CN208805365U - A kind of dual-rotor structure turboshaft engine unbalance response simulator - Google Patents
A kind of dual-rotor structure turboshaft engine unbalance response simulator Download PDFInfo
- Publication number
- CN208805365U CN208805365U CN201821802578.9U CN201821802578U CN208805365U CN 208805365 U CN208805365 U CN 208805365U CN 201821802578 U CN201821802578 U CN 201821802578U CN 208805365 U CN208805365 U CN 208805365U
- Authority
- CN
- China
- Prior art keywords
- rotor
- turboshaft engine
- disk
- outer rotor
- opposite opened
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Abstract
The utility model discloses a kind of dual-rotor structure turboshaft engine unbalance response simulators, including internal rotor, outer rotor, test macro；Internal rotor is passed through out of outer rotor, and internal rotor and outer rotor installation are on the base；Outer rotor, internal rotor are equipped with disk；Test macro includes the first fluted disc, the second fluted disc, the first key mutually disk, the second key mutually disk, acceleration transducer and control cabinet, and mutually disk is mounted on internal rotor both ends for the first fluted disc and the first key；Mutually disk is mounted on outer rotor both ends for second fluted disc and the second key；Acceleration transducer is mounted on packaged type bearing block；Acceleration transducer acquisition signal is transferred to control cabinet.The different order vibration shape unbalance responses of the compressor of the utility model analog turboshaft engine, gas turbine and free turbine, can study the inner-outer birotor turboshaft engine unbalance vibration characteristic with multiple turntable structure forms.
Description
Technical field
The utility model relates to motor field, in particular to a kind of dual-rotor structure turboshaft engine unbalance response simulation
Device.
Background technique
Birotor turboshaft engine is the primary structure form of current helicopter dynamical system.It is this kind of to improve power to weight ratio
Engine structure design it is often very compact, size is small, connection components it is more, and due to the heterogeneity of each components material,
Mismachining tolerance, assembling deviation and connection status can change with turboshaft engine rotor operation temperature gradient between them
Become this monopolizing characteristic, compressor in turboshaft engine, gas turbine and free turbine is easily caused to generate complicated imbalance
Vibration under state and its multiple combinations form, since turboshaft engine rotor is elongated, work operate in second order critical speed it
On, usually excite uneven (the i.e. power imbalance and couple unbalance) vibration of strong single order, second_mode；On the other hand, by
Contain the non-linear components such as rotor cage type elastic support and squeeze film damper in turboshaft engine bearing, so that complicated
Unbalance response becomes more prominent under the influence of non-linear factor.Turboshaft engine birotor unbalance vibration characteristic master at present
To use simulating analysis, since the Dynamic boundary conditions such as squeeze film damper, resilient support are difficult to determine, emulation point
Analysis result also needs many experiments to be verified, it is therefore necessary to design corresponding simulated experiment platform and carry out turboshaft engine birotor
Imbalance in weight characteristic research.
Currently, usually turboshaft engine rotor testbed is designed for certain a kind of turboshaft engine type, work as needs
When simulating the turboshaft engine of different structure form, if turbine is placed in front of bearing or after bearing, turboshaft engine rotor is real
Testing the corresponding part-structure form of platform also needs to be changed, it will causes critical speed to change, the different order vibration shapes are not
Equilibrium response can also change as turboshaft engine rotor testbed structure type changes.To solve this problem, it mostly uses greatly
Disassembly bearing redesigns new experimental bench.Since turboshaft engine dual-rotor structure rotor testbed uses internal rotor across outer
The form of rotor, when dismantling outer rotor bearing, need first by adjacent internal rotor bearing remove can, lead to operation extremely not
Just；In addition, assembly is re-started after bearing disassembly, because being difficult to ensure rotor cage type elastic support and squeeze film damper this kind of zero
The nonlinear dynamic characteristic of component easily causes the performance of disassembly front and back not identical, or even can introduce biggish assembling deviation
And influence the accuracy of experimental studies results.In practical projects, a new turboshaft engine dual-rotor structure experiment is designed
Platform is often subject to processing the constraint of many unfavorable factors such as long period, manufacturing cost height and experimental site.
Summary of the invention
In order to solve the above-mentioned technical problem, the utility model provides the dual-rotor structure that a kind of structure is simple, reliable and stable
Turboshaft engine unbalance response simulator.
The technical solution that the utility model solves the above problems is:
A kind of dual-rotor structure turboshaft engine unbalance response simulator has dual-rotor structure form for simulating
Turboshaft engine compressor, gas turbine, free turbine rotor difference order vibration shape unbalance response, including it is pedestal, removable
Dynamic formula bearing block, internal rotor, outer rotor, detachable opposite opened disk, test macro, first motor and the second motor；First electricity
Machine is connected by shaft coupling with internal rotor, and internal rotor is passed through out of outer rotor, and internal rotor and outer rotor both ends pass through removable
Formula bearing block is installed on the base；The first belt pulley is arranged on outer rotor, on the simulation compressor area inner and outer Rotator on outer rotor
Simulation gas turbine area in, in the simulation free turbine area on internal rotor be equipped with detachable opposite opened disk；Second motor
It is connected with the second belt pulley, the second belt pulley drives the first belt pulley on outer rotor by belt, to drive outer rotor；It surveys
Test system include for measuring the first fluted disc of internal rotor revolving speed, the second fluted disc for measuring outer rotor revolving speed, for measuring
Mutually mutually disk, acceleration transducer, current vortex sense first key of internal rotor phase for disk, the second key for measuring outer rotor phase
Mutually disk is mounted on internal rotor both ends for device and control cabinet, the first fluted disc and the first key；Mutually disk is mounted on outside for second fluted disc and the second key
Two ends of rotor；Acceleration transducer is mounted on packaged type bearing block, and multiple current vortex sensors are separately mounted to internal rotor
With outer rotor gap；Acceleration transducer, current vortex sensor acquisition signal, to control cabinet, are controlled simultaneously by optical cable transmission
The revolving speed of cabinet control internal rotor and outer rotor.
Above-mentioned dual-rotor structure turboshaft engine unbalance response simulator, the detachable opposite opened disk is along vertical
Direction is splitted, and section bolt, nut are connected and fixed, do not cut open two sides be equipped with and the consistent concave station of section junction size, it is convex
Platform is equipped with and the consistent bolts and nuts of section junction specification.
Above-mentioned dual-rotor structure turboshaft engine unbalance response simulator is provided on the detachable opposite opened disk
Multiple annular grooves, annular groove is interior to be equipped with stop nut, and clump weight is screwed into the stop nut in annular groove by hexagon socket head cap screw,
The axial position being fixed on detachable opposite opened disk using wedge-shaped expansion sleeve on chromium plating straight optical axis；Different annular grooves,
Difference angles install the clump weight of different number and different size, to simulate the detachable opposite opened disk present position
On different amount of unbalance sizes.
Above-mentioned dual-rotor structure turboshaft engine unbalance response simulator, the simulation free turbine area of the internal rotor
Two detachable opposite opened disks are installed to simulate the two-stage free vortex wheel disc of turboshaft engine；The simulation compressor area of outer rotor
Four detachable opposite opened disks of installation are calmed the anger with the three-level axial-flow compressor disk and first-stage centrifugal formula of simulating turboshaft engine
Two detachable opposite opened disks are installed to simulate the two-stage combustion gas of turboshaft engine by machine disk, the simulation gas turbine area of outer rotor
The turbine disk；By the way that different number, different rule are arranged in simulation compressor area, simulation gas turbine area and simulation free turbine area
Compressor disc, gas turbine disk in corresponding region on turboshaft engine of the detachable opposite opened disk of lattice to simulate different type of machines
With the quantity and specification of free vortex wheel disc.
Above-mentioned dual-rotor structure turboshaft engine unbalance response simulator, the packaged type bearing block includes bearing
Seat, countersunk bolt, the pedestal are equipped with several grooves, and the cross section of groove is T shape, are equipped in groove and are used for countersunk bolt,
Countersunk bolt can be slided along groove length direction, and bearing block is slidably arranged in groove by countersunk bolt, by pedestal
Upper mobile packaged type bearing block is to change span；By installing or removing packaged type bearing on the axially different position of pedestal
Seat is to change different supporting forms.
Above-mentioned dual-rotor structure turboshaft engine unbalance response simulator, according to the practical knot of turboshaft engine birotor
Configuration formula is based on the similar design principle of rotor dynamics, adjusts and matches detachable opposite opened disk, packaged type bearing
Seat, the basic size of chromium plating straight optical axis and relative position, make before the imitative experimental appliance of design two rank critical rotor speeds with
The ratio between working speed is equal to the ratio between two rank critical rotor speeds and working speed before the turboshaft engine rotor being modeled, and each turn
Two first order modes are similar before son.
Above-mentioned dual-rotor structure turboshaft engine unbalance response simulator is used to simulate birotor type whirlpool axis hair
Compressor, gas turbine, free turbine unbalance response at the axially different position of motivation pass through the multistage detachable opposite opened of replacement
Disk and the detachable opposite opened disk axial position of adjustment, the birotor whirlpool axis hair in the form of research has multiple turntable structures
Motivation unbalance vibration characteristic, the influence that birotor turboshaft engine is vibrated including single-turn disk amount of unbalance size, double turntables
The upper uneven influence to the vibration of birotor turboshaft engine, the shadow that imbalance vibrates birotor turboshaft engine on three turntables
It rings.
The utility model has the beneficial effects that:
1, the utility model structure is simple, and used disk is opposite opened, without dismantling turboshaft engine rotor mould
It, can be to one of them or several simulation compressor discs, gas turbine disk in the case where draft experiment means bearing seat or shaft coupling
It is dismantled with the disk of free vortex wheel disc, simulates compressor, gas turbine and the free turbine of different turboshaft engine types,
It is conveniently replaceable various sizes of disk, to change the critical speed and the vibration shape of rotor-support-foundation system, simulates different amount of unbalances to whole
Machine vibration influences, and structure is simple, is easily installed and dismantles.
2, the different order vibration shapes of the compressor of the utility model analog turboshaft engine, gas turbine and free turbine
Unbalance response can study the inner-outer birotor turboshaft engine unbalance vibration characteristic with multiple turntable structure forms.
3, design method used in the utility model with the critical speed of practical birotor turboshaft engine prototype and
The vibration shape is referring especially to foundation, and using its structure type and operating parameter as reference conditions, the imitative experimental appliance of design is shown
Rotor dynamics characteristic formp and the actual conditions goodnesses of fit it is high.
Detailed description of the invention
The schematic diagram that Fig. 1 designs for the utility model.
Fig. 2 is the structural schematic diagram of the utility model simulator.
Fig. 3 is the sectional view of detachable opposite opened disk in Fig. 2.
Fig. 4 is the front view of detachable opposite opened disk in Fig. 2.
Fig. 5 is the side view of detachable opposite opened disk in Fig. 2.
Fig. 6 is to simulate certain type turboshaft engine structural schematic diagram.
Fig. 7 is certain preposition bending vibation mode picture of type turboshaft engine free turbine.
Fig. 8 is certain preposition bending vibation mode picture of type turboshaft engine gas turbine.
Fig. 9 is certain type turboshaft engine free turbine postposition bending vibation mode picture.
Figure 10 is certain type turboshaft engine gas turbine postposition bending vibation mode picture.
Figure 11 is the multiple turntable non-equilibrium site schematic diagrames of certain type turboshaft engine.
Specific embodiment
The utility model is further described with reference to the accompanying drawings and examples.
As shown in Figure 1, a kind of dual-rotor structure turboshaft engine unbalance response analogy method, comprising the following steps:
(1) according to turboshaft engine birotor practical structures form, it is based on the similar design principle of rotor dynamics, will be turned
Son is reduced to simply supported beam, then the critical speed ω of rotornFormula are as follows:
Wherein k is rigidity, and m is quality, and g is acceleration of gravity, σsCause natural bow for disk weight,
Wherein F is load, and l is span, and EI is bending stiffness；
It follows that critical turn of rotor-support-foundation system can be adjusted by changing quality, rigidity, span and load distribution
Speed；
(2) based on two rank critical speeds before dual-rotor structure turboshaft engine prototype and its vibration shape, consider prototype
The practical structures and actual operation parameters of machine, such as: temperature field, lubricating oil viscosity are based on kinetic characteristics principle of similarity, lead to
The position for moving detachable opposite opened disk 20 on axis is crossed, and changes the distance between packaged type bearing block 1 to change
The rigidity k of rotor-support-foundation system；Change the quality m of rotor-support-foundation system by changing the size of detachable opposite opened disk 20.By rigidity k
With the variation of quality m, make before the simulated experiment platform of design the ratio between two rank critical rotor speeds and working speed equal to being modeled
The ratio between two rank critical rotor speeds and working speed before turboshaft engine rotor.
(3) each rotor is similar with corresponding prototype rotor vibration model, i.e., one first order mode of outer rotor be tubular rigid mode vibration, two
First order mode is biconial rigid mode vibration；One first order mode of internal rotor is the bending vibration shape of not node, and second_mode is a node
The bending vibration shape；According to the prototype vibration shape, keep two first order modes before imitative experimental appliance rotor rotor corresponding with prototype similar；
Close to vibration shape off-axis center maximum to uneven susceptibility highest, the uneven effect of addition is most obvious, obtains imbalance
Characteristic is best.
As shown in Fig. 2, a kind of dual-rotor structure turboshaft engine unbalance response designed based on above-mentioned design method
Simulator, for simulating the turboshaft engine compressor with dual-rotor structure form, gas turbine, free turbine rotor not
With order vibration shape unbalance response, including more turntable imbalance sizes in different rotor, axial position, phase difference and between each other
Combining form.
Dual-rotor structure turboshaft engine unbalance response simulator includes pedestal 21, packaged type bearing block 1, interior turn
Son 13, outer rotor 14, detachable opposite opened disk 20, test macro, first motor 12 and the second motor 18；First motor 12 is logical
It crosses the first flat key 11 to be connected with shaft coupling 10, shaft coupling 10 is connected with internal rotor 13, and internal rotor 13 is passed through out of outer rotor 14, interior
Rotor 13 and 14 both ends of outer rotor pass through packaged type bearing block 1 and are mounted on pedestal 21；The first skin is arranged on outer rotor 14
Belt wheel 4, the simulation gas turbine area 6 on simulation 5 inner and outer Rotator 14 of compressor area on outer rotor 14 is interior, on internal rotor 13
Simulation is equipped with detachable opposite opened disk 20 in free turbine area 8；Second motor 18 passes through the second flat key 17 and the second belt
Wheel 16 is connected, and the second belt pulley 16 drives the first belt pulley 4 on outer rotor 14 by belt 15, to drive outer rotor 14；
Test macro include for measuring the first fluted disc 2 of 13 revolving speed of internal rotor, the second fluted disc 3 for measuring 14 revolving speed of outer rotor,
Mutually mutually disk 7, acceleration pass the first key for measuring 13 phase of internal rotor for disk 9, the second key for measuring 14 phase of outer rotor
Mutually disk 9 is mounted on 13 both ends of internal rotor for sensor, current vortex sensor and control cabinet 19, the first fluted disc 2 and the first key；Second fluted disc
3 and second key mutually disk 7 be mounted on 14 both ends of outer rotor；Acceleration transducer is mounted on packaged type bearing block 1, multiple electricity whirlpools
Flow sensor is separately mounted to 14 gap of internal rotor 13 and outer rotor；Acceleration transducer, current vortex sensor acquire signal
By optical cable transmission to control cabinet 19, while control cabinet 19 controls the revolving speed of internal rotor 13 and outer rotor 14.
As shown in figure 3, figure 4 and figure 5, the detachable opposite opened disk 20 is splitted along the vertical direction, section bolt 22,
Nut 23 is connected and fixed, while in order to reduce because of amount of unbalance brought by connector at subdivision, being ensured from structure detachable
Opposite opened disk quality, in being uniformly and symmetrically distributed, is not cuing open two sides equipped with consistent recessed with section junction size along the centre of gyration
Platform, boss is equipped with and the consistent bolt of section junction specification 22 and nut 23.
It is provided with multiple annular grooves on the detachable opposite opened disk 20, is equipped with stop nut 26, clump weight in annular groove
24 are screwed into the stop nut 26 in annular groove by hexagon socket head cap screw 25, using wedge-shaped expansion sleeve by detachable opposite opened disk
20 are fixed on the axial position on straight optical axis；Uneven cooperation can be carried out in annular groove any position, it can be in different annulars
The clump weight 24 of slot, Difference angles installation different number and different size, to simulate the detachable opposite opened disk 20
Different amount of unbalance sizes on present position.
As shown in fig. 6, the internal rotor 13 simulation free turbine area 8 install two detachable opposite opened disks 20 with
Simulate the two-stage free vortex wheel disc of turboshaft engine；Four detachable opposite openeds are installed in the simulation compressor area 5 of outer rotor 14
Disk 20 is to simulate the three-level axial-flow compressor disk and first-stage centrifugal formula compressor disc of turboshaft engine, in the mould of outer rotor 14
Two detachable opposite opened disks 20 are installed to simulate the two-stage gas turbine disk of turboshaft engine in quasi- gas turbine area 6；Pass through
Simulation compressor area 5, simulation gas turbine area 6 and simulate free turbine area 8 in be arranged different number, different size it is removable
Unload on turboshaft engine of the opposite opened disk 20 to simulate different type of machines compressor disc, gas turbine disk and freedom in corresponding region
The quantity and specification of the turbine disk.
The packaged type bearing block 1 includes bearing block, countersunk bolt, and the pedestal 21 is equipped with several grooves, groove
Cross section be T shape, be equipped in groove and be used for countersunk bolt, countersunk bolt can be slided along groove length direction, and bearing block passes through
Countersunk bolt is slidably arranged in groove, by packaged type bearing block 1 mobile on pedestal 21 to change span；By
Packaged type bearing block 1 is installed or removed on the axially different position of pedestal 21 to change different supporting forms.
The utility model is former based on the similar design of rotor dynamics according to turboshaft engine birotor practical structures form
Then, adjust with match detachable opposite opened disk 20, packaged type bearing block 1, chromium plating straight optical axis basic size with relatively
Position starts the ratio between two rank critical rotor speeds and working speed before the imitative experimental appliance of design equal to the whirlpool axis being modeled
The ratio between two rank critical rotor speeds and working speed before machine rotor, and two first order modes are similar before each rotor.
The utility model for simulate compressor at the axially different position of birotor type turboshaft engine, gas turbine,
Free turbine unbalance response, without on the basis of dismantling bearing block, the multistage detachable opposite opened disk 20 of quick-replaceable with
And detachable 20 axial position of opposite opened disk of adjustment, the birotor turboshaft engine in the form of research has multiple turntable structures
Unbalance vibration characteristic, in the influence vibrated including single-turn disk amount of unbalance size to birotor turboshaft engine, double turntables not
Balance (including a first order mode is uneven, second_mode imbalance, i.e. amount of unbalance size and phase subtractive combination) is to birotor whirlpool
The influence of shaft generator vibration, uneven on three turntables (including a first order mode is uneven, second_mode is uneven, i.e., uneven
Measure size and phase subtractive combination) influence to the vibration of birotor turboshaft engine.
As shown in Figure 7, Figure 8, certain type birotor turboshaft engine of experimental bench simulation, before free turbine and gas turbine
It sets, that is, is placed in the resulting vibration shape before bearing, wherein preceding two first order mode of internal rotor 13 shows as flexible mode, and a first order mode does not have
There is node, second_mode has a node；Preceding two first order mode of outer rotor 14 shows as rigid body mode, and a first order mode does not save
Point, second_mode have a node.
As shown in Figure 9, Figure 10, certain type birotor turboshaft engine of the experimental bench simulation, by free turbine and combustion gas
Turbine postposition is placed in the resulting vibration shape after bearing.Compared with free turbine and gas turbine are preposition, internal rotor 13 turns with outer
The vibration shape of son 14 is changed, and corresponding variation also has occurred in unbalance response.According to different vibration shape forms, rotor is real
It is different to test platform addition non-equilibrium site, has directive significance to the uneven additive amount of rotor testbed.
As shown in figure 11, the experimental bench simulates certain type inner-outer birotor turboshaft engine, simulates compressor area 5, mould
Different zones, the imbalance of different number and different directions in quasi- gas turbine area 6 and simulation free turbine area 8.It can be single
Solely simulation compressor area 5, simulation gas turbine area 6 and simulation free turbine area 8 in the multiple and different quantity of a regional simulation,
The imbalance of different size and different directions；It can be in simulation compressor area 5, simulation gas turbine area 6 and simulation free turbine
The multiple and different quantity of two regional simulations, the imbalance of different size and different directions in area 8；Can simulation compressor area 5,
Simulate the multiple and different quantity of three regional simulations, different size and different directions in gas turbine area 6 and simulation free turbine area 8
Imbalance.Such as: adding an imbalance on level-one axial-flow compressor in simulation compressor area 5 and calm the anger centrifugal
The imbalance with level-one axial-flow compressor opposite direction is added on machine；The level-one combustion gas whirlpool in simulation gas turbine area 6 simultaneously
Wheel addition imbalance identical with simulation 8 second level free turbine of free turbine area.And so on, can to simulation compressor area 5,
Simulate gas turbine area 6 and simulate in free turbine area 8 it is uneven carry out different location, size and phase combination form into
Row research.
Based on the design method design dual-rotor structure turboshaft engine unbalance response simulator, containing optical axis,
Detachable opposite opened disk 20 and packaged type bearing block 1.Optical axis may make detachable opposite opened disk 20 and packaged type axis
Holding seat 1 can be moved in the axial direction in the case where no replacement is required axis, and the detachable opposite opened disk 20 of adjustment is facilitated to exist
Axis improve quality distribution and packaged type bearing block 1 span adjustment；Detachable opposite opened disk 20 can not dismantle bearing
In the case where seat, the replacement of disk quality size is carried out.Pass through optical axis, detachable opposite opened disk 20 and packaged type bearing block
1, it can quick and convenient variation, the change of bearing block span and the replacement of disk quality size for carrying out disk Mass Distribution.
Based on the dual-rotor structure turboshaft engine unbalance response simulator of design method design, by detachable
The imbalance of arbitrary phase can be set in the annular groove being arranged on opposite opened disk 20, to simulate unbalanced phase；It is simulating
It is added on the Bu Tong detachable opposite opened disk 20 that compressor area 5, simulation gas turbine area 6 and simulation free turbine area 8 are arranged
Different imbalance, to simulate non-equilibrium site；In conjunction with above two, the uneven size of change, to simulate unbalanced size.
Claims (7)
1. a kind of dual-rotor structure turboshaft engine unbalance response simulator, for simulating with dual-rotor structure form
Turboshaft engine compressor, gas turbine, free turbine rotor difference order vibration shape unbalance response, it is characterised in that: including
Pedestal, packaged type bearing block, internal rotor, outer rotor, detachable opposite opened disk, test macro, first motor and the second electricity
Machine；First motor is connected by shaft coupling with internal rotor, and internal rotor is passed through out of outer rotor, and internal rotor and outer rotor both ends are logical
Cross the installation of packaged type bearing block on the base；The first belt pulley is arranged on outer rotor, in the simulation compressor area on outer rotor,
Detachable opposite opened disk is equipped in simulation gas turbine area on outer rotor, in the simulation free turbine area on internal rotor；
Second motor and the second belt pulley are connected, and the second belt pulley drives the first belt pulley on outer rotor by belt, to drive
Outer rotor；Test macro include for measuring the first fluted disc of internal rotor revolving speed, the second fluted disc for measuring outer rotor revolving speed,
For measuring the first key of internal rotor phase mutually disk, the second key for measuring outer rotor phase mutually disk, acceleration transducer, electricity
Mutually disk is mounted on internal rotor both ends for eddy current sensor and control cabinet, the first fluted disc and the first key；Second fluted disc and the second key mutually disk
It is mounted on outer rotor both ends；Acceleration transducer is mounted on packaged type bearing block, and multiple current vortex sensors are installed respectively
In internal rotor and outer rotor gap；Acceleration transducer, current vortex sensor acquisition signal by optical cable transmission to control cabinet,
The revolving speed of control cabinet control simultaneously internal rotor and outer rotor.
2. dual-rotor structure turboshaft engine unbalance response simulator according to claim 1, it is characterised in that: institute
It states detachable opposite opened disk to split along the vertical direction, section bolt, nut are connected and fixed, and are equipped with and section not cuing open two sides
The consistent concave station of junction size, boss is equipped with and the consistent bolts and nuts of section junction specification.
3. dual-rotor structure turboshaft engine unbalance response simulator according to claim 2, it is characterised in that: institute
It states and is provided with multiple annular grooves on detachable opposite opened disk, stop nut is equipped in annular groove, clump weight passes through hexagon socket head cap screw
It is screwed into the stop nut in annular groove, detachable opposite opened disk is fixed on chromium plating straight optical axis using wedge-shaped expansion sleeve
Axial position；It, should with simulation in the clump weight of different annular grooves, Difference angles installation different number and different size
Different amount of unbalance sizes on detachable opposite opened disk present position.
4. dual-rotor structure turboshaft engine unbalance response simulator according to claim 3, it is characterised in that: institute
Two detachable opposite opened disks are installed to simulate the two-stage free vortex of turboshaft engine in the simulation free turbine area for stating internal rotor
Wheel disc；Four detachable opposite opened disks are installed to simulate the three-level axial-flow type of turboshaft engine in the simulation compressor area of outer rotor
Compressor disc and first-stage centrifugal formula compressor disc, the simulation gas turbine area of outer rotor install two detachable opposite opened disks with
Simulate the two-stage gas turbine disk of turboshaft engine；By in simulation compressor area, simulation gas turbine area and simulation free vortex
It takes turns and is arranged on turboshaft engine of the detachable opposite opened disk of different number, different size to simulate different type of machines in area accordingly
The quantity and specification of compressor disc in region, gas turbine disk and free vortex wheel disc.
5. dual-rotor structure turboshaft engine unbalance response simulator according to claim 3, it is characterised in that: institute
Stating packaged type bearing block includes bearing block, countersunk bolt, and the pedestal is equipped with several grooves, and the cross section of groove is T shape,
It is equipped in groove and is used for countersunk bolt, countersunk bolt can be slided along groove length direction, and bearing block passes through countersunk bolt slidably
It is arranged in groove, by moving packaged type bearing block on the base to change span；By in the axially different position of pedestal
Upper installation or removal packaged type bearing block is to change different supporting forms.
6. dual-rotor structure turboshaft engine unbalance response simulator according to claim 3, it is characterised in that: root
According to turboshaft engine birotor practical structures form, it is based on the similar design principle of rotor dynamics, adjust and is matched detachably
Opposite opened disk, packaged type bearing block, the basic size of chromium plating straight optical axis and relative position make the simulated experiment dress of design
Two rank critical rotors before the ratio between preceding two ranks critical rotor speed and working speed are equal to the turboshaft engine rotor being modeled are set to turn
The ratio between speed and working speed, and two first order modes are similar before each rotor.
7. dual-rotor structure turboshaft engine unbalance response simulator according to claim 3, it is characterised in that: its
For simulating compressor, gas turbine, free turbine unbalance response at the axially different position of birotor type turboshaft engine,
By the multistage detachable opposite opened disk of replacement and the detachable opposite opened disk axial position of adjustment, there are multiple turns with research
The birotor turboshaft engine unbalance vibration characteristic of dish structure form, including single-turn disk amount of unbalance size is to birotor whirlpool axis
It is uneven right in imbalance vibrates birotor turboshaft engine in the influence of engine luggine, double turntables influence, three turntables
The influence of birotor turboshaft engine vibration.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821802578.9U CN208805365U (en) | 2018-11-02 | 2018-11-02 | A kind of dual-rotor structure turboshaft engine unbalance response simulator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821802578.9U CN208805365U (en) | 2018-11-02 | 2018-11-02 | A kind of dual-rotor structure turboshaft engine unbalance response simulator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208805365U true CN208805365U (en) | 2019-04-30 |
Family
ID=66239507
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821802578.9U Expired - Fee Related CN208805365U (en) | 2018-11-02 | 2018-11-02 | A kind of dual-rotor structure turboshaft engine unbalance response simulator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208805365U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110320044A (en) * | 2019-05-27 | 2019-10-11 | 西北工业大学 | Active load shedding device after aero-engine tester sudden applied load |
-
2018
- 2018-11-02 CN CN201821802578.9U patent/CN208805365U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110320044A (en) * | 2019-05-27 | 2019-10-11 | 西北工业大学 | Active load shedding device after aero-engine tester sudden applied load |
| CN110320044B (en) * | 2019-05-27 | 2020-12-08 | 西北工业大学 | Active load reduction device after sudden loading of aircraft engine tester |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101246071B (en) | Shafting dynamic balance experimental bench | |
| Guo et al. | Nonlinear dynamic analysis of rigid rotor supported by gas foil bearings: Effects of gas film and foil structure on subsynchronous vibrations | |
| Chen et al. | Modeling and analysis of fit clearance between rolling bearing outer ring and housing | |
| Chiang et al. | Rotor-bearing analysis for turbomachinery single-and dual-rotor systems | |
| CN104568351B (en) | Damping-structure-optimized blade testing experiment table and experimental method thereof | |
| CN108519235A (en) | Air impeller drive-type birotor testing stand | |
| Piekos | Numerical simulation of gas-lubricated journal bearings for microfabricated machines | |
| CN109253885A (en) | Dual-rotor structure turboshaft engine unbalance response simulator and its design method | |
| CN105928676A (en) | Vibration testing device of damping mistuning blade-turbine disk with damping block structure | |
| CN106226015A (en) | A kind of assay device of turbine disk coupled vibrations | |
| Hilditch et al. | Installation of a turbine stage in the Pyestock Isentropic Light Piston Facility | |
| CN111780940A (en) | Adjustable stator blade motion control experimental device of aeroengine | |
| CN208805365U (en) | A kind of dual-rotor structure turboshaft engine unbalance response simulator | |
| CN110672292B (en) | Rotary damping blade vibration magnetic excitation vibration modeling test device | |
| CN201166597Y (en) | Shafting dynamic balance experimental bench | |
| von Osmanski et al. | Gas foil bearings with radial injection: Multi-domain stability analysis and unbalance response | |
| CN109684711A (en) | A kind of turboshaft engine is pneumatically connected more rotor coupled vibration analysis methods | |
| CN112903228A (en) | Magnetic force excitation bolt joint vibration failure experimental device and test method | |
| Han et al. | Nonlinear dynamic behavior research on high-speed turbo-expander refrigerator rotor | |
| Ma et al. | Multi-body dynamic simulation and vibration transmission characteristics of dual-rotor system for aeroengine with rubbing coupling faults | |
| CN115876451A (en) | Simulation design method, experiment table and simulation method for rotor system with elastic ring type squeeze film damper | |
| Han et al. | Experimental research on the dynamic characteristics of gas-hybrid bearing-flexible rotor system | |
| Miranda et al. | Lateral vibration analysis of flexible shafts supported on elliptical journal bearings | |
| CN203894018U (en) | Three-span rotor vibration test platform | |
| KR101642274B1 (en) | Vibration exciter in the horizontal and vertical and rotational direction |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190430 Termination date: 20211102 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |