CN114323652A - Exhaust and gas collection device of axial flow compressor tester - Google Patents
Exhaust and gas collection device of axial flow compressor tester Download PDFInfo
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- CN114323652A CN114323652A CN202011041536.XA CN202011041536A CN114323652A CN 114323652 A CN114323652 A CN 114323652A CN 202011041536 A CN202011041536 A CN 202011041536A CN 114323652 A CN114323652 A CN 114323652A
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Abstract
The invention aims to provide an exhaust and gas collection device of an axial flow compressor tester, which reduces the cavity effect. In order to achieve the purpose, the exhaust gas collection device of the axial-flow compressor tester comprises an annular gas collection chamber, wherein the annular gas collection chamber is provided with a closed end and an open end in the axial direction, and is provided with a main exhaust interface and a bypass exhaust interface in the circumferential direction, and the open end is provided with a gas collection interface connected with a test piece; the exhaust main pipeline is connected with the main exhaust interface and is provided with a main pipeline pressure regulating device; the exhaust bypass is connected with the bypass exhaust interface and is provided with a bypass pressure regulating device; the sectional area of the flow passage of the exhaust main pipeline is larger than that of the exhaust bypass.
Description
Technical Field
The invention relates to an exhaust and gas collection device of an axial-flow compressor tester.
Background
With the deep development of the aviation industry, higher requirements are put forward on the working performance of an aero-engine, and with the continuous improvement of the use requirements, the compressor technology with high load, high efficiency, low noise, high stability and high reliability is developed. However, the flow field in the compressor is extremely complex, unsteady flow is obvious, stall and flutter are accompanied, the technical indexes of the compressor must be verified through a compressor test, and therefore a series of high-precision and high-performance test facilities are built for carrying out design verification and improvement and modification of the compressor.
At present, most of the exhaust gas collecting devices of the gas compressor tester adopt a volute structure, and have large volume and large space size. A similar device is disclosed in utility model patent publication CN 205280366U.
The following problems exist in the test process of the exhaust gas collection device of the current compressor tester: 1) the cavity effect easily causes high-amplitude and low-frequency pulsation of the outlet pressure of the test piece, the airflow in the gas collection chamber influences the uniformity of the exhaust flow field of the test piece, and particularly in high-rotation-speed surge boundary recording, the test result is distorted; 2) the volute body is complex in shape, the air flow exhaust loss is large, and the low-speed and low-pressure ratio test requirements of the air compressor cannot be met; 3) the size is large, the weight is large, and the equipment is not easy to adjust in the installation process, so that the installation and debugging period is long; 4) most of the volute inner annular surface and the compressor test piece are in a spigot lap joint mode, air leakage is easy, the temperature of a gas collection chamber is increased due to high-temperature exhaust of the compressor, and an effective cooling mode is not available.
Disclosure of Invention
The invention aims to provide an exhaust and gas collection device of an axial flow compressor tester, which reduces the cavity effect.
To achieve the object, in one embodiment, an axial flow compressor tester exhaust gas collection device comprises an annular gas collection chamber having a closed end and an open end in an axial direction and a main exhaust port and a bypass exhaust port in a circumferential direction, wherein the open end is provided with a gas collection port connected with a test piece; the exhaust main pipeline is connected with the main exhaust interface and is provided with a main pipeline pressure regulating device; the exhaust bypass is connected with the bypass exhaust interface and is provided with a bypass pressure regulating device; the sectional area of the flow passage of the exhaust main pipeline is larger than that of the exhaust bypass.
In one embodiment, the exhaust main pipeline is provided with a merging interface, the tail end of the exhaust bypass is connected with the merging interface, and the merging interface is located on the downstream side of the main pipeline pressure regulating device.
In one embodiment, the main exhaust interface is tapered.
In one embodiment, the main exhaust gas line comprises a divergent section on the upstream side of the inlet connection.
In one embodiment, the annular gas collection chamber is arranged horizontally in the axial direction, and the main exhaust pipeline extends obliquely upwards from the annular gas collection chamber and then vertically upwards.
In one embodiment, the exhaust bypass extends obliquely upwards from one side of the annular air collection chamber opposite to the main exhaust pipeline and then merges into the main exhaust pipeline.
In one embodiment, the axial flow compressor tester exhaust gas collection device further comprises a power transmission device for connecting the tester and the test piece; the annular air collection chamber comprises an inner annular wall and an outer annular wall, and the power transmission device axially penetrates through the inner portion of the inner annular wall of the annular air collection chamber.
In one embodiment, the inner portion of the inner annular wall is further provided with a cooling device, and an exhaust port of the cooling device is aligned with the power transmission device.
In one embodiment, the outer annular wall has an end plate at the closed end, the end plate being flanged to the end of the inner annular wall and having a central aperture through which the power transmission means passes.
In one embodiment, the gas collection port includes a connecting flange disposed at the open end of the inner and outer annular walls.
The inner ring and the outer ring are combined to form a gas collecting chamber cavity, so that the structure of an exhaust gas collecting chamber of the axial flow compressor is optimized, the cavity effect is reduced, the influence of the gas flow of the gas collecting chamber on the outlet flow field of the compressor is reduced, and the test accuracy is improved; compared with the traditional volute, the novel volute has the advantages that the novel structure is simpler, the processing technology can be simplified, the processing cost and the processing period are saved, the size is more simplified, the requirement on space is low, the installation and debugging are convenient and fast, and the test preparation time is shortened; the adjustment precision and efficiency of the test state are improved, so that the test time is shortened, the high-rotation-speed and unstable-working-condition running time of a gas compressor test piece is reduced, the test running risk is reduced, the test efficiency is improved, and the test cost is saved; the high-pressure cooling gas effectively controls the temperature of the gas collecting chamber in the test process, and thermal deformation of the power transmission device is avoided.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a front view of an axial compressor tester exhaust gas collection device.
Fig. 2 is a sectional view taken along line I-I in fig. 1.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
As shown in fig. 1 and 2, an exhaust gas collection device of an axial flow compressor tester comprises an inner annular wall 1 of a gas collection chamber, an outer annular wall 2 of the gas collection chamber, an exhaust main pipeline 3 and a pressure regulating device 6 thereof, an exhaust bypass 4 and a pressure regulating device 7 thereof, and a cooling device 5. An inner annular wall 1 of the gas collection chamber and an outer annular wall 2 of the gas collection chamber form an annular gas collection chamber.
During the test of the compressor, exhaust gas axially flows into the gas collecting chamber cavity from the left side in the figure 2 and is radially discharged through the main exhaust pipeline 3 and the exhaust bypass 4, and the pressure regulating mechanisms 6 and 7 are respectively arranged on the main exhaust pipeline 3 and the exhaust bypass 4, so that the requirement of regulating the pressure ratio of the test of the compressor can be met. The flow passage sectional area of the exhaust main pipeline 3 is larger than that of the exhaust bypass 4, and the adjustment precision required by the test is realized through the exhaust bypass 4.
As shown in FIG. 2, the annular plenum has a closed end at the right end and an open end at the left end in the axial direction. In fig. 2, the main exhaust port 31 is shown in the circumferential direction, but the bypass exhaust port 41 is not shown. The main exhaust interface 31 and the bypass exhaust interface 41 are shown in FIG. 1.
The annular gas collection chamber is provided with a gas collection interface connected with a test piece at the open end of the left end, and comprises connecting flanges 11 and 21 positioned on the inner annular wall 1 of the gas collection chamber and the outer annular wall 2 of the gas collection chamber in figures 1 and 2. The inner annular surface of the volute and a gas compressor test piece are mostly in a spigot lap joint mode, gas leakage is easy, and the problems can be solved by adopting the connecting flange.
As shown in fig. 1 and fig. 2, the inner annular wall 1 of the collection chamber and the outer annular wall 2 of the collection chamber are both annular cylinders, the outer annular wall 2 of the collection chamber is provided with an end plate 22 at the closed end of the annular collection chamber, bolt holes are machined in the end plate, the right end of the inner annular wall 1 of the collection chamber is fixed on the end plate 22 of the outer annular wall 2 of the collection chamber through bolts, and forms an annular collection chamber together with the outer annular wall 2 of the collection chamber, and the front ends of the inner annular wall 1 of the collection chamber and the outer annular wall 2 of the collection chamber are flange interfaces for fixing test pieces. The cylinder body of the outer annular wall 2 of the gas collecting chamber is provided with an exhaust port, and a main exhaust interface 31 and a bypass exhaust interface 41 for connecting an exhaust main pipeline 3 and an exhaust bypass 4 are arranged.
The straight molded lines of the inner annular wall 1 of the gas collection chamber and the outer annular wall 2 of the gas collection chamber ensure the axial exhaust requirement of the gas compressor, can reduce the exhaust flow resistance and loss, reduce the cavity effect, and ensure the uniformity of an outlet flow field.
As shown in figure 1, the main exhaust pipeline 3 and the bypass exhaust pipeline 4 are different in size and are respectively provided with the pressure regulating devices 6 and 7, so that the requirements of rough adjustment and fine adjustment of the pressure ratio of the air compressor can be met, and the test precision is improved. The pressure regulating devices 6 and 7 may be butterfly valves or the like.
The molded lines of the main exhaust pipeline 3 and the exhaust bypass 4 can be designed by adopting the principle of minimum exhaust loss, for example, a simulation model of an exhaust gas collection device of an axial flow compressor tester is established in CFD software, optimization is carried out by the minimum exhaust loss, and the molded line of the main exhaust pipeline 3 can be determined. In fig. 1, one type of the exhaust main pipe 3 is shown, but the type is not limited thereto, and the type may be varied according to the test requirements and the type of the test piece. For example, the main exhaust pipe 3 and the bypass exhaust pipe 4 both extend obliquely upward, rather than vertically to the annular plenum, and the main exhaust pipe 3 extends obliquely and then vertically, which is beneficial to reducing exhaust loss. In addition, the design of the detail can be carried out to increase the flow pressure, for example, the main exhaust interface 31 is a conical mouth or a tapered shape, so that the accelerated exhaust of the air flow can be realized, and the exhaust is finally converted into radial exhaust. If the exhaust main pipeline 3 is provided with a flexible connecting structure, micro deformation can be compensated, and exhaust loss can be reduced.
The main exhaust gas line 3 and the bypass exhaust gas line 4 are connected to an exhaust gas tower above the annular plenum, which is not shown in the figures. The main exhaust line 3 and the bypass exhaust line 4 can be connected to the exhaust tower, respectively, or, as shown in fig. 1, the bypass exhaust line 4 leads into the main exhaust line 3 and then into the exhaust tower together.
The exhaust main pipe 3 is provided with a merging port 32, the end of the exhaust bypass 4 is connected to the merging port 32, and the merging port 32 is provided on the downstream side of the pressure adjusting device 31. The main exhaust line 3 further comprises a divergent section 33 arranged upstream of the inlet connection 32, the divergent section 33 slowing down the fluid in order to introduce the exhaust gas fed by its bypass 4.
The main exhaust pipe 3 further comprises a reducing section 34 arranged at the tail end, and the reducing section 34 is beneficial to exhaust to be discharged quickly so as to inject gas in the exhaust tower, so that airflow can be smoothly discharged out of the exhaust tower.
As shown in fig. 2, the power transmission device 8 between the tester and the test piece passes through the inner annular wall 1 of the plenum, specifically, the central hole of the end plate 22 of the outer annular wall 2 of the plenum, and one embodiment of the power transmission device 8 is a diaphragm type coupling. In the test process of the gas compressor, the high-temperature exhaust can lead the temperature of the wall of the gas collection chamber to rise, in order to prevent the high temperature from corroding the power transmission device 8, the cooling device 5 is arranged in the inner annular wall 1 of the gas collection chamber, the structure is a straight pipe type, the radial exhaust pipe is machined and installed on the pipe body, the exhaust port is aligned with the power transmission device 8, the cooling device 5 is additionally arranged on the end plate 22 of the outer annular wall 2 of the gas collection chamber through a hoop, and during the test, the cooling device 5 continuously sprays high-pressure cooling gas, so that the temperature of a shaft system can be reduced, and the thermal deformation is avoided.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (10)
1. Axial compressor tester exhaust gas collection device, its characterized in that includes:
the annular gas collection chamber is provided with a closed end and an open end in the axial direction, and a main exhaust interface and a bypass exhaust interface in the circumferential direction, and the open end is provided with a gas collection interface connected with the test piece;
the exhaust main pipeline is connected with the main exhaust interface and is provided with a main pipeline pressure regulating device; and
the exhaust bypass is connected with the bypass exhaust interface and is provided with a bypass pressure regulating device;
the sectional area of the flow passage of the exhaust main pipeline is larger than that of the exhaust bypass.
2. The axial-flow compressor tester exhaust gas collection device according to claim 1, wherein the exhaust main pipeline is provided with a merging interface, the tail end of the exhaust bypass is connected with the merging interface, and the merging interface is positioned at the downstream side of the main pipeline pressure regulating device.
3. The axial compressor tester exhaust gas collection apparatus of claim 2, wherein the main exhaust interface is tapered.
4. The axial compressor tester exhaust gas collection apparatus of claim 3, wherein the main exhaust gas conduit includes a diverging section upstream of the inlet interface.
5. The axial flow compressor tester exhaust gas collection device according to claim 1 or 4, wherein the annular gas collection chamber is arranged horizontally in the axial direction, and the main exhaust gas pipeline extends obliquely upwards from the annular gas collection chamber and then vertically upwards.
6. The axial compressor tester exhaust gas collection apparatus of claim 5, wherein the exhaust bypass extends obliquely upward from a side of the annular plenum opposite the main exhaust gas conduit and then merges into the main exhaust gas conduit.
7. The axial flow compressor tester exhaust gas collection apparatus of claim 1, further comprising a power transmission for connection between the tester and the test piece;
the annular air collection chamber comprises an inner annular wall and an outer annular wall, and the power transmission device axially penetrates through the inner portion of the inner annular wall of the annular air collection chamber.
8. The axial compressor tester exhaust gas collection device of claim 7, wherein the interior of the inner annular wall is further provided with a cooling device, and the exhaust port of the cooling device is aligned with the power transmission device.
9. The axial compressor tester exhaust gas collection assembly of claim 7, wherein said outer annular wall has an end plate at said closed end, said end plate being flanged to an end of said inner annular wall and having a central aperture for said power transmission means to pass through.
10. The axial compressor tester exhaust gas collection apparatus of claim 7, wherein said collection interface comprises a connecting flange disposed at said open end of said inner and outer annular walls.
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| CN202011041536.XA CN114323652B (en) | 2020-09-28 | 2020-09-28 | Exhaust and gas collection device of axial-flow compressor tester |
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| CN202011041536.XA CN114323652B (en) | 2020-09-28 | 2020-09-28 | Exhaust and gas collection device of axial-flow compressor tester |
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Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003083584A (en) * | 2001-09-11 | 2003-03-19 | Daikin Ind Ltd | Air supply/exhaust ventilator |
| JP2005351095A (en) * | 2004-06-08 | 2005-12-22 | Toyota Motor Corp | Internal combustion engine equipped with exhaust recirculating device |
| US20080175703A1 (en) * | 2007-01-09 | 2008-07-24 | Sonic Blue Aerospace | Electric turbine bypass fan and compressor for hybrid propulsion |
| CN204286730U (en) * | 2014-11-21 | 2015-04-22 | 中国航空工业集团公司沈阳发动机设计研究所 | The system of breathing heavily is moved back in a kind of bypass for Compressor test part |
| CN104675522A (en) * | 2015-01-30 | 2015-06-03 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Turbine gas circuit of gas turbine |
| CN205280366U (en) * | 2015-12-15 | 2016-06-01 | 中国燃气涡轮研究院 | A exhaust apparatus for axial flow compressor tester |
| CN106053082A (en) * | 2016-05-31 | 2016-10-26 | 中国航空动力机械研究所 | Compressor testpieces and surge method thereof |
| CN108362501A (en) * | 2017-12-27 | 2018-08-03 | 中国航发四川燃气涡轮研究院 | A kind of rack installation method for aviation axial flow compressor performance test |
| CN109339875A (en) * | 2018-09-21 | 2019-02-15 | 南京航空航天大学 | A kind of mixing diffuser of band bypass bleed |
| KR101962368B1 (en) * | 2017-11-29 | 2019-07-17 | 한국해양과학기술원 | Salt contamination test apparatus of concrete structure under pressure and method thereof |
| US20190277139A1 (en) * | 2018-03-09 | 2019-09-12 | Mitsubishi Heavy Industries, Ltd. | Steam turbine apparatus |
| CN110374909A (en) * | 2019-07-19 | 2019-10-25 | 中国航发沈阳发动机研究所 | It is a kind of for become circulation Compressor test outer culvert be vented air collecting chamber device |
| CN110397615A (en) * | 2019-07-31 | 2019-11-01 | 中国航发沈阳发动机研究所 | A kind of multistage compressor experimental rig |
| CN116625700A (en) * | 2023-05-26 | 2023-08-22 | 中国航发沈阳发动机研究所 | Variable-circulation core machine external culvert exhaust collection and measurement system |
-
2020
- 2020-09-28 CN CN202011041536.XA patent/CN114323652B/en active Active
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2003083584A (en) * | 2001-09-11 | 2003-03-19 | Daikin Ind Ltd | Air supply/exhaust ventilator |
| JP2005351095A (en) * | 2004-06-08 | 2005-12-22 | Toyota Motor Corp | Internal combustion engine equipped with exhaust recirculating device |
| US20080175703A1 (en) * | 2007-01-09 | 2008-07-24 | Sonic Blue Aerospace | Electric turbine bypass fan and compressor for hybrid propulsion |
| CN204286730U (en) * | 2014-11-21 | 2015-04-22 | 中国航空工业集团公司沈阳发动机设计研究所 | The system of breathing heavily is moved back in a kind of bypass for Compressor test part |
| CN104675522A (en) * | 2015-01-30 | 2015-06-03 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Turbine gas circuit of gas turbine |
| CN205280366U (en) * | 2015-12-15 | 2016-06-01 | 中国燃气涡轮研究院 | A exhaust apparatus for axial flow compressor tester |
| CN106053082A (en) * | 2016-05-31 | 2016-10-26 | 中国航空动力机械研究所 | Compressor testpieces and surge method thereof |
| KR101962368B1 (en) * | 2017-11-29 | 2019-07-17 | 한국해양과학기술원 | Salt contamination test apparatus of concrete structure under pressure and method thereof |
| CN108362501A (en) * | 2017-12-27 | 2018-08-03 | 中国航发四川燃气涡轮研究院 | A kind of rack installation method for aviation axial flow compressor performance test |
| US20190277139A1 (en) * | 2018-03-09 | 2019-09-12 | Mitsubishi Heavy Industries, Ltd. | Steam turbine apparatus |
| CN109339875A (en) * | 2018-09-21 | 2019-02-15 | 南京航空航天大学 | A kind of mixing diffuser of band bypass bleed |
| CN110374909A (en) * | 2019-07-19 | 2019-10-25 | 中国航发沈阳发动机研究所 | It is a kind of for become circulation Compressor test outer culvert be vented air collecting chamber device |
| CN110397615A (en) * | 2019-07-31 | 2019-11-01 | 中国航发沈阳发动机研究所 | A kind of multistage compressor experimental rig |
| CN116625700A (en) * | 2023-05-26 | 2023-08-22 | 中国航发沈阳发动机研究所 | Variable-circulation core machine external culvert exhaust collection and measurement system |
Non-Patent Citations (2)
| Title |
|---|
| XIAOZHI KONG: "Experimental testing for the influences of rotation and tip clearance on the labyrinth seal in a compressor stator well", 《AEROSPACE SCIENCE AND TECHNOLOGY》, vol. 71, pages 556 - 567, XP085288499, DOI: 10.1016/j.ast.2017.10.003 * |
| 马昌友 等: "核心机驱动风扇级与高压压气机匹配试验中外涵排气系统的设计与试验验证", 《燃气涡轮试验与研究》, vol. 33, no. 1, pages 6 - 11 * |
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