CN214040636U - High-power compressor test bed for recovering power by using auxiliary air turbine - Google Patents
High-power compressor test bed for recovering power by using auxiliary air turbine Download PDFInfo
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- CN214040636U CN214040636U CN202022412792.7U CN202022412792U CN214040636U CN 214040636 U CN214040636 U CN 214040636U CN 202022412792 U CN202022412792 U CN 202022412792U CN 214040636 U CN214040636 U CN 214040636U
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Abstract
An object of the utility model is to provide a retrieve high-power compressor test bench of power with auxiliary air turbine, including air intake system, experimental compressor, the air turbine, first gas turbine device, the second gas turbine device, air intake system connects experimental compressor, the exhaust pipe of experimental compressor includes two the tunnel, connect the air turbine all the way, another way is direct to be discharged, first gas turbine device connects the gear box through first 3S clutch, the second gas turbine device passes through second 3S clutch and connects the gear box, the air turbine is connected to the gear box, first gas turbine device is realized to the gear box, the second gas turbine device is alone worked or parallel work. The utility model provides a marine and industry gas turbine compressor part test power demand problem, adopt the recoverable partial compression work of this test bench, satisfy the comprehensive test demand of the large-scale compressor of full-size, full parameter of high-power source driven.
Description
Technical Field
The utility model relates to a test bench, specifically speaking are gas turbine test bench.
Background
The power source power required by the performance test of the full-size full-parameter air compressor of the high-power ship and the industrial gas turbine is large, and the problems of internal flow field measurement, characteristic measurement, interstage pulsation parameter measurement, pressure distribution, temperature distribution, stable working range, reliability and the like of the high-power air compressor are difficult to solve. At present, a whole air compressor test bed which adopts a gas turbine as a power source to directly drive an air compressor for testing is insufficient in power, high-temperature and high-pressure gas generated by the air compressor is directly exhausted to the atmosphere, and energy waste to a certain extent is caused because the high-temperature and high-pressure gas is not effectively recycled.
Disclosure of Invention
An object of the utility model is to provide a can solve the marine and industrial gas turbine compressor part test power demand problem with the high-power compressor test bench of auxiliary air turbine regaining power.
The purpose of the utility model is realized like this:
the utility model relates to a retrieve high-power compressor test bench of power with auxiliary air turbine, characterized by: the air inlet system is connected with the test air compressor, an exhaust pipeline of the test air compressor comprises two paths, one path is connected with the air turbine, the other path is directly exhausted, the first gas turbine device is connected with the gear box through the first 3S clutch, the second gas turbine device is connected with the gear box through the second 3S clutch, the gear box is connected with the air turbine, and the gear box realizes independent work or parallel work of the first gas turbine device and the second gas turbine device.
The utility model discloses can also include:
1. the rotatable guide vane actuating mechanism is controlled by the electric cylinder and the servo driver, so that the single-row adjustment of the rotatable guide vanes of the test gas compressor is realized.
2. A butterfly valve is arranged on an exhaust pipeline of the test air compressor to control the flow of gas exhausted by the test air compressor and entering the air turbine, so that all or part of the exhausted gas enters the air turbine.
The utility model has the advantages that: the utility model provides a marine and industry gas turbine compressor part test power demand problem, adopt the recoverable partial compression work of this test bench, satisfy the comprehensive test demand of the large-scale compressor of full-size, full parameter of high-power source driven.
Drawings
Fig. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic diagram of twisted pair dimensions;
FIG. 3 is a schematic view of a rotatable vane actuator.
Detailed Description
The invention will be described in more detail below by way of example with reference to the accompanying drawings:
with reference to fig. 1-3, the present invention comprises an air intake system 1, an exhaust passage assembly 2, an air turbine 3, a transmission device 4, a gas turbine device 5, a lubricating oil system 6, an exhaust system 7, a stall surge identification system, a surge relief system, an interstage bleed system, an interstage pulsation test system, an electrical system, a data acquisition system, a control system, etc. The structure diagram is shown in figure 1. The power source is composed of two gas turbine devices 5 as the main power source and a gear box, an air turbine 3 is added behind the test air compressor, about 20-40% of the power consumption of the air compressor is recovered, the test bed obtains power again, and the output power of the whole test bed is greatly improved.
The air inlet system 1 ensures that the speed of air flowing through the flow stabilizing box is not more than 20m/s, the turbulence degree of the inlet speed of the air compressor is not more than 2 percent, and the total pressure unevenness is not more than 3 percent. The flow tube design is based on a twisted pair profile design, as shown in FIG. 2, and a modeling formula R2＝a2cos 2 α, R is the twisted pair profile radius, 0.6D<a<0.8D, D is the diameter of the inner wall, and alpha is 0-45 degrees. The flow tube should contain two different sets of specifications depending on the flow requirements.
The exhaust passage component 2 needs to resist high temperature and high pressure, the total pressure unevenness is not more than 9%, and the position of the exhaust throttle valve is selected to ensure that the exhaust cavity is as small as possible. After passing through the exhaust passage component 2, the gas is divided into two paths, two paths of electric butterfly valves are adjusted, the flow of the gas exhausted by the gas compressor and entering the turbine is controlled, and all or part of the exhausted gas enters the air turbine 3 to be expanded.
The rotatable guide vane actuating mechanism is used for driving an inlet guide vane and a rear stage rotatable guide vane of a test compressor, is realized by an electric cylinder and a servo driver, and can realize single-row adjustment of the rotatable guide vanes of the compressor, as shown in figure 3.
The gas turbine device 5 has the advantages of large power density, mature operation and maintenance technology and the like, the power requirement is not lower than 33MW, and the efficiency is not lower than 38.5%.
The air turbine 3 is used as effective power compensation equipment of a power source, energy recovered by work of the turbine can fully utilize high-temperature and high-pressure exhaust of the test air compressor, and 20% -40% of compression consumed power of the test air compressor can be recovered, so that an energy-saving effect is achieved. The gas expanded by the turbine is led out from the exhaust volute and enters the exhaust pipeline.
The power output of the two combustion engines 5 needs to be transmitted by the gear box, so that the whole compressor test bed can meet the test requirements of different powers and rotating speeds conveniently, the two combustion engines can run independently and parallelly, and a 3S clutch is respectively designed and arranged between each combustion engine and the gear box.
The stall surge online identification system can monitor the surge state of the gas compressor in real time, generate a surge elimination control voltage and cooperate with a surge elimination system to carry out rapid surge elimination treatment on the gas compressor.
The interstage pulsation test system consists of a high-frequency pulsation pressure sensor, a pulsation probe and a dynamic data acquisition system, the frequency response of the sensor is not lower than 10kHz, and the stalling and surge boundaries of the multistage gas compressor can be accurately captured and the leading stalling position of the multistage gas compressor can be judged by utilizing gas compressor instability signal analysis software and a signal identification and analysis technology.
The data acquisition system, the control system and other systems share the functions of testing, acquiring and analyzing the performance parameters of the test bed. The oil system 6 and the electrical system are auxiliary systems provided to ensure safe operation of the test stand.
Claims (3)
1. A high-power compressor test bed for recovering power by using an auxiliary air turbine is characterized in that: the air inlet system is connected with the test air compressor, an exhaust pipeline of the test air compressor comprises two paths, one path is connected with the air turbine, the other path is directly exhausted, the first gas turbine device is connected with the gear box through the first 3S clutch, the second gas turbine device is connected with the gear box through the second 3S clutch, the gear box is connected with the air turbine, and the gear box realizes independent work or parallel work of the first gas turbine device and the second gas turbine device.
2. A high power compressor test stand for recapturing power from an auxiliary air turbine as claimed in claim 1, wherein: the rotatable guide vane actuating mechanism is controlled by the electric cylinder and the servo driver, so that the single-row adjustment of the rotatable guide vanes of the test gas compressor is realized.
3. A high power compressor test stand for recapturing power from an auxiliary air turbine as claimed in claim 1, wherein: a butterfly valve is arranged on an exhaust pipeline of the test air compressor to control the flow of gas exhausted by the test air compressor and entering the air turbine, so that all or part of the exhausted gas enters the air turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022412792.7U CN214040636U (en) | 2020-10-27 | 2020-10-27 | High-power compressor test bed for recovering power by using auxiliary air turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202022412792.7U CN214040636U (en) | 2020-10-27 | 2020-10-27 | High-power compressor test bed for recovering power by using auxiliary air turbine |
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| CN214040636U true CN214040636U (en) | 2021-08-24 |
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| CN202022412792.7U Active CN214040636U (en) | 2020-10-27 | 2020-10-27 | High-power compressor test bed for recovering power by using auxiliary air turbine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114252216A (en) * | 2021-12-13 | 2022-03-29 | 中国船舶重工集团公司第七0三研究所 | Method for detecting leakage of lubricating oil of gas turbine |
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2020
- 2020-10-27 CN CN202022412792.7U patent/CN214040636U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114252216A (en) * | 2021-12-13 | 2022-03-29 | 中国船舶重工集团公司第七0三研究所 | Method for detecting leakage of lubricating oil of gas turbine |
| CN114252216B (en) * | 2021-12-13 | 2024-02-20 | 中国船舶重工集团公司第七0三研究所 | Detection method for lubricating oil leakage of gas turbine |
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