating a motorized flight aero-engine rotor includes a base 1, a swing arm 7, a support beam 12, a total support shaft 5, a resin protection plate 16 and a bearing seat I4; the base The tops of one of the two beams arranged in parallel with each other on 1 are installed with bearing seats I4 through bolts. One end of the two general support shafts 5 is respectively rotatably installed with the bearing seat I4, and the other end is rotatably installed with the bearing seat II6. II6 is installed on the bottom of the side wall of the swing arm 7 through bolts, the top of the side wall of the swing arm 7 is provided with a bearing seat III8, and a rocker support shaft 9 is rotatably installed between the two bearing seats III8. The first reducer connected to the motor 2 is fixed by the first spacer 3, the output shaft of the first reducer is connected to one end of the crank 11 through the elastic coupling I10, and the two ends of the lower surface of the support beam 12 are respectively installed with bearings Seat IV13, the bearing seat IV13 at one end of the support beam 12 is connected with the other end of the crank 11, the bearing seat IV13 at the other end of the support beam 12 is sleeved on the rocker support shaft 9, and the middle of the upper surface of the support beam 12 is connected to the support through a thick angle code 15. One end of the column 14 is connected, and the other end of the support column 14 is connected to the resin protection plate 16 through the thick corner code 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 seat cushion block I18 and a bearing seat cushion Block II19, bearing block I18 and bearing block II19 are matched with the long holes on the bottom plate of the resin protection plate 16 through bolts, and the bearing block I18 and the bearing block II19 are fixed on the bottom plate of the resin protection plate 16 , and because the position of the bearing seat cushion block I18 and the bearing seat cushion block II19 relative to the bottom plate can be adjusted due to the long holes, the second cushion block 17 is installed with the second motor 20 and the second motor 20 connected to the second motor 20. The reducer, the bearing seat spacer I18 is connected with the bearing seat V21 by bolts, the bearing seat spacer II19 is connected with the bearing seat VI22 by bolts, and the output shaft of the second reducer is connected with the optical axis through the elastic coupling II and the bearing seat V21. One end of I23 is connected, the other end of optical axis I23 is welded to the integrally formed circular sleeve at the center of thin-walled flange I25, the bearing seat VI22 is connected to one end of optical axis II24, and the other end of optical axis II24 is welded to the integrally formed circular sleeve at the center of thin-walled flange II26. Connection, thin-walled flange I25 and thin-walled flange II26 are connected by aviation bolts 27. By adjusting the pre-tightening force required by aviation bolts 27, different pre-tightening forces in different states are studied. Aviation bolts 27 can simulate the high-speed rotation of the aircraft when it rolls laterally. The tightening of the connecting parts in the aero-engine, the thin-walled flange I25, the thin-walled flange II26, the optical axis I23 and the optical axis II24 constitute the disc drum rotor. The disc drum rotor is consistent with the actual structure of the aeroengine rotor. An acceleration sensor is installed on the bearing seat VI22, and the acceleration sensor, the first motor 2 and the second motor 20 are all connected to the computer in the vibration test system. The model of the acceleration sensor is 1A102E, and the model of the vibration test system is DH5922D.

The resin protection plate 16 is composed of a bottom plate, a long side plate and a short side plate. The protrusions provided on the board are respectively inserted into the grooves on the short sides of the bottom plate, and the protrusions on the short sides of the long side boards are inserted into the grooves on the short side boards.

The base 1 is formed by five equal-length aluminum profiles connected by bolts and corner codes.

The thin-walled flange I25, thin-walled flange II26, optical axis I23 and optical axis II24 are all made of the same material, and in this way, the mechanical properties of the thin-walled parts of the disc drum rotor in the aero-engine can be simulated to the greatest extent.

There is at least one disc drum rotor on the resin protection plate 16. By adjusting the number and position of the disc drum rotors, the stress and vibration characteristics of different aero-engine internal structures can be simulated during maneuvering of a single-engine or multi-engine aircraft.

All components of the experimental device are standard parts. If the parts are damaged during the simulation of extreme maneuvering of the aircraft, they can be repaired or rebuilt in a very short time, ensuring the stability of the research progress to the maximum extent.

A method for using an experimental device for simulating a motorized flight aero-engine rotor, comprising the following steps:

Step 1, install the disc drum rotor and tighten the bolts on the bearing seat V21 and bearing seat VI22, fix the disc drum rotor on the bottom plate of the resin protection plate 16 through the bearing seat V21 and bearing seat VI22, and then adjust the disc drum The pre-tightening force of the aviation bolts 27 on the rotor, connect the first motor 2, the second motor 20 and the acceleration sensor with the computer in the vibration test system, start the second motor 20, and the second motor 20 works through the second reducer and The elastic coupling drives the disc drum rotor to rotate at a high speed, and the rotational speed is measured by a hand-held non-contact speed measuring instrument. When the speed reaches the experimental set speed, the internal mechanical characteristics of the disc drum rotor and the mechanical properties of the disc drum rotor in the aero-engine consistent;

Step 2, start the first motor 2, the first motor 2 works to drive the crank 11 to rotate axially through the first reducer and the elastic coupling, and the support beam 12 is pulled by the circumferential rotation of the crank 11, and the support beam 12 pulls the rocker support shaft 9. Swing. At this time, the disc drum rotor begins to periodically reciprocate. At this time, the internal mechanical characteristics of the disc drum rotor are consistent with the internal mechanical characteristics of the aero-engine when the aircraft is maneuvering. When the computer measures that the experimental device runs to the set time After the set time does not exceed two flight cycles, first turn off the first motor 2, after the support beam 12 and the rocker support shaft 9 stop working, turn off the second motor 20, the test is over, and the acceleration is sorted by the computer in the vibration test system. The experimental data fed back by the sensor is used to analyze and demonstrate the collected 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.

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