CN113864223B - Structure and method for measuring back pressure of turbocharger wheel - Google Patents
Structure and method for measuring back pressure of turbocharger wheel Download PDFInfo
- Publication number
- CN113864223B CN113864223B CN202111285390.8A CN202111285390A CN113864223B CN 113864223 B CN113864223 B CN 113864223B CN 202111285390 A CN202111285390 A CN 202111285390A CN 113864223 B CN113864223 B CN 113864223B
- Authority
- CN
- China
- Prior art keywords
- pressure
- turbine
- compressor
- intermediate body
- pressure channel
- 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.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 13
- 238000007789 sealing Methods 0.000 claims abstract description 21
- 238000009530 blood pressure measurement Methods 0.000 claims description 10
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- 229910002804 graphite Inorganic materials 0.000 claims description 6
- 239000010439 graphite Substances 0.000 claims description 6
- 230000006835 compression Effects 0.000 claims description 3
- 238000007906 compression Methods 0.000 claims description 3
- 238000012360 testing method Methods 0.000 abstract description 3
- 238000002955 isolation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
The invention discloses a back pressure measuring structure and a back pressure measuring method of a turbocharger, wherein the back pressure measuring structure comprises a compressor impeller, a compressor air seal ring, an intermediate body, a pressure sensor, a screw plug, a turbine end heat shield and a turbine, wherein a pressure channel is arranged on the intermediate body, the compressor air seal ring and the turbine end heat shield, sealing threads are arranged at the joint of the pressure channel of the intermediate body and the compressor air seal ring and the turbine end heat shield, the pressure channel is plugged through the screw plug, and under the condition that the main structure of the turbocharger is not changed, the pressure measuring channel is only increased on the compressor air seal ring, the intermediate body and the turbine end heat shield, so that the back pressure value of the turbocharger can be measured in any stable state when the turbocharger test stand or a diesel engine runs.
Description
Technical Field
The invention relates to the technical field of turbochargers, in particular to a turbocharger wheel back pressure measuring structure and a turbocharger wheel back pressure measuring method.
Background
With the development of internal combustion engine technology, the efficiency and reliability of the supercharger are higher and higher, and the supercharger efficiency is mainly improved by improving the aerodynamic performance and reducing the mechanical friction loss. Supercharger bearings, and in particular thrust bearings, are the primary source of mechanical friction losses during supercharger operation and are key core components affecting supercharger life. The axial thrust of the supercharger is the design basis of a thrust bearing of the supercharger, and is a key parameter for reasonably determining the load distribution and the power consumption of the thrust bearing. The method has the advantages that the method has important significance in accurately obtaining the axial thrust of the working state of the supercharger, the axial thrust of the working state of the supercharger is generally obtained through pneumatic calculation, and the pressure behind the wheel, particularly the wheel back with air seal teeth, is calculated through estimating the pressure difference of the sealing structure of the supercharger, and has a certain error with the actual existence.
Disclosure of Invention
The invention provides a structure and a method for measuring the back pressure of a turbocharger wheel, which are used for solving the technical problem of inaccurate measurement of the back pressure of the turbocharger wheel.
In order to achieve the above object, the technical scheme of the present invention is as follows:
The utility model provides a turbo charger wheel back pressure measurement structure, includes compressor impeller, compressor air seal circle, midbody, pressure sensor, plug, turbine end heat exchanger and turbine, the midbody is inside to be equipped with first pressure channel, second pressure channel and third pressure channel, the upper end fixed connection of second pressure channel pressure sensor, first pressure channel's one end with second pressure channel intercommunication, its other end is seted up to the left end side of midbody and is equipped with sealed screw thread, third pressure channel's one end with first pressure channel intercommunication, its other end is seted up to the right-hand member face of midbody and is equipped with sealed screw thread, first pressure channel with third pressure channel's sealed screw thread department is through the plug seals, be provided with the pressure channel of connecting compressor impeller back and midbody on the compressor air seal circle, be provided with the pressure channel of connecting turbine back and midbody on the turbine heat exchanger, the compressor air seal circle is fixed between compressor impeller and the midbody, turbine end heat exchanger is fixed between the turbine heat exchanger.
Further, the gas seal ring of the gas compressor is connected with the intermediate body through bolts, and the gas seal ring of the gas compressor is sealed with the intermediate body by adopting a 0-shaped sealing ring.
Furthermore, the turbine-end heat shield is in compression connection with the turbine shell through the intermediate body, and the gap between the turbine-end heat shield and the intermediate body measuring channel is sealed by a C-shaped ring or a graphite gasket.
A turbocharger wheel back pressure measurement method, comprising:
S1: when the back pressure of the impeller of the air compressor is measured, the plug is plugged on the sealing thread of the intermediate body close to the turbine end;
s2: starting the supercharger and adjusting the pressure ratio flow to a set stable working state, and measuring the pressure value in the pressure channel by the pressure sensor;
S3: closing the air compressor;
s4: when the back pressure of the turbine is measured, the plug is blocked on the sealing thread of the intermediate body close to the compressor end;
s5: and starting the booster and adjusting the pressure ratio flow under the set stable working state, and measuring the pressure value in the pressure channel by the pressure sensor.
The beneficial effects are that: the invention provides a simple measuring method of the back pressure of a turbocharger wheel, which can be used for testing in any stable state of a turbocharger test bed or during running along with a diesel engine, and can measure an accurate back pressure value of the turbocharger wheel by only adding a measuring pressure channel on a gas seal ring of a gas compressor, an intermediate body and a heat shield at a turbine end without changing the main structure of the turbocharger, thereby more accurately calculating the axial thrust born by a thrust bearing, finely and accurately designing the thrust bearing and providing a basis for the correct calculation and correction of the back pressure of the turbocharger wheel.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the drawings that are needed in the embodiments or the description of the prior art will be briefly described below, it will be obvious that the drawings in the following description are some embodiments of the present invention, and that other drawings can be obtained according to these drawings without inventive effort to a person skilled in the art.
FIG. 1 is a schematic view of a turbocharger wheel back pressure measurement structure and method according to the present disclosure;
FIG. 2 is an enlarged view of a portion of a seal ring of type 0 in accordance with the present invention;
FIG. 3 is an enlarged view of a portion of a turbocharger wheel back pressure measurement structure and method C-ring or graphite gasket of the present disclosure;
In the figure: 1. the gas turbine comprises a gas compressor impeller, 2, a gas compressor sealing ring, 3, an intermediate body, 4, a pressure sensor, 5, a plug, 6, a turbine end heat shield, 7, a turbine, 8, an O-shaped sealing ring, 9, a C-shaped ring or a graphite gasket, 10, a turbine shell, 301, a first pressure channel, 302, a second pressure channel, 303 and a third pressure channel.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The embodiment provides a back pressure measurement structure of a turbocharger wheel, as shown in fig. 1, the back pressure measurement structure comprises a compressor impeller 1, a compressor air seal ring 2, an intermediate body 3, a pressure sensor 4, a screw plug 5, a turbine end heat shield 6 and a turbine 7, wherein a first pressure channel 301, a second pressure channel 302 and a third pressure channel 303 are arranged in the intermediate body 3, the upper end of the second pressure channel 302 is fixedly connected with the pressure sensor 4, one end of the first pressure channel 301 is communicated with the second pressure channel 302, the other end of the first pressure channel is arranged on the left end side surface of the intermediate body 3 and is provided with a sealing thread, one end of the third pressure channel 303 is communicated with the first pressure channel 301, the other end of the third pressure channel is arranged on the right end surface of the intermediate body 3 and is provided with a sealing thread, the sealing thread of the first pressure channel 301 and the third pressure channel 303 is sealed by the screw plug 5, the pressure channel which is connected with the back of the compressor impeller 1 and the intermediate body 3 is arranged on the compressor air seal ring 2, the turbine heat shield 6 is provided with a sealing thread which is connected with the back of the compressor impeller 1 and the turbine end of the intermediate body 3, and the turbine end of the intermediate body 3 is fixedly connected with the turbine impeller 3 and the intermediate body 3, and the turbine end of the intermediate body 3 is sealed between the turbine impeller 3 and the intermediate body 3. Under the condition that the main structure of the supercharger is not changed, a measuring pressure channel is only increased on the air seal ring 1 of the compressor, the intermediate body 3 and the heat shield 6 at the turbine end, and meanwhile, the air seal ring 1 of the compressor, the intermediate body 3 and the heat shield 6 at the turbine end are detachable, so that the back pressure of the impeller of the compressor and the back pressure of the turbine end can be accurately measured.
In a specific embodiment, as shown in fig. 2, the gas seal ring 2 of the compressor is connected with the intermediate body 3 through a bolt, the impeller 1 of the compressor is connected with the turbine 7 through a thread, the gas seal ring 2 of the compressor is sealed with the intermediate body 3 by adopting a 0-type sealing ring 8, and the gas tightness can be increased by arranging the 0-type sealing ring 8, so that the measured back pressure result of the impeller of the compressor is more accurate.
In a specific embodiment, as shown in fig. 3, the turbine-end heat shield 6 is in compression connection with the turbine shell 10 through the intermediate body 3, the turbine shell 10 is fixedly connected with the intermediate body 3 through bolts, the rotor formed by the compressor impeller 1 and the turbine 7 is connected with the intermediate body 3 through a bearing seat, a measuring channel gap between the turbine-end heat shield 6 and the intermediate body 3 is sealed by adopting a C-shaped ring or a graphite gasket 9, and the measured back pressure value of the turbine end is more accurate by arranging the C-shaped ring or the graphite gasket 9.
A turbocharger wheel back pressure measurement method, comprising:
s1: when the back pressure of the impeller of the air compressor is measured, the turbine shell and the turbine are disassembled through the disassembling bolts, the turbine end isolation cover is taken out, the plug is plugged on the intermediate sealing thread close to the turbine end, and then the turbine end isolation cover is assembled again;
S2: starting the supercharger and adjusting the pressure ratio flow to any stable working state, and measuring the pressure value in the pressure channel by the pressure sensor;
S3: closing the air compressor;
S4: when the back pressure of the turbine is measured, the bolt of the intermediate body is disassembled, the rotating thread pressure reducing compressor impeller is disassembled on the turbine, the plug is plugged on the intermediate body sealing thread at the compressor end, and then the bolt is assembled again;
S5: and starting the booster and adjusting the pressure ratio flow under any stable working state, and measuring the pressure value in the pressure channel by the pressure sensor.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (2)
1. The utility model provides a turbocharger wheel back pressure measurement structure, characterized by, including compressor impeller (1), compressor gas seal circle (2), midbody (3), pressure sensor (4), plug (5), turbine end heat exchanger (6) and turbine (7), midbody (3) inside is equipped with first pressure channel (301), second pressure channel (302) and third pressure channel (303), the upper end fixed connection of second pressure channel (302) pressure sensor (4), the one end of first pressure channel (301) with second pressure channel (302) intercommunication, its other end is seted up to the left end side of midbody (3) and is provided with sealing thread, the one end of third pressure channel (303) with first pressure channel (301) intercommunication, its other end is seted up to the right-hand member face of midbody (3) and is provided with sealing thread, the sealing thread department of first pressure channel (301) and third pressure channel (303) is sealed through plug (5), the back pressure of compressor (2) is provided with back pressure channel (6) and is connected with midbody (3) back pressure channel (7) on the compressor gas seal circle (2), the gas seal ring (2) of the gas compressor is fixed between the impeller (1) of the gas compressor and the intermediate body (3), and the heat shield (6) at the turbine end is fixed between the turbine (7) and the intermediate body (3);
The gas seal ring (2) of the gas compressor is connected with the intermediate body (3) through bolts, and the gas seal ring (2) of the gas compressor and the intermediate body (3) are sealed by adopting an O-shaped sealing ring (8);
The turbine end heat shield (6) is in compression connection with the turbine shell (10) through the intermediate body (3), and the gap between the turbine end heat shield (6) and a measuring channel of the intermediate body (3) is sealed by a C-shaped ring or a graphite gasket (9).
2. A turbocharger wheel back pressure measurement method using a turbocharger wheel back pressure measurement structure according to claim 1, comprising:
S1: when the back pressure of the impeller of the air compressor is measured, the plug is plugged on the sealing thread of the intermediate body close to the turbine end;
s2: starting the supercharger and adjusting the pressure ratio flow to a set stable working state, and measuring the pressure value in the pressure channel by the pressure sensor;
S3: closing the air compressor;
s4: when the back pressure of the turbine is measured, the plug is blocked on the sealing thread of the intermediate body close to the compressor end;
s5: and starting the booster and adjusting the pressure ratio flow under the set stable working state, and measuring the pressure value in the pressure channel by the pressure sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111285390.8A CN113864223B (en) | 2021-11-01 | 2021-11-01 | Structure and method for measuring back pressure of turbocharger wheel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111285390.8A CN113864223B (en) | 2021-11-01 | 2021-11-01 | Structure and method for measuring back pressure of turbocharger wheel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113864223A CN113864223A (en) | 2021-12-31 |
| CN113864223B true CN113864223B (en) | 2024-05-14 |
Family
ID=78986395
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111285390.8A Active CN113864223B (en) | 2021-11-01 | 2021-11-01 | Structure and method for measuring back pressure of turbocharger wheel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113864223B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101726378A (en) * | 2009-11-12 | 2010-06-09 | 北京理工大学 | Device and method for measuring mechanical loss power of turbocharger |
| CN108168851A (en) * | 2017-11-22 | 2018-06-15 | 中国北方发动机研究所(天津) | A kind of turbocharger axial direction load test device and test method |
| CN108952951A (en) * | 2018-07-27 | 2018-12-07 | 中车大连机车研究所有限公司 | A kind of turbocharger pressure gas balance system structure |
| WO2019000258A1 (en) * | 2017-06-26 | 2019-01-03 | 深圳市樊溪电子有限公司 | Gas turbine flowmeter detection device and detection method |
| CN110374695A (en) * | 2019-07-17 | 2019-10-25 | 北京理工大学 | A kind of turbocharger acceleration measuring device and measuring method |
| CN110470434A (en) * | 2019-08-07 | 2019-11-19 | 中国北方发动机研究所(天津) | A kind of air leakage test device and the test method of turbocharger |
| CN112343668A (en) * | 2020-11-03 | 2021-02-09 | 上海齐耀动力技术有限公司 | Thrust balance system of supercritical carbon dioxide TAC unit and control method |
| CN216077687U (en) * | 2021-11-01 | 2022-03-18 | 中车大连机车研究所有限公司 | Turbocharger wheel back pressure measuring structure |
-
2021
- 2021-11-01 CN CN202111285390.8A patent/CN113864223B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101726378A (en) * | 2009-11-12 | 2010-06-09 | 北京理工大学 | Device and method for measuring mechanical loss power of turbocharger |
| WO2019000258A1 (en) * | 2017-06-26 | 2019-01-03 | 深圳市樊溪电子有限公司 | Gas turbine flowmeter detection device and detection method |
| CN108168851A (en) * | 2017-11-22 | 2018-06-15 | 中国北方发动机研究所(天津) | A kind of turbocharger axial direction load test device and test method |
| CN108952951A (en) * | 2018-07-27 | 2018-12-07 | 中车大连机车研究所有限公司 | A kind of turbocharger pressure gas balance system structure |
| CN110374695A (en) * | 2019-07-17 | 2019-10-25 | 北京理工大学 | A kind of turbocharger acceleration measuring device and measuring method |
| CN110470434A (en) * | 2019-08-07 | 2019-11-19 | 中国北方发动机研究所(天津) | A kind of air leakage test device and the test method of turbocharger |
| CN112343668A (en) * | 2020-11-03 | 2021-02-09 | 上海齐耀动力技术有限公司 | Thrust balance system of supercritical carbon dioxide TAC unit and control method |
| CN216077687U (en) * | 2021-11-01 | 2022-03-18 | 中车大连机车研究所有限公司 | Turbocharger wheel back pressure measuring structure |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113864223A (en) | 2021-12-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN216077687U (en) | Turbocharger wheel back pressure measuring structure | |
| CN201627605U (en) | Sealing and heat insulation structure at vortex end of turbocharger | |
| CN113864223B (en) | Structure and method for measuring back pressure of turbocharger wheel | |
| CN212105975U (en) | Turbocharger with improved floating bearing positioning structure | |
| CN101832845B (en) | Self-correcting system and method for sealing test of exhaust gas turbocharger | |
| CN210240759U (en) | AH-level stop valve sealing structure | |
| CN218376590U (en) | Bearing cooling device of air bearing turbocharger | |
| CN110454275B (en) | Independent measuring structure for air leakage of compressor end and turbine end of turbocharger | |
| CN201568568U (en) | Sealing structure at pressure end of turbocharger | |
| CN115030784A (en) | Bearing cooling device of air bearing turbocharger | |
| CN211425784U (en) | Leakage test device for detecting engine exhaust manifold | |
| CN201653658U (en) | Self-calibration type sealing testing system of exhaust turbocharger | |
| CN209129685U (en) | Variable-geometry mixed-flow turbocharger sealing structure | |
| CN220850163U (en) | Low-noise compressor shell with replaceable air inlet | |
| CN109560656A (en) | A kind of connection type in reliable motor cycle water route | |
| CN218479933U (en) | Air compressor shell structure and air compressor | |
| CN109724726A (en) | A kind of turbocharger axial direction force test system and test method | |
| CN219412730U (en) | Turbocharger core with good lubricity | |
| CN218271268U (en) | Testing system of rotary sealing structure | |
| CN116663157B (en) | Method for analyzing invalid air leakage of aero-engine and restraining device | |
| CN220395852U (en) | Integrated EGR outlet duct and EGR system | |
| CN218151163U (en) | Gas turbine exhaust diffuser structure | |
| CN215109055U (en) | Turbocharger middle shell | |
| CN201843810U (en) | Small-size turbocharger air compressor scroll casing and bearing body adopting rigid sealing structure | |
| CN216621618U (en) | Sealing device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |