CN110470434B - Device and method for air leakage test of turbocharger - Google Patents
Device and method for air leakage test of turbocharger Download PDFInfo
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- CN110470434B CN110470434B CN201910725369.1A CN201910725369A CN110470434B CN 110470434 B CN110470434 B CN 110470434B CN 201910725369 A CN201910725369 A CN 201910725369A CN 110470434 B CN110470434 B CN 110470434B
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- turbine
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- isolation cover
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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 invention provides a device for a gas leakage test of a turbocharger, which comprises a gas compressor assembly, a turbine shaft, a magnetic impeller rotor, a turbine shaft, a magnetic turbine rotor, a bearing body at the gas compressor end, a bearing body at the gas turbine end, a first isolation cover and a second isolation cover, wherein the left end and the right end of the bearing body at the gas compressor end are respectively and fixedly connected with the gas compressor assembly and the first isolation cover; the gas compressor end bearing body, the first isolation cover, the turbine end bearing body and the second isolation cover are connected through a screw rod. The turbocharger is divided into two independent closed units by changing the shaft structure of the turbocharger, the compressor and the turbine are flexibly connected in a non-contact manner and the rotating speeds are synchronous, so that the independent test of the gas leakage at the compressor end and the independent test of the gas leakage at the turbine end are realized, and the problem that the leakage flow at the sealing position of the turbine cannot be independently tested in the prior art is solved.
Description
Technical Field
The invention belongs to the technical field of electromechanics, and particularly relates to a device and a method for a turbocharger air leakage test.
Background
Both the compressor end and the turbine end of the turbocharger have sealing structures to minimize gas leakage from the compressor and turbine into the bearing cavity.
In the prior art, only the air leakage of the whole turbocharger can be measured, and the air flow leaked from a compressor seal or the air flow leaked from a turbine seal cannot be separately measured. The air leakage amount entering the bearing cavity from different sealing devices is known and evaluated, and the method is important for improving the design of the sealing structure and evaluating the influence of the air leakage amount at different positions on the performance of the engine.
The existing test method can not meet the requirements, and a test device and a test method which are targeted and can respectively measure the air leakage of the air compressor and the turbine of the turbocharger need to be found.
Disclosure of Invention
In view of the above, the invention aims to provide a device and a method for testing air leakage of a turbocharger, wherein the turbocharger is divided into two independent closed units by changing a shaft structure of the turbocharger, additionally arranging a magnetic rotor, a shielding case and a fastening device, a gas compressor and a turbine are flexibly and non-contactingly connected and rotate synchronously, so that the independent test of the air leakage at the gas compressor end and the independent test of the air leakage at the turbine end are realized, the problem that the leakage flow at the sealing position of the gas compressor can not be independently tested in the prior art is solved, and the device and the method are used for improving the design of a sealing structure of the turbocharger and evaluating the influence of the air leakage at different positions on the performance of an engine.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
the invention provides a device for a gas leakage test of a turbocharger, which comprises a compressor assembly, a turbine assembly, an impeller shaft, an impeller magnetic rotor, a turbine shaft, a turbine magnetic rotor, a compressor end bearing body, a turbine end bearing body, a first isolation cover, a second isolation cover, a plurality of lead screws, a compressor gas leakage measuring instrument and a turbine gas leakage measuring instrument, wherein the left end and the right end of the compressor end bearing body are respectively and fixedly connected with the compressor assembly and the first isolation cover; the left end and the right end of the turbine end bearing body are respectively fixedly connected with a turbine assembly and a second isolation cover, a turbine shaft is fixed in the turbine end bearing body through a bearing, one end of the turbine shaft is connected with a turbine of the turbine assembly, and the other end of the turbine shaft is fixedly connected with a turbine magnetic rotor; the left end of each lead screw is fixedly connected with a compressor end bearing body and a first isolation cover, and the right end of each lead screw is fixedly connected with a turbine end bearing body and a second isolation cover; the air compressor air leakage quantity measuring instrument is connected with an air compressor end oil return hole on the air compressor end bearing body during testing; and the turbine air leakage quantity measuring instrument is connected with a turbine end oil return hole of the turbine end bearing body during testing.
Furthermore, the first isolation cover and the second isolation cover are both of a semi-closed revolving body structure and are arranged oppositely back to back.
Further, the compressor assembly comprises a volute, a shaft end nut, a compressor impeller, a volute pressing plate, a compressor screw, a shaft sleeve, a compressor sealing ring, a back plate screw and a back plate, and the volute is connected with the back plate through the compressor screw; the back disc is connected with the compressor end bearing body through the back disc screw; the left side of the impeller shaft is sequentially connected with the shaft sleeve, the compressor impeller and the shaft end nut; the shaft seal sleeve is provided with the compressor sealing ring, and the compressor sealing ring is internally connected with a central hole of the back plate.
Furthermore, the turbine assembly comprises a turbine box pressing plate, a turbine box screw, a heat insulation cover, a turbine box, a turbine end sealing ring and a turbine, the right side of the turbine shaft is connected with the turbine, the turbine end sealing ring is arranged at the joint of the turbine shaft and the turbine, and the turbine end sealing ring is internally connected with a center hole at the right end of the turbine end bearing body; the turbine end bearing body is connected with the turbine box through the turbine box pressure plate and the turbine box screw.
Furthermore, a plurality of holes are formed in connecting flanges of the compressor end bearing body and the turbine end bearing body; a plurality of holes are also formed in the connecting flanges of the first isolation cover and the second isolation cover; each lead screw is sleeved with a connecting nut, and each connecting nut on the left side fixes the compressor end bearing body and the first isolation cover together; and each connecting nut on the right fixes the turbine end bearing body and the second isolation cover together.
The invention also provides a test method for testing by adopting the device for testing the air leakage of the turbocharger, which comprises the following steps:
step 1, mounting a device for air leakage test of a turbocharger on a turbocharger test bench, and connecting an air inlet pipeline, an air outlet pipeline and a lubricating oil inlet pipeline;
step 2, connecting an oil return hole at the end of the compressor with a gas leakage quantity measuring instrument of the compressor; the oil return hole at the turbine end is connected with a turbine air leakage quantity measuring instrument;
step 4, switching the combustion chamber of the turbocharger test bed into a self-circulation state after ignition;
and 6, after the test is finished, reducing the oil supply amount, reducing the rotating speed of the turbine to cool down, and flameout the combustion chamber.
Compared with the prior art, the system and the method have the following advantages:
the turbocharger is divided into two independent closed units, so that the independent test of the air leakage at the compressor end and the independent test of the air leakage at the turbine end are realized, and the problem that the leakage flow at the sealing position of the compressor and the leakage flow at the sealing position of the turbine cannot be independently tested in the prior art is solved.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate an embodiment of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic view of a device for testing air leakage of a turbocharger according to an embodiment of the present invention.
Description of reference numerals:
1-volute, 2-shaft end nut, 3-compressor impeller, 4-volute pressure plate, 5-compressor screw, 6-shaft sealing sleeve, 7-compressor sealing ring, 8-back plate screw, 9-back plate, 10-compressor end bearing body, 11-bearing I, 12-compressor end oil return hole, 13-impeller shaft, 14-connecting nut, 15-bearing II, 16-lead screw, 17-impeller magnetic rotor, 18-gland nut I, 19-spanner hole I, 20-isolation cover I, 21-isolation cover II, 22-spanner hole II, 23-gland nut II, 24-turbine magnetic rotor, 25-turbine shaft, 26-turbine end bearing body, 27-bearing III, 28-turbine end oil return hole, 29-a turbine box pressure plate, 30-a turbine box screw, 31-a heat insulation cover, 32-a bearing four, 33-a turbine box, 34-a turbine end sealing ring, 35-a turbine, 36-a compressor air leakage quantity measuring instrument and 37-a turbine air leakage quantity measuring instrument.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Fig. 1 is a schematic structural diagram of a device for testing air leakage of a turbocharger according to this embodiment, where the testing system includes a compressor assembly, a turbine assembly, a compressor end bearing body 10, an impeller shaft 13, a plurality of lead screws 16, an impeller magnetic rotor 17, a first shielding cover 20, a second shielding cover 21, a turbine magnetic rotor 24, a turbine shaft 25, a turbine end bearing body 26, a compressor air leakage measuring instrument 36, and a turbine air leakage measuring instrument 37;
wherein the compressor component comprises a volute 1, a shaft end nut 2, a compressor impeller 3, a volute pressure plate 4, a compressor screw 5, a shaft seal sleeve 6, a compressor seal ring 7, a back disc screw 8 and a back disc 9, the turbine component comprises a turbine box pressure plate 29, a turbine box screw 30, a heat insulation cover 31, a turbine box 33, a turbine end seal ring 34 and a turbine 35,
the volute 1 is connected with the back disc 9 through the compressor screw 5; the back disc 9 is connected with the compressor end bearing body 10 through the back disc screw 8;
a plurality of holes are formed in the connecting flanges of the compressor end bearing body 10 and the turbine end bearing body 26; the first isolation cover 20 and the second isolation cover 21 are both of a semi-closed revolving body structure, and a plurality of holes are formed in connecting flanges of the first isolation cover 20 and the second isolation cover 21; each lead screw 16 is sleeved with 4 connecting nuts 14, and each 2 connecting nuts 14 on the left side fix the compressor end bearing body 10 and the first isolation cover 20 together; the right 2 connecting nuts 14 fix the turbine end bearing body 26 and the second isolation cover 21 together; the first isolation cover 20 and the second isolation cover 21 are opposite back to back;
the turbine end bearing body 26 is connected with the turbine box 33 through the turbine box pressure plate 29 and the turbine box screw 30;
a first bearing 11 and a second bearing 15 are fixed in the compressor end bearing body 10, and the impeller shaft 13 is fixed in the first bearing 11 and the second bearing 15; the left side of the impeller shaft 13 is sequentially connected with the shaft sleeve 6, the compressor impeller 3 and the shaft end nut 2; the shaft sleeve 6 is provided with the compressor sealing ring 7, and the compressor sealing ring 7 is internally connected with a central hole of the back disc 9;
the right side of the impeller shaft 13 is connected with the impeller magnetic rotor 17, and the first compression nut 18 connects the impeller shaft 13 and the impeller magnetic rotor 17 together; the first compression nut 18 is provided with the first wrench hole 19, so that the operation is convenient;
a third bearing 27 and a fourth bearing 32 are fixed in the turbine end bearing body 26, and the turbine shaft 25 is fixed in the third bearing 27 and the fourth bearing 32; the right side of the turbine shaft 25 is connected with the turbine 35; the turbine end sealing ring 34 is arranged at the joint of the turbine shaft 25 and the turbine 35, and the turbine end sealing ring 34 is inscribed in the central hole at the right end of the turbine end bearing body 26; the left side of the turbine shaft 25 is connected with the turbine magnetic rotor 24, and the second compression nut 23 is used for connecting the turbine shaft 25 and the turbine magnetic rotor 24 together; the second wrench hole 22 is formed in the second compression nut 23, so that the operation is convenient;
all the rotating members in the above-mentioned supercharger device are concentric in the center.
The test method for testing by the test device comprises the following steps:
step 1, mounting a device for a gas leakage test of a turbocharger on a turbocharger test bench, and finishing connection of an air inlet pipeline, an air outlet pipeline and a lubricating oil inlet pipeline;
step 2, connecting the compressor end oil return hole 12 with a compressor air leakage measuring instrument 36; the turbine end oil return hole 28 is connected with a turbine air leakage measuring instrument 37;
step 4, switching the combustion chamber of the test bed to a self-circulation state after ignition;
and 6, after the test is finished, reducing the oil supply amount, reducing the rotating speed of the turbine 35 for cooling, and flameout the combustion chamber.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (6)
1. The utility model provides a device is used in turbocharger's air leakage test which characterized in that: comprises a compressor assembly, a turbine shaft (13), a magnetic impeller rotor (17), a turbine shaft (25), a magnetic turbine rotor (24), a bearing body at the compressor end (10), a bearing body at the turbine end (26), a first isolation cover (20), a second isolation cover (21) and a plurality of lead screws (16),
the left end and the right end of the compressor end bearing body (10) are respectively fixedly connected with a compressor assembly and a first isolation cover (20), an impeller shaft (13) is fixed in the compressor end bearing body (10) through a bearing, one end of the impeller shaft (13) is connected with a compressor impeller (3) of the compressor assembly, the other end of the impeller shaft is fixedly connected with an impeller magnetic rotor (17), and the impeller magnetic rotor (17) and the impeller shaft (13) are both positioned in the first isolation cover (20);
the left end and the right end of the turbine end bearing body (26) are fixedly connected with a turbine assembly and a second isolation cover (21) respectively, a turbine shaft (25) is fixed in the turbine end bearing body (26) through a bearing, one end of the turbine shaft (25) is connected with a turbine (35) of the turbine assembly, the other end of the turbine shaft (25) is fixedly connected with a turbine magnetic rotor (24), and the turbine magnetic rotor (24) and the turbine shaft (25) are located inside the second isolation cover (21);
the left end of each lead screw (16) is fixedly connected with a compressor end bearing body (10) and a first isolation cover (20), and the right end of each lead screw is fixedly connected with a turbine end bearing body (26) and a second isolation cover (21).
2. The apparatus of claim 1, wherein: the first isolation cover (20) and the second isolation cover (21) are both of a semi-closed revolving body structure and are arranged oppositely back to back.
3. The apparatus of claim 1, wherein: the compressor assembly comprises a volute (1), a shaft end nut (2), a compressor impeller (3), a volute pressing plate (4), a compressor screw (5), a shaft seal sleeve (6), a compressor seal ring (7), a back plate screw (8) and a back plate (9), and the volute (1) is connected with the back plate (9) through the compressor screw (5); the back disc (9) is connected with a gas compressor end bearing body (10) through a back disc screw (8); the left side of the impeller shaft (13) is sequentially connected with the shaft sleeve (6), the compressor impeller (3) and the shaft end nut (2); the shaft sleeve (6) is provided with the compressor sealing ring (7), and the compressor sealing ring (7) is internally connected with a central hole of the back plate (9).
4. The apparatus of claim 1, wherein: the turbine assembly comprises a turbine box pressing plate (29), a turbine box screw (30), a heat insulation cover (31), a turbine box (33), a turbine end sealing ring (34) and a turbine (35), the right side of the turbine shaft (25) is connected with the turbine (35), the turbine end sealing ring (34) is arranged at the joint of the turbine shaft (25) and the turbine (35), and the turbine end sealing ring (34) is internally connected with a central hole at the right end of the turbine end bearing body (26); the turbine end bearing body (26) is connected with the turbine box (33) through the turbine box pressure plate (29) and the turbine box screw (30).
5. The apparatus of claim 1, wherein: a plurality of holes are formed in connecting flanges of the compressor end bearing body (10) and the turbine end bearing body (26); a plurality of holes are also formed in the connecting flanges of the first isolation cover (20) and the second isolation cover (21); each lead screw (16) is sleeved with 4 connecting nuts (14), and each 2 connecting nuts (14) on the left fix the compressor end bearing body (10) and the first isolation cover (20) together; and every 2 connecting nuts (14) on the right fix the turbine end bearing body (26) and the second isolation cover (21) together.
6. A test method for performing a test using the apparatus of any one of claims 1 to 5, characterized by comprising the steps of:
step 1, mounting a device for air leakage test of a turbocharger on a turbocharger test bench, and connecting an air inlet pipeline, an air outlet pipeline and a lubricating oil inlet pipeline;
step 2, connecting an oil return hole (12) at the end of the compressor with a gas leakage quantity measuring instrument (36) of the compressor; the turbine end oil return hole (28) is connected with a turbine air leakage quantity measuring instrument (37);
step 3, driving a turbine (35) to rotate by using an external air source of the turbocharger test stand;
step 4, switching the combustion chamber of the turbocharger test bed into a self-circulation state after ignition;
step 5, gradually increasing the rotating speed of the turbine (35), and simultaneously recording respective numerical values of the compressor air leakage quantity measuring instrument (36) and the turbine air leakage quantity measuring instrument (37) under different rotating speeds;
and 6, after the test is finished, reducing the oil supply amount, reducing the rotating speed of the turbine (35) for cooling, and flameout the combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201910725369.1A CN110470434B (en) | 2019-08-07 | 2019-08-07 | Device and method for air leakage test of turbocharger |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910725369.1A CN110470434B (en) | 2019-08-07 | 2019-08-07 | Device and method for air leakage test of turbocharger |
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| CN110470434A CN110470434A (en) | 2019-11-19 |
| CN110470434B true CN110470434B (en) | 2021-04-09 |
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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 |
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