CN106092558A - Integrated liquid rocket engine high-speed turbine pump rotor test installation for dynamic characteristics - Google Patents
Integrated liquid rocket engine high-speed turbine pump rotor test installation for dynamic characteristics Download PDFInfo
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- CN106092558A CN106092558A CN201610709907.4A CN201610709907A CN106092558A CN 106092558 A CN106092558 A CN 106092558A CN 201610709907 A CN201610709907 A CN 201610709907A CN 106092558 A CN106092558 A CN 106092558A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
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Abstract
Integrated liquid rocket engine high-speed turbine pump rotor test installation for dynamic characteristics, including tile fragment on device (1), tile fragment (2) under device, lubricating oil return chamber (3), bearing central oiling oil circuit (4), lubricating oil fuel feed hole (5), the outside axial locating surface (6) of device, device outer radial locating surface (7), lubricating oil return hole (8), lubrication spray bar (9) surveyed by bearing two, rotor supports axial locating surface (10), rotor supports radially locating surface (11), Sensor (12), dowel hole (13), spray bar (14) in the middle of bearing；The two ends fulcrum of testpieces is attached supporting by an integrated tooling, it is primarily adapted for use in the turbo pump rotor system that span is less, rotating speed is higher, it is provided simultaneously with bearing lubrication, gathers the several functions such as point layout, it is ensured that the accuracy of the dynamic response test of high-speed turbine pump rotor system and stability.
Description
Technical field
Integrated liquid rocket engine high-speed turbine pump rotor test installation for dynamic characteristics of the present invention, relates to liquid rocket and sends out
Motivation high-speed turbine pump rotor dynamic analysis field, is a kind of for liquid-propellant rocket engine high-speed turbine pump rotor dynamic characteristic
The integrated device of test, mainly to postcritical flexible turbo pump rotor.
Background technology
Turbo pump rotor system is the main member of liquid-propellant rocket engine turbine pump, along with aerospace industry develops rapidly,
The performance of electromotor improves constantly, and the working speed of turbo pump rotor improves constantly, and usually exceedes single order, even second order critical
The flex rotor of rotating speed.Flex rotor dynamics under the state of running up is obvious, causes the factors such as amount of unbalance
Vibration very sensitive, the vibration effect factor under its fast state and the research of fault characteristic, always liquid rocket are sent out
In place of the key of motivation rotor dynamics design, and rotor vibration level at high speeds can be suppressed, be to ensure that liquid
The important step of rocket engine stable operation.
Existing turbo pump rotor assay device is split type assay device, each at two fulcrums of rotor the most respectively
Designing a support means, this design cannot ensure that rotor has higher concentricity and the alignment degree with driving motor, no
But disturb the acquisition precision of test data, even cause motor driving shaft to rupture.Simultaneously because split-type structural, assay device
Rigidity more weak, it is difficult to stably rise to higher rotation speed, and easily with test rotor and resonate, there is considerable risk.
Summary of the invention
Present invention solves the technical problem that for: overcome prior art not enough, it is provided that integrated liquid rocket engine is at a high speed
Turbo pump rotor test installation for dynamic characteristics is in order to carry out the dynamic response test of liquid-propellant rocket engine high-speed turbine pump rotor, full
Test rotor and testing stand are carried out the requirement of high accuracy Butt Assembling by foot, devise the assay device of a kind of integral structure,
Will the two ends fulcrum of rotor be attached supporting by an integrated tooling, assay device structural rigidity is strong, and accuracy of alignment is high,
It is primarily adapted for use in the turbo pump rotor system that span is less, rotating speed is higher, is provided simultaneously with bearing lubrication, collection point layout etc. many
Plant function, it is ensured that the accuracy of the dynamic response test of high-speed turbine pump rotor system and stability.
The technical scheme that the present invention solves is: integrated liquid rocket engine high-speed turbine pump rotor dynamic response test fills
Put, including: tile fragment (2) under tile fragment (1), device, lubricating oil return chamber (3), bearing central oiling oil circuit (4), lubrication on device
The outside axial locating surface (6) of oil fuel feed hole (5), device, device outer radial locating surface (7), lubricating oil return hole (8), bearing
Two survey lubrication spray bar (9), rotor supports axial locating surface (10), rotor supports radially locating surface (11), Sensor
(12), spray bar (14) in the middle of dowel hole (13), bearing；
On device, under tile fragment (1) and device, tile fragment (2) is the half of hollow semi-cylinders body, tile fragment (1) and dress on device
Put lower tile fragment (2) and can make up a hollow semi-cylinders body, the sky that on device, under tile fragment (1) and device, tile fragment (2) forms
Two faces of cylinder of heart semicylinder are near hollow position as rotor supports axial locating surface (10), and hollow semi-cylinders body is close
The inner surface on two faces of cylinder is as rotor supports radially locating surface (11), rotor supports axial locating surface (10) and rotor supports
Radially locating surface (11) is ring surface, provides for rotor and supports；The outer arcuate table of tile fragment (2) under tile fragment (1), device on device
It is respectively arranged with a protruding annulus near two faces of cylinder on face, and two protruding annulus are coaxial with hollow semi-cylinders body；Two
Protruding device outer radial locating surface (7) on annulus arranges dowel hole (13), it is possible to inserts alignment pin and makes assay device
Fixing；
The front of protruding annulus is device outer radial locating surface (7), and side is the outside axial locating surface (6) of device；
On two faces of cylinder of hollow semi-cylinders body, two or more Sensor (12) is respectively set, and at hollow semi-cylinders
Between two protruding annulus in the outer arcuate face of body, two or more Sensor (12) is set,
Device outer radial locating surface (7) on two protruding annulus respectively arranges one group of lubricating oil fuel feed hole (5), often group
It is 2 lubricating oil fuel feed holes (5), near protruding circle between two protruding annulus in the outer arcuate face of hollow semi-cylinders body
Lubricating oil return hole (8) is set at ring, the radially locating surface of the rotor supports on a face of cylinder near hollow semi-cylinders body
(11) bearing two is set on and surveys lubrication spray bar (9), another face of cylinder of hollow semi-cylinders body arranges spray in the middle of bearing
Oil pipe (14), it is interior that lubricating oil return chamber (3) are arranged on tile fragment (2) under tile fragment on device (1) and device；And lubricating oil return chamber
(3) on device, tile fragment (1) connects in tile fragment under device (2)；
Device is provided with in tile fragment (1) bearing central oiling oil circuit (4), one end of bearing central oiling oil circuit (4)
Connecting one group of lubricating oil fuel feed hole (5), the other end of bearing central oiling oil circuit (4) connects the one of the middle spray bar (14) of bearing
End, in the middle of bearing, the other end of spray bar (14) connects lubricating oil return chamber (3)；
One end that another group lubricating oil fuel feed hole (5) surveys lubrication spray bar (9) with bearing two connects, and lubrication spray surveyed by bearing two
The other end of oil pipe (9) connects with lubricating oil return chamber (3), and lubricating oil return chamber (3) are provided with lubricating oil return hole (8)；
The two or more sensor arranged between two protruding annulus in the outer arcuate face of described hollow semi-cylinders body
In measuring point (12), at least Sensor (12) is vertical with the line in the axle center of hollow semi-cylinders body.
Described device outer radial locating surface (7) place plane is orthogonal with device outside axial locating surface (6) place plane,
And the outside axial locating surface (6) of device is parallel with two faces of cylinder；
Another proper bearing to testpieces of lubrication spray bar (9) surveyed by described bearing two.
The oilhole of another proper elastic supporting member for supporting optical member to testpieces of spray bar (14) in the middle of bearing；
Present invention advantage compared with prior art is:
(1) assay device of the present invention many successes are applied in the dynamic response test of high-speed turbine pump rotor, examination
Testing result good, assembly reliability is high.
(2) the two ends fulcrum of rotor is attached supporting by the present invention by an integrated tooling, the assembling structure of device
Simply, support stiffness and self structure rigidity are higher, it is possible to the true actual support operating mode simulating turbo pump rotor, it is achieved that
Body formula designs.
(3) integral structure of the present invention is able to ensure that the endoporus of device and exit orifice locating surface benchmark are consistent, improves rotor
The concentricity docked with testing stand.Integral structure farthest simplifies the adaptor quantity of rotor and testing stand simultaneously,
Avoid multilamellar and coordinate the assembly precision error caused, it is achieved that positioning precision is high.
(4) set lubricant passage way in the present invention, it is to avoid external bearing feed pipe, simplify assemble flow, solve axle
Hold a difficult problem for lubrication.Internal oil passages makes bearing lubrication effect more preferable simultaneously.
(5) present invention precisely arranges multiple measuring point, device at most can be arranged 6 displacement measuring points simultaneously, it is to avoid use
Magnetic force suction base fixes the problems such as the support that sensor causes is unstable, test position is inaccurate, improves safety and the essence of test
Really property.
(6) present configuration avoids interference frequency, owing to this assay device is for high-speed working condition (n > 60000r/min), if
Timing makes the natural frequency of apparatus structure avoid power frequency and the natural frequency of rotor so that it is have enough rigidity and stability,
Avoid, owing to rotor oscillation causes resonance, producing interfering frequency.
(7) the integral structure rigidity of the test installation for dynamic characteristics of the high-speed turbine pump rotor of present invention design is strong, location
Respond well, data point layout is accurate, and device stability is strong at high speeds, has been put at present using and completing many
The high-speed balancing of secondary turbo pump rotor and dynamic response test.
Accompanying drawing explanation
Fig. 1 is the integrated liquid rocket engine turbopump rotor high speed test installation for dynamic characteristics three dimensional structure of invention
Figure；
Fig. 2 is that the integrated liquid rocket engine turbopump rotor high speed test installation for dynamic characteristics structure master of invention regards
Figure；
Fig. 3 is the integrated liquid rocket engine turbopump rotor high speed test installation for dynamic characteristics structure left view of invention
Figure；
Fig. 4 is that the integrated liquid rocket engine turbopump rotor high speed test installation for dynamic characteristics structure of invention is overlooked
Figure；
Fig. 5 is that the integrated liquid rocket engine turbopump rotor high speed test installation for dynamic characteristics test data of invention is bent
Line chart.
Detailed description of the invention
The basic ideas of the present invention are: integrated liquid rocket engine high-speed turbine pump rotor test installation for dynamic characteristics,
Being made up of upper and lower tile fragment two parts, tile fragment two ends are rotor supports locating surface, provide 2 supports for rotor, and pass through tile fragment certainly
Body integral structure, by two support level consolidation one, improves positioning precision and the rigidity of support.Both sides are passed through outside tile fragment
Locating surface docks with experiment supporting device, and is positioned by upper tile fragment top dowel pin, it is possible to effective guarantee test rotor with
The alignment degree of assay device.Lower tile fragment side has 4 fuel feed holes, and bearing is moistened by the oil circuit that lubricating oil can set in passing through
Sliding, the design of oil circuit ensure that the efficiently and accurately of bearing lubrication.Tile fragment inside is the oil back chamber of hollow, has 2 bottom lower tile fragment
Individual spill port, it is ensured that the recycling of lubricating oil.6 displacement transducer measuring points are set altogether at the middle part of upper tile fragment and both sides, with
Bearing temperature can be set up time inside and support the Sensors such as mouse cage strain, it is ensured that the most effectively prison to test data
Survey.
With specific embodiment, the present invention is described in further detail below in conjunction with the accompanying drawings.
As shown in Figure 1, Figure 2, Figure 3, Figure 4, integrated liquid rocket engine high-speed turbine pump rotor dynamic response test dress
Put, it is characterised in that: include tile fragment (2) under tile fragment on device (1), device, lubricating oil return chamber (3), bearing central oiling oil
Road (4), lubricating oil fuel feed hole (5), the outside axial locating surface (6) of device, device outer radial locating surface (7), lubricating oil return
Hole (8), bearing two are surveyed lubrication spray bar (9), rotor supports axial locating surface (10), rotor supports radially locating surface (11), are passed
Spray bar (14) in the middle of sensor measuring point (12), dowel hole (13), bearing；
On device, under tile fragment (1) and device, tile fragment (2) is the half of hollow semi-cylinders body, tile fragment (1) and dress on device
Put lower tile fragment (2) and can make up a hollow semi-cylinders body, the sky that on device, under tile fragment (1) and device, tile fragment (2) forms
Two faces of cylinder of heart semicylinder are near hollow position as rotor supports axial locating surface (10), and hollow semi-cylinders body is close
The inner surface on two faces of cylinder is as rotor supports radially locating surface (11), rotor supports axial locating surface (10) and rotor supports
Radially locating surface (11) is ring surface, provides for rotor and supports, and the two ends fulcrum of rotor is passed through an overall work by the present invention
Dress is attached supporting, the assembling simple in construction of device, and structure uses hardness to process at the rustless steel of more than 30HRC, supports just
Degree and self structure rigidity are higher, it is possible to the true actual support operating mode simulating turbo pump rotor, it is achieved that unitary design.；
It is respectively arranged with a protruding annulus near two faces of cylinder on the outer arcuate surface of tile fragment (2) under tile fragment (1), device on device, and
Two protruding annulus are coaxial with hollow semi-cylinders body；Device outer radial locating surface (7) on two protruding annulus is arranged
Dowel hole (13), it is possible to insert alignment pin and make assay device fix；
The front of protruding annulus is device outer radial locating surface (7), and side is the outside axial locating surface (6) of device；
Assembly of the invention is that integral type structure is able to ensure that the endoporus of device and exit orifice locating surface benchmark are consistent, and preferably that each is fixed
Within plane concentricity is limited to 0.05mm, improve the concentricity that rotor docks with testing stand.Integral structure maximum journey simultaneously
The adaptor quantity that simplifies rotor and testing stand of degree, it is to avoid multilamellar coordinates the assembly precision error caused, it is achieved that height
Precision positions.
On two faces of cylinder of hollow semi-cylinders body, two or more Sensor (12) is respectively set, and at hollow semi-cylinders
Arranging two or more Sensor (12) between two protruding annulus in the outer arcuate face of body, point position is arranged precisely,
Avoid the problems such as support that sensor causes is unstable, test position is inaccurate that use magnetic force suction base to fix, improve test
Safety and accuracy.Two preferably arranged between two protruding annulus in the outer arcuate face of described hollow semi-cylinders body
In above Sensor (12), at least two Sensors (12) are vertical with the line in the axle center of hollow semi-cylinders body, this
Sample can accurately test out the orbit of shaft center of test rotor.
Device outer radial locating surface (7) on two protruding annulus respectively arranges one group of lubricating oil fuel feed hole (5), often group
It is 2 lubricating oil fuel feed holes (5), near protruding circle between two protruding annulus in the outer arcuate face of hollow semi-cylinders body
Lubricating oil return hole (8) is set at ring, the radially locating surface of the rotor supports on a face of cylinder near hollow semi-cylinders body
(11) bearing two is set on and surveys lubrication spray bar (9), another face of cylinder of hollow semi-cylinders body arranges spray in the middle of bearing
Oil pipe (14), it is interior that lubricating oil return chamber (3) are arranged on tile fragment (2) under tile fragment on device (1) and device；And lubricating oil return chamber
(3) on device, tile fragment (1) connects in tile fragment under device (2)；Preferably lubricating oil return chamber (3) wall thickness is 15mm, is ensureing
While structural strength, having again sufficiently large lubricating oil return chamber (3) internal diameter, internal diameter is 190mm, it is ensured that lubricating oil
Reclaim circulation unimpeded.
Device is provided with in tile fragment (1) bearing central oiling oil circuit (4), one end of bearing central oiling oil circuit (4)
Connecting one group of lubricating oil fuel feed hole (5), the other end of bearing central oiling oil circuit (4) connects the one of the middle spray bar (14) of bearing
End, in the middle of bearing, the other end of spray bar (14) connects lubricating oil return chamber (3)；The present invention sets lubricant passage way in passing through, it is to avoid
External bearing feed pipe, simplifies assemble flow, solves a difficult problem for bearing lubrication.Internal oil passages makes bearing lubrication simultaneously
Effect is more preferable.
One end that another group lubricating oil fuel feed hole (5) surveys lubrication spray bar (9) with bearing two connects, and lubrication spray surveyed by bearing two
The other end of oil pipe (9) connects with lubricating oil return chamber (3), and lubricating oil return chamber (3) are provided with lubricating oil return hole (8)；
Ensure that bearing lubrication effect, avoid that flow of lubrication is excessive causes waste simultaneously, preferably the flow of lubrication of fuel feed hole is set
Being set to 8-10L/min, the internal diameter of corresponding spray bar is set to 3mm, it is ensured that good lubricant effect.
Present configuration avoids interference frequency, owing to this assay device is for high-speed working condition (n > 60000r/min), design
Time make the natural frequency of apparatus structure avoid power frequency and the natural frequency of rotor so that it is there is enough rigidity and stability, keep away
Exempt from, owing to rotor oscillation causes resonance, to produce interfering frequency.
As shown in Figure 1, Figure 2, Figure 3, Figure 4, the integrated liquid rocket engine turbopump rotor height quick-action of the present invention is special
Property assay device is the device for testing experiment part, and described testpieces includes: rotary shaft, elastic supporting member for supporting optical member, bearing；
Elastic supporting member for supporting optical member is installed on the rotary shaft, and elastic supporting member for supporting optical member is provided with through hole, and through hole one end connects spray in the middle of bearing
The other end of oil pipe (14), through hole another rectify countershaft holding；Elastic supporting member for supporting optical member: include flange, elastic support；
Flange is connected with bearing by elastic support, and elastic support can reduce the support stiffness between flange and bearing；
Bearing holder (housing, cover) fills on the rotary shaft, and rotary shaft can rotate in bearing；
Need a motor, motor output shaft be connected with the rotary shaft of testpieces, enable motor output shaft to drive examination
The rotary shaft testing part rotates, and integrated liquid rocket engine turbopump rotor high speed dynamic response test method of testing is:
(1) bearing holder (housing, cover) is filled on the rotary shaft, elastic supporting member for supporting optical member is arranged on the bearing of testpieces；
(2) testpieces is placed in tile fragment on device (1), makes the other end of spray bar (14) in the middle of bearing insert test
In oilhole on the elastic supporting member for supporting optical member of part；Radially locating surface (11) laminating of the elastic support of testpieces and rotor supports；Flange with
Rotor supports axial locating surface (10) is fixing to be connected
(3) tile fragment under device (2) is fastened with tile fragment on device (1) and fastens；
(4) regulation bearing two survey lubrication spray bar (9) position, make bearing two survey lubrication spray bar (9) another rectify right
Ball in bearing；
(5) integrated liquid rocket engine turbopump rotor high speed test installation for dynamic characteristics is arranged on test rocker
On, and spacing by dowel hole；
(6) motor output shaft is connected with the rotary shaft of testpieces, enables the rotation of motor output shaft motoring ring test part
Axle rotates；
(7) at Sensor, current vortex sensor is installed, adjusts the position of current vortex sensor, make current vortex sensor
Measurement voltage between 10～12V；
(8) start motor, the speed setting of motor output shaft is rotated 5 minutes at 500r/min, then motor is exported
The rotating speed of axle improves to maximum speed 60000r/min；
(9) current vortex sensor gathers the vibration data of testpieces.
Utilize the integrated liquid rocket engine turbopump rotor high speed test installation for dynamic characteristics of the present invention to testpieces
Testing, gained test data is as shown in Figure 5.In Fig. 5, abscissa is test speed, and vertical coordinate top is vibration displacement peak-to-peak
Value, bottom is vibration phase, and in Fig. 5, three curve rotating speeds respectively rise to survey close to during 60000r/min three diverse locations from 0
Vibration displacement peak-to-peak value measured by Dian.Curve from Fig. 5 this it appears that the critical speed of rotor is 30000r/min,
During critical speed, vibration displacement peak-to-peak value is less than 90 μm, shows that testpieces amount of unbalance at high speeds is less, reaches excellent
Elegant vibration level.Can be seen that trial curve is smooth steadily simultaneously, show that testpieces assembly precision and accuracy of alignment are higher, and
And bearing lubrication is the most without exception.Demonstrate designed apparatus structure natural frequency can effectively avoid the power frequency of testpieces with
Natural frequency, has enough rigidity and stability, it is to avoid owing to rotor oscillation causes resonance, produce interfering frequency.
Claims (5)
1. integrated liquid rocket engine high-speed turbine pump rotor test installation for dynamic characteristics, it is characterised in that: include on device
Tile fragment (2), lubricating oil return chamber (3), bearing central oiling oil circuit (4), lubricating oil fuel feed hole (5), dress under tile fragment (1), device
Put outside axial locating surface (6), device outer radial locating surface (7), lubricating oil return hole (8), bearing two survey lubrication spray bar
(9), rotor supports axial locating surface (10), rotor supports radially locating surface (11), Sensor (12), dowel hole
(13), spray bar (14) in the middle of bearing；
On device, under tile fragment (1) and device, tile fragment (2) is the half of hollow semi-cylinders body, on device under tile fragment (1) and device
Tile fragment (2) can make up a hollow semi-cylinders body, hollow half that on device, under tile fragment (1) and device, tile fragment (2) forms
Cylindrical two faces of cylinder are near hollow position as rotor supports axial locating surface (10), and hollow semi-cylinders body is near two
The inner surface on the face of cylinder is as rotor supports radially locating surface (11), rotor supports axial locating surface (10) and rotor supports radially
Locating surface (11) is ring surface, provides for rotor and supports；On device under tile fragment (1), device on the outer arcuate surface of tile fragment (2)
It is respectively arranged with a protruding annulus near two faces of cylinder, and two protruding annulus are coaxial with hollow semi-cylinders body；Two projections
Annulus on device outer radial locating surface (7) dowel hole (13) is set, it is possible to insert alignment pin make assay device fix；
The front of protruding annulus is device outer radial locating surface (7), and side is the outside axial locating surface (6) of device；Hollow half
Cylindrical two faces of cylinder respectively arrange two or more Sensor (12), and two of the outer arcuate face at hollow semi-cylinders body
Two or more Sensor (12) is set between the annulus of individual projection；
Device outer radial locating surface (7) on two protruding annulus respectively arranges one group of lubricating oil fuel feed hole (5), hollow half
Between two protruding annulus in cylindrical outer arcuate face, lubricating oil return hole (8) is set at protruding annulus, is leaning on
On the rotor supports on one face of cylinder of near-space heart semicylinder radially locating surface (11), bearing two is set and surveys lubrication spray bar
(9), arranging spray bar (14) in the middle of bearing on another face of cylinder of hollow semi-cylinders body, lubricating oil return chamber (3) are arranged
On device under tile fragment (1) and device in tile fragment (2)；And lubricating oil return chamber (3) tile fragment under tile fragment (1) and device on device
(2) connection in；
Being provided with bearing central oiling oil circuit (4) on device in tile fragment (1), one end of bearing central oiling oil circuit (4) connects
One group of lubricating oil fuel feed hole (5), the other end of bearing central oiling oil circuit (4) connects one end of spray bar (14) in the middle of bearing,
In the middle of bearing, the other end of spray bar (14) connects lubricating oil return chamber (3)；
One end that another group lubricating oil fuel feed hole (5) surveys lubrication spray bar (9) with bearing two connects, and lubrication spray bar surveyed by bearing two
(9) the other end connects with lubricating oil return chamber (3), and lubricating oil return chamber (3) are provided with lubricating oil return hole (8).
Integrated liquid rocket engine high-speed turbine pump rotor test installation for dynamic characteristics the most according to claim 1, its
It is characterised by: the two or more sensor arranged between two protruding annulus in the outer arcuate face of described hollow semi-cylinders body
In measuring point (12), at least Sensor (12) is vertical with the line in the axle center of hollow semi-cylinders body.
Integrated liquid rocket engine high-speed turbine pump rotor test installation for dynamic characteristics the most according to claim 1, its
It is characterised by: described device outer radial locating surface (7) place plane is with device outside axial locating surface (6) place plane just
Hand over, and the outside axial locating surface (6) of device is parallel with two faces of cylinder.
Integrated liquid rocket engine high-speed turbine pump rotor test installation for dynamic characteristics the most according to claim 1, its
It is characterised by: another proper bearing to testpieces of lubrication spray bar (9) surveyed by described bearing two.
Integrated liquid rocket engine high-speed turbine pump rotor test installation for dynamic characteristics the most according to claim 1, its
It is characterised by: the oilhole of another proper elastic supporting member for supporting optical member to testpieces of spray bar (14) in the middle of bearing.
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| CN107014562A (en) * | 2017-04-26 | 2017-08-04 | 北京航天动力研究所 | A kind of liquid-propellant rocket engine turbine pump flex rotor high-speed balancing supporting arrangement |
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| CN108225783B (en) * | 2016-12-15 | 2020-01-31 | 中国航发商用航空发动机有限责任公司 | Method and device for balancing fan rotor of aviation turbofan engine |
| CN107014562A (en) * | 2017-04-26 | 2017-08-04 | 北京航天动力研究所 | A kind of liquid-propellant rocket engine turbine pump flex rotor high-speed balancing supporting arrangement |
| CN107014562B (en) * | 2017-04-26 | 2023-07-14 | 北京航天动力研究所 | High-speed dynamic balance supporting device for flexible rotor of turbopump of liquid rocket engine |
| CN115306592A (en) * | 2022-08-09 | 2022-11-08 | 北京理工大学 | Integrated self-rotating system of ultrahigh rotating speed shaft machine |
| CN115306592B (en) * | 2022-08-09 | 2024-07-05 | 北京理工大学 | Ultra-high rotation speed shaft machine integrated spin system |
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| CN106092558B (en) | 2018-05-22 |
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