CN110470434A - A kind of air leakage test device and the test method of turbocharger - Google Patents
A kind of air leakage test device and the test method of turbocharger Download PDFInfo
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- CN110470434A CN110470434A CN201910725369.1A CN201910725369A CN110470434A CN 110470434 A CN110470434 A CN 110470434A CN 201910725369 A CN201910725369 A CN 201910725369A CN 110470434 A CN110470434 A CN 110470434A
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- turbine
- compressor
- bearing body
- isolation cover
- end bearing
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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
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/26—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
Abstract
The present invention provides a kind of air leakage test devices of turbocharger, including compressor assemblies, turbine assembly, impeller shaft, impeller magnet rotor, turbine wheel shaft, turbine magnet rotor, compressor end bearing body, turbine end bearing body, isolation cover one, isolation cover two, the left and right ends of the compressor end bearing body are respectively fixedly connected with compressor assemblies and isolation cover one, and the left and right ends of the turbine end bearing body are respectively fixedly connected with turbine assembly and isolation cover two；Compressor end bearing body, isolation cover one, turbine end bearing body and isolation cover two are connected by lead screw.The axle construction that the present invention passes through change turbocharger, turbocharger is divided into two independent closed cells, compressor and turbine implement to flexible non-contact connects and revolving speed is synchronous, the independent test for generator terminal air leakage of calming the anger and the independent test of turbine end air leakage are realized, solves the problems, such as that the prior art cannot individually test at compressor sealing leakage flow at the sealing of leakage flow turbine.
Description
Technical field
The invention belongs to field of electromechanical technology, more particularly, to a kind of air leakage test device of turbocharger and examination
Proved recipe method.
Background technique
Turbocharger calm the anger generator terminal and turbine end has sealing structure, to be reduced as far as possible from compressor and turbine
Into the quantity of gas leakage of bearing body cavity.
The prior art can only measure the air leakage of entire turbocharger, can not individually test from compressor sealing place
Leaked gas flow or from turbine sealing place leaked gas flow.Understand and assess and enters bearing from different sealing devices
The air leakage of body cavity, it is critically important for improving the influence of design of Sealing Structure, evaluation different location air leakage to engine performance.
Existing test method cannot be met the requirements, and need to find pressure that is targeted, can measuring turbocharger respectively
The experimental rig and test method of mechanism of qi and turbine air leakage.
Summary of the invention
In view of this, the present invention is directed to propose air leakage test device and the test method of a kind of turbocharger, lead to
It crosses and changes the axle construction of turbocharger, installs magnet rotor, isolation cover and clamp device additional, turbocharger is divided into two independences
Closed cell, compressor and turbine implement to flexible non-contact connects and revolving speed is synchronous, realizes generator terminal gas leakage of calming the anger
The independent test of amount and the independent test of turbine end air leakage solve the prior art and cannot individually test at compressor sealing and let out
At leakage current amount turbine sealing the problem of leakage flow, for improving seal structure of turbocharger design, evaluation different location leakage
Influence of the tolerance to engine performance.
In order to achieve the above objectives, the technical scheme of the present invention is realized as follows:
One aspect of the present invention provides a kind of air leakage test device of turbocharger, including compressor assemblies, whirlpool
Wheel assembly, impeller shaft, impeller magnet rotor, turbine wheel shaft, turbine magnet rotor, compressor end bearing body, turbine end bearing body, isolation cover
One, isolation cover two, several lead screws, compressor air-leakage quantity measuring instrument and turbine air-leakage quantity measuring instrument, the compressor end bearing body
Left and right ends be respectively fixedly connected with compressor assemblies and isolation cover one, pass through bearing fixation impeller in compressor end bearing body
The compressor impeller of axis, described impeller shaft one end and compressor assemblies connects, and the other end is fixedly connected with impeller magnet rotor；The whirlpool
The left and right ends of wheel end bearing body are respectively fixedly connected with turbine assembly and isolation cover two, are fixed in turbine end bearing body by bearing
The turbine of turbine wheel shaft, described turbine wheel shaft one end and turbine assembly connects, and the other end is fixedly connected with turbine magnet rotor；Each silk
The left end of thick stick is fixedly connected with compressor end bearing body and isolation cover one, and right end is fixedly connected with turbine end bearing body and isolation cover two；
The compressor air-leakage quantity measuring instrument is connect when testing with the generator terminal oil return hole of calming the anger on compressor end bearing body；The turbine leakage
Tolerance measuring instrument is connect when testing with the turbine end oil return hole of turbine end bearing body.
Further, the isolation cover one and the isolation cover two are semiclosed rotary structure, and opposite back-to-back
Setting.
Further, the compressor assemblies include spiral case, shaft end nut, compressor impeller, spiral case pressing plate, compressor spiral shell
Nail, axle envelope set, compressor sealing ring, back valve snail follows closely and back disk, and the spiral case passes through machine screw and the back disk company of calming the anger
It is connected together；The back disk is followed closely by the back valve snail and is linked together with the compressor end bearing body；The impeller shaft
The left side is sequentially connected the axle envelope set, compressor impeller and shaft end nut；The axle envelope puts on the setting compressor sealing
The centre bore of the back disk is inscribed in ring, the compressor sealing ring.
Further, the turbine assembly includes that turbine box pressing plate, turbine box screw, heat shield, turbine box, turbine end are close
Seal ring, turbine, the right of the turbine wheel shaft connect the turbine, the junction setting whirlpool of the turbine wheel shaft and the turbine
End sealing ring is taken turns, the centre bore of the turbine end bearing body right end is inscribed in the turbine end sealing ring；The turbine end bearing body
It is linked together by the turbine box pressing plate and the turbine box screw with the turbine box.
Further, there are several holes on the connecting flange of the compressor end bearing body and the turbine end bearing body；
Also there are several holes on the connecting flange of isolation cover one and the isolation cover two；Each lead screw is socketed an attaching nut, left
The compressor end bearing body and the isolation cover one are fixed together by each attaching nut in side；The each attaching nut in the right will
The turbine end bearing body and the isolation cover two are fixed together.
Another aspect of the present invention provides the examination tested using the air leakage test of above-mentioned turbocharger with device
Proved recipe method, includes the following steps:
Step 1, the air leakage test of turbocharger is mounted on turbocharger test rack with device, connection is empty
The inlet ductwork of gas import and export pipeline and lubricating oil；
Step 2, generator terminal of calming the anger oil return hole connects compressor air-leakage quantity measuring instrument；The turbine end oil return hole connection turbine leakage
Tolerance measuring instrument；
Step 3, with the outer gas source driving turbine rotation of turbocharger test rack；
Step 4, self-loopa state is switched to after the combustion chamber ignition of turbocharger test rack；
Step 5, the revolving speed of turbine is gradually risen, while being recorded under different rotating speeds, compressor air-leakage quantity measuring instrument and whirlpool
Take turns the respective numerical value of air-leakage quantity measuring instrument；
Step 6, after test, reduce fuel delivery, reduce secondary speed and carry out cooling down, combustion chamber is flame-out.
Compared with the existing technology, system and method for the present invention has the advantage that
Turbocharger is divided into two independent closed cells by the present invention, is realized the independent of generator terminal air leakage of calming the anger and is surveyed
The independent test of examination and turbine end air leakage, leakage flow turbine at compressor sealing cannot individually be tested by solving the prior art
At sealing the problem of leakage flow.
Detailed description of the invention
The attached drawing for constituting a part of the invention is used to provide further understanding of the present invention, schematic reality of the invention
It applies example and its explanation is used to explain the present invention, do not constitute improper limitations of the present invention.In the accompanying drawings:
A kind of air leakage test of turbocharger of Fig. 1, the embodiment of the present invention schematic diagram of device.
Description of symbols:
1- spiral case, 2- shaft end nut, 3- compressor impeller, 4- spiral case pressing plate, 5- calm the anger machine screw, 6- axle envelope set, 7- pressure
Mechanism of qi sealing ring, 8- back valve snail nail, 9- back disk, 10- compressor end bearing body, 11- bearing one, 12- calm the anger generator terminal oil return hole,
13- impeller shaft, 14- attaching nut, 15- bearing two, 16- lead screw, 17- impeller magnet rotor, 18- clamp nut one, 19- driving hole
One, 20- isolation cover one, 21- isolation cover two, 22- driving hole two, 23- clamp nut two, 24- turbine magnet rotor, 25- turbine wheel shaft,
26- turbine end bearing body, 27- bearing three, 28- turbine end oil return hole, 29- turbine box pressing plate, 30- turbine box screw, 31- are heat-insulated
Cover, 32- bearing four, 33- turbine box, 34- turbine end sealing ring, 35- turbine, 36- compressor air-leakage quantity measuring instrument, 37- turbine
Air-leakage quantity measuring instrument.
Specific embodiment
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the present invention can phase
Mutually combination.
In the description of the present invention, it is to be understood that, term " center ", " longitudinal direction ", " transverse direction ", "upper", "lower",
The orientation or positional relationship of the instructions such as "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is
It is based on the orientation or positional relationship shown in the drawings, is merely for convenience of description of the present invention and simplification of the description, rather than instruction or dark
Show that signified device or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as pair
Limitation of the invention.In addition, term " first ", " second " etc. are used for description purposes only, it is not understood to indicate or imply phase
To importance or implicitly indicate the quantity of indicated technical characteristic.The feature for defining " first ", " second " etc. as a result, can
To explicitly or implicitly include one or more of the features.In the description of the present invention, unless otherwise indicated, " multiple "
It is meant that two or more.
In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, term " installation ", " phase
Even ", " connection " shall be understood in a broad sense, for example, it may be being fixedly connected, may be a detachable connection, or be integrally connected；It can
To be mechanical connection, it is also possible to be electrically connected；It can be directly connected, can also can be indirectly connected through an intermediary
Connection inside two elements.For the ordinary skill in the art, above-mentioned term can be understood by concrete condition
Concrete meaning in the present invention.
The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is a kind of air leakage test of turbocharger of the present embodiment structural schematic diagram of device, this pilot system
Including compressor assemblies, turbine assembly, compressor end bearing body 10, impeller shaft 13, several lead screws 16, impeller magnet rotor 17, every
From cover 1, isolation cover 2 21, turbine magnet rotor 24, turbine wheel shaft 25, turbine end bearing body 26, compressor air-leakage quantity measuring instrument
36, turbine air-leakage quantity measuring instrument 37；
Wherein, the compressor assemblies include spiral case 1, shaft end nut 2, compressor impeller 3, spiral case pressing plate 4, compressor spiral shell
Nail 5, axle envelope set 6, compressor sealing ring 7, back valve snail nail 8, back disk 9, the turbine assembly includes turbine box pressing plate 29, turbine box
Screw 30, heat shield 31, turbine box 33, turbine end sealing ring 34, turbine 35,
The spiral case 1 is linked together by the machine screw 5 of calming the anger with the back disk 9；The back disk 9 passes through the back
Valve snail nail 8 links together with the compressor end bearing body 10；
There are several holes on the connecting flange of the compressor end bearing body 10 and the turbine end bearing body 26；It is described every
It is semiclosed rotary structure, the connection of isolation cover 1 and the isolation cover 2 21 from cover 1 and the isolation cover 2 21
There are several holes on flange；Each lead screw 16 is socketed 4 attaching nuts 14, and every 2 attaching nuts 14 in the left side are by the pressure
Mechanism of qi end bearing body 10 and the isolation cover 1 are fixed together；Every 2 attaching nuts 14 in the right are by the turbine end bearing
Body 26 and the isolation cover 2 21 are fixed together；The isolation cover 1 and the isolation cover 2 21 are opposite back-to-back；
The turbine end bearing body 26 passes through the turbine box pressing plate 29 and the turbine box screw 30 and the turbine box
33 link together；
Bearing 1 and bearing 2 15, the bearing 1 and the bearing are fixed in the compressor end bearing body 10
The impeller shaft 13 is fixed in 2 15；The left side of the impeller shaft 13 is sequentially connected the axle envelope and covers 6, the compressor impeller 3
And the shaft end nut 2；There is the compressor sealing ring 7 on the axle envelope set 6, the compressor sealing ring 7 is inscribed described
Carry on the back the centre bore of disk 9；
The right of the impeller shaft 13 connects the impeller magnet rotor 17, and the clamp nut 1 is by the impeller shaft 13
It links together with the impeller magnet rotor 17；There is the driving hole 1 on the clamp nut 1, facilitates operation；
Bearing 3 27 and bearing 4 32, the bearing 3 27 and the bearing four are fixed in the turbine end bearing body 26
The turbine wheel shaft 25 is fixed in 32；The right of the turbine wheel shaft 25 connects the turbine 35；The turbine wheel shaft 25 and the turbine
There is the turbine end sealing ring 34 in 35 junction, and 26 right end of turbine end bearing body is inscribed in the turbine end sealing ring 34
Centre bore；The left side of the turbine wheel shaft 25 connects the turbine magnet rotor 24, and the clamp nut 2 23 is by the turbine wheel shaft 25
It links together with the turbine magnet rotor 24；There is the driving hole 2 22 on the clamp nut 2 23, facilitates operation；
The equal central coaxial of all revolving parts in above-mentioned supercharger arrangement.
The test method tested by above-mentioned experimental rig, includes the following steps:
Step 1, the air leakage test of turbocharger is mounted on turbocharger test rack with device, air
Import and export pipeline is connected with the inlet ductwork of lubricating oil and is finished；
Step 2, generator terminal of calming the anger oil return hole 12 connects compressor air-leakage quantity measuring instrument 36；The turbine end oil return hole 28 connects
Turbine air-leakage quantity measuring instrument 37；
Step 3, it is rotated with the outer gas source driving turbine 35 of test-bed, the turbine magnet rotor 24, the leaf can be made
It takes turns magnet rotor 17 and the compressor impeller 3 rotates synchronously；
Step 4, self-loopa state is switched to after the combustion chamber ignition of test-bed；
Step 5, the revolving speed of turbine 35 is gradually risen, while being recorded under different rotating speeds, compressor air-leakage quantity measuring instrument 36
With the respective numerical value of turbine air-leakage quantity measuring instrument 37；
Step 6, after test, reduce fuel delivery, reduce by 35 revolving speed of turbine and carry out cooling down, combustion chamber is flame-out.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Within mind and principle, any modification, equivalent replacement, improvement and so on be should all be included in the protection scope of the present invention.
Claims (6)
1. a kind of air leakage test device of turbocharger, it is characterised in that: including compressor assemblies, turbine assembly, leaf
Wheel shaft (13), impeller magnet rotor (17), turbine wheel shaft (25), turbine magnet rotor (24), compressor end bearing body (10), turbine end axis
Body (26), isolation cover one (20), isolation cover two (21) and several lead screws (16) are held,
The left and right ends of the compressor end bearing body (10) are respectively fixedly connected with compressor assemblies and isolation cover one (20), calm the anger
It is fixed impeller shaft (13) by bearing in generator terminal bearing body (10), the compressor of described impeller shaft (13) one end and compressor assemblies
Impeller (3) connection, the other end are fixedly connected with impeller magnet rotor (17)；
The left and right ends of the turbine end bearing body (26) are respectively fixedly connected with turbine assembly and isolation cover two (21), turbine end axis
It holding and passes through bearing fixed turbine axis (25) in body (26), the turbine (35) of described turbine wheel shaft (25) one end and turbine assembly connects,
The other end is fixedly connected with turbine magnet rotor (24)；
The left end of each lead screw (16) is fixedly connected with compressor end bearing body (10) and isolation cover one (20), and right end is fixed to be connected
Connect turbine end bearing body (26) and isolation cover two (21).
2. the apparatus according to claim 1, it is characterised in that: the isolation cover one (20) and the isolation cover two (21) are equal
For semiclosed rotary structure, and it is oppositely arranged back-to-back.
3. the apparatus according to claim 1, it is characterised in that: the compressor assemblies include spiral case (1), shaft end nut
(2), compressor impeller (3), spiral case pressing plate (4), machine screw of calming the anger (5), axle envelope set (6), compressor sealing ring (7), back valve snail
(8) and back disk (9) are followed closely, the spiral case (1) is linked together by machine screw of calming the anger (5) and back disk (9)；The back disk (9) is logical
Back valve snail nail (8) is crossed to link together with compressor end bearing body (10)；The left side of the impeller shaft (13) is sequentially connected axle envelope
Cover (6), compressor impeller (3) and shaft end nut (2)；The compressor sealing ring (7), institute are set on the axle envelope set (6)
State the centre bore of compressor sealing ring (7) inscribed back disk (9).
4. the apparatus according to claim 1, it is characterised in that: the turbine assembly includes turbine box pressing plate (29), turbine
Case screw (30), heat shield (31), turbine box (33), turbine end sealing ring (34), turbine (35), the right side of the turbine wheel shaft (25)
Side connects the turbine (35), the junction setting turbine end sealing ring of the turbine wheel shaft (25) and the turbine (35)
(34), the centre bore of turbine end bearing body (26) right end is inscribed in the turbine end sealing ring (34)；The turbine end bearing
Body (26) is linked together by the turbine box pressing plate (29) and the turbine box screw (30) with the turbine box (33).
5. the apparatus according to claim 1, it is characterised in that: the compressor end bearing body (10) and the turbine end axis
Holding on the connecting flange of body (26) has several holes；On the connecting flange of isolation cover one (20) and the isolation cover two (21) also
There are several holes；Each lead screw (16) is socketed (4) a attaching nut (14), and the left side will be described per (2) a attaching nut (14)
Compressor end bearing body (10) and the isolation cover one (20) are fixed together；It the right will be described per (2) a attaching nut (14)
Turbine end bearing body (26) and the isolation cover two (21) are fixed together.
6. the test method tested using the device any in claim 1 to 5, it is characterised in that including walking as follows
It is rapid:
Step 1, the air leakage test of turbocharger is mounted on turbocharger test rack with device, connects air
The inlet ductwork of import and export pipeline and lubricating oil；
Step 2, generator terminal of calming the anger oil return hole (12) connects compressor air-leakage quantity measuring instrument (36)；Turbine end oil return hole (28) connects whirlpool
It takes turns air-leakage quantity measuring instrument (37)；
Step 3, with outer gas source driving turbine (35) rotation of turbocharger test rack；
Step 4, self-loopa state is switched to after the combustion chamber ignition of turbocharger test rack；
Step 5, the revolving speed of turbine (35) is gradually risen, while being recorded under different rotating speeds, compressor air-leakage quantity measuring instrument (36)
With turbine air-leakage quantity measuring instrument (37) respective numerical value；
Step 6, after test, reduce fuel delivery, reduce turbine (35) revolving speed and carry out cooling down, combustion chamber is flame-out.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910725369.1A CN110470434B (en) | 2019-08-07 | 2019-08-07 | Device and method for air leakage test of turbocharger |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910725369.1A CN110470434B (en) | 2019-08-07 | 2019-08-07 | Device and method for air leakage test of turbocharger |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110470434A true CN110470434A (en) | 2019-11-19 |
| CN110470434B CN110470434B (en) | 2021-04-09 |
Family
ID=68510395
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910725369.1A Active CN110470434B (en) | 2019-08-07 | 2019-08-07 | Device and method for air leakage test of turbocharger |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0576859B1 (en) * | 1992-07-02 | 1996-08-14 | Sulzer Turbo AG | Turbo machine with axial dry gas seal |
| CN1358991A (en) * | 2002-01-28 | 2002-07-17 | 北京理工大学 | Platform for detecting leakage of pressurizing device |
| CN101832845A (en) * | 2010-04-22 | 2010-09-15 | 浙江大学 | Self-correcting system and method for sealing test of exhaust gas turbocharger |
| CN102589894A (en) * | 2012-03-01 | 2012-07-18 | 南京航空航天大学 | Micro gas compressor/turbine combined test bed and test method |
| CN104769229A (en) * | 2012-08-24 | 2015-07-08 | 康明斯有限公司 | Sensor apparatus, corresponding turbocharger and method of measuring a mass flow rate |
| CN105352676A (en) * | 2015-09-29 | 2016-02-24 | 北京理工大学 | Measurement method of air leakage of compressor and turbine of turbocharger |
| CN109356877A (en) * | 2018-12-12 | 2019-02-19 | 中国北方发动机研究所(天津) | A kind of sealing structure of turbocharger |
-
2019
- 2019-08-07 CN CN201910725369.1A patent/CN110470434B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0576859B1 (en) * | 1992-07-02 | 1996-08-14 | Sulzer Turbo AG | Turbo machine with axial dry gas seal |
| CN1358991A (en) * | 2002-01-28 | 2002-07-17 | 北京理工大学 | Platform for detecting leakage of pressurizing device |
| CN101832845A (en) * | 2010-04-22 | 2010-09-15 | 浙江大学 | Self-correcting system and method for sealing test of exhaust gas turbocharger |
| CN102589894A (en) * | 2012-03-01 | 2012-07-18 | 南京航空航天大学 | Micro gas compressor/turbine combined test bed and test method |
| CN104769229A (en) * | 2012-08-24 | 2015-07-08 | 康明斯有限公司 | Sensor apparatus, corresponding turbocharger and method of measuring a mass flow rate |
| CN105352676A (en) * | 2015-09-29 | 2016-02-24 | 北京理工大学 | Measurement method of air leakage of compressor and turbine of turbocharger |
| CN109356877A (en) * | 2018-12-12 | 2019-02-19 | 中国北方发动机研究所(天津) | A kind of sealing structure of turbocharger |
Non-Patent Citations (1)
| Title |
|---|
| 中华人民共和国机械工业部: "《JB/T 9752.2-1999》", 31 December 1999 * |
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| CN110470434B (en) | 2021-04-09 |
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