CN111964930A - Test method for turbine cooler - Google Patents
Test method for turbine cooler Download PDFInfo
- Publication number
- CN111964930A CN111964930A CN202010732226.6A CN202010732226A CN111964930A CN 111964930 A CN111964930 A CN 111964930A CN 202010732226 A CN202010732226 A CN 202010732226A CN 111964930 A CN111964930 A CN 111964930A
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- test
- pipeline
- turbine cooler
- turbine
- cooler
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- 238000010998 test method Methods 0.000 title claims abstract description 10
- 238000012360 testing method Methods 0.000 claims abstract description 47
- 230000035939 shock Effects 0.000 claims abstract description 7
- 238000001816 cooling Methods 0.000 claims abstract description 6
- 238000000034 method Methods 0.000 claims description 8
- 230000008569 process Effects 0.000 claims description 7
- 238000000926 separation method Methods 0.000 claims description 4
- 238000012544 monitoring process Methods 0.000 claims description 3
- 238000004378 air conditioning Methods 0.000 abstract description 3
- 238000005381 potential energy Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing 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
- 230000009467 reduction Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
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Classifications
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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
- G01M99/00—Subject matter not provided for in other groups of this subclass
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention relates to the field of aircraft air conditioning systems, in particular to a test method for a turbine cooler, which comprises a first pipeline and a second pipeline, and comprises the following specific steps: s1: setting parameters of a simulator; s2: connecting pipelines; s3: installing a shock pad; s4: cooling and outputting; s5: recording parameters; s6: remote control; the temperature, the rotating speed, the vibration and the temperature drop of the turbine cooler are set through the control box, the on-machine state of the turbine cooler is accurately simulated, the real-time temperature, the rotating speed, the flow, the pressure and the temperature drop of the turbine cooler are controlled simultaneously, the test precision and the work efficiency of the turbine cooler are improved, the test cost is reduced, and the safety of testers is guaranteed through remote control.
Description
Technical Field
The invention relates to the field of aircraft air conditioning systems, in particular to a test method for a turbine cooler.
Background
The turbine cooler is used for carrying out third-stage cooling on an aircraft air conditioning system, and air potential energy is converted into functions through the turbine guider, so that the turbine shaft is driven to be converted into mechanical energy to achieve temperature reduction. Turbo cooler principle: air enters the guider through the inlet pipe and then enters the turbine disc through the guider, the air expands on the turbine blades, and potential energy of the air is changed into kinetic energy. After passing through the blades, the air is reduced in temperature and pressure and enters the cabin and equipment compartments for cooling. The early test adopts a civil aviation turbine cooler test bed, and because the flow of civil aviation is large, the diameter of a pipeline is large, the numerical deviation of the test is large, and the test is particularly suitable for the acquisition of rotating speed measurement, temperature control and vibration and temperature drop test.
Disclosure of Invention
In order to solve the above problems, the present invention proposes a test method for a turbine cooler.
A test method for a turbine cooler comprises a first pipeline and a second pipeline, and comprises the following specific steps:
s1: setting parameters of a simulator: compressed air of temperature, flow and pressure on a simulator is provided for the test of the turbine cooler through the large-flow valve test bed;
s2: pipeline connection: the test pipeline of the turbine cooler is correctly connected through the first pipeline and the second pipeline, and the pipeline connection of the airplane is fully simulated so as to ensure the accuracy of the test parameters of the turbine cooler;
s3: installing a shock pad: the support for the turbine cooler is fixed on a test frame vehicle, and a shock pad for preventing the test turbine cooler from high rotating speed and large vibration is arranged on the test frame vehicle;
s4: and (3) cooling and outputting: the turbine cooler reduces the high-temperature gas to below 0 ℃ through high-speed rotation, turbine work and compressed gas, and outputs the gas;
s5: recording parameters: monitoring and recording the bearing temperature, the vibration, the rotating speed and the temperature drop of the turbine cooler in the test process of the turbine cooler by a control box;
s6: remote control: through man-machine separation, the personal safety is guaranteed in the remote operation turbine cooler test process.
And the first pipeline and the second pipeline are both provided with a pressure sensor and a temperature sensor, and the numerical values of the pressure sensors and the temperature sensors are connected to a secondary instrument of the control box through signal lines.
And S3, connecting the inlet of the turbine cooler to the large-flow valve test bed through a first pipeline, and connecting the outlet of the turbine cooler to a second pipeline through a flexible connection.
The invention has the beneficial effects that: the temperature, the rotating speed, the vibration and the temperature drop of the turbine cooler are set through the control box, the on-machine state of the turbine cooler is accurately simulated, the real-time temperature, the rotating speed, the flow, the pressure and the temperature drop of the turbine cooler are controlled simultaneously, the test precision and the work efficiency of the turbine cooler are improved, the test cost is reduced, and the safety of testers is guaranteed through remote control.
Drawings
The invention is further illustrated with reference to the following figures and examples.
FIG. 1 is a schematic view of the flow structure of the present invention.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement purposes and the effects of the invention easy to understand, the invention is further explained below.
As shown in fig. 1, a test method for a turbine cooler includes a first pipeline and a second pipeline, and includes the following steps:
s1: setting parameters of a simulator: compressed air of temperature, flow and pressure on a simulator is provided for the test of the turbine cooler through the large-flow valve test bed;
s2: pipeline connection: the test pipeline of the turbine cooler is correctly connected through the first pipeline and the second pipeline, and the pipeline connection of the airplane is fully simulated so as to ensure the accuracy of the test parameters of the turbine cooler;
s3: installing a shock pad: the support for the turbine cooler is fixed on a test frame vehicle, and a shock pad for preventing the test turbine cooler from high rotating speed and large vibration is arranged on the test frame vehicle;
s4: and (3) cooling and outputting: the turbine cooler reduces the high-temperature gas to below 0 ℃ through high-speed rotation, turbine work and compressed gas, and outputs the gas;
s5: recording parameters: monitoring and recording the bearing temperature, the vibration, the rotating speed and the temperature drop of the turbine cooler in the test process of the turbine cooler by a control box;
s6: remote control: through man-machine separation, the personal safety is guaranteed in the remote operation turbine cooler test process.
The temperature, the rotating speed, the vibration and the temperature drop of the turbine cooler are set through the control box, the on-machine state of the turbine cooler is accurately simulated, the real-time temperature, the rotating speed, the flow, the pressure and the temperature drop of the turbine cooler are controlled simultaneously, the test precision and the work efficiency of the turbine cooler are improved, the test cost is reduced, and the safety of testers is guaranteed through remote control.
And the first pipeline and the second pipeline are both provided with a pressure sensor and a temperature sensor, and the numerical values of the pressure sensors and the temperature sensors are connected to a secondary instrument of the control box through signal lines.
And S3, connecting the inlet of the turbine cooler to the large-flow valve test bed through a first pipeline, and connecting the outlet of the turbine cooler to a second pipeline through a flexible connection.
According to the working principle of the turbine cooler on an airplane, the airplane environment simulation and test pipeline manufacturing are completely combined with the existing large-flow test bed to provide high temperature, high pressure and high flow, the flow and pressure of the turbine cooler are remotely controlled in the test process, the temperature drop, the rotating speed and the bearing temperature are monitored through the control box, the problems that the turbine cooler is complex in test and installation and inaccurate in test data are solved, the operation is convenient and fast, the working efficiency is improved by adopting a man-machine separation method, the test cost is reduced, and meanwhile, the personnel safety is greatly improved.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are merely illustrative of the principles of the invention, but that various changes and modifications may be made without departing from the spirit and scope of the invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (3)
1. A test method for a turbine cooler comprises a first pipeline and a second pipeline, and is characterized in that: the method comprises the following specific steps:
s1: setting parameters of a simulator: compressed air of temperature, flow and pressure on a simulator is provided for the test of the turbine cooler through the large-flow valve test bed;
s2: pipeline connection: the test pipeline of the turbine cooler is correctly connected through the first pipeline and the second pipeline, and the pipeline connection of the airplane is fully simulated so as to ensure the accuracy of the test parameters of the turbine cooler;
s3: installing a shock pad: the support for the turbine cooler is fixed on a test frame vehicle, and a shock pad for preventing the test turbine cooler from high rotating speed and large vibration is arranged on the test frame vehicle;
s4: and (3) cooling and outputting: the turbine cooler reduces the high-temperature gas to below 0 ℃ through high-speed rotation, turbine work and compressed gas, and outputs the gas;
s5: recording parameters: monitoring and recording the bearing temperature, the vibration, the rotating speed and the temperature drop of the turbine cooler in the test process of the turbine cooler by a control box;
s6: remote control: through man-machine separation, the personal safety is guaranteed in the remote operation turbine cooler test process.
2. A test method for a turbine cooler according to claim 1, characterized in that: and the first pipeline and the second pipeline are both provided with a pressure sensor and a temperature sensor, and the numerical values of the pressure sensors and the temperature sensors are connected to a secondary instrument of the control box through signal lines.
3. A test method for a turbine cooler according to claim 1, characterized in that: and S3, connecting the inlet of the turbine cooler to the large-flow valve test bed through a first pipeline, and connecting the outlet of the turbine cooler to a second pipeline through a flexible connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010732226.6A CN111964930A (en) | 2020-07-27 | 2020-07-27 | Test method for turbine cooler |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010732226.6A CN111964930A (en) | 2020-07-27 | 2020-07-27 | Test method for turbine cooler |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111964930A true CN111964930A (en) | 2020-11-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010732226.6A Pending CN111964930A (en) | 2020-07-27 | 2020-07-27 | Test method for turbine cooler |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111964930A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105092250A (en) * | 2014-05-16 | 2015-11-25 | 北京光徽德润航空技术有限公司 | ACM testing stand |
| EP3266709A1 (en) * | 2016-07-08 | 2018-01-10 | Hamilton Sundstrand Corporation | Bearing monitoring system for an air cycle machine and method of monitoring |
| CN109187001A (en) * | 2018-09-25 | 2019-01-11 | 芜湖天航装备技术有限公司 | A kind of motorized adjustment class valve big flow performance test apparatus and its test method |
| CN208520592U (en) * | 2018-06-25 | 2019-02-19 | 襄阳航顺航空科技有限公司 | A kind of cooling turbine unit testing stand with elevating mechanism |
| CN109781446A (en) * | 2019-01-11 | 2019-05-21 | 贵州永红航空机械有限责任公司 | A kind of aircraft refrigeration packet boost type air bearing turbine cooler performance test apparatus |
| CN209542085U (en) * | 2019-04-08 | 2019-10-25 | 中国航空综合技术研究所 | A kind of cooling turbine unit equivalent lifetime testing equipment |
| CN209542727U (en) * | 2018-12-25 | 2019-10-25 | 北京航天飞腾装备技术有限责任公司 | A kind of electronic equipment remote environment pilot system |
-
2020
- 2020-07-27 CN CN202010732226.6A patent/CN111964930A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105092250A (en) * | 2014-05-16 | 2015-11-25 | 北京光徽德润航空技术有限公司 | ACM testing stand |
| EP3266709A1 (en) * | 2016-07-08 | 2018-01-10 | Hamilton Sundstrand Corporation | Bearing monitoring system for an air cycle machine and method of monitoring |
| CN208520592U (en) * | 2018-06-25 | 2019-02-19 | 襄阳航顺航空科技有限公司 | A kind of cooling turbine unit testing stand with elevating mechanism |
| CN109187001A (en) * | 2018-09-25 | 2019-01-11 | 芜湖天航装备技术有限公司 | A kind of motorized adjustment class valve big flow performance test apparatus and its test method |
| CN209542727U (en) * | 2018-12-25 | 2019-10-25 | 北京航天飞腾装备技术有限责任公司 | A kind of electronic equipment remote environment pilot system |
| CN109781446A (en) * | 2019-01-11 | 2019-05-21 | 贵州永红航空机械有限责任公司 | A kind of aircraft refrigeration packet boost type air bearing turbine cooler performance test apparatus |
| CN209542085U (en) * | 2019-04-08 | 2019-10-25 | 中国航空综合技术研究所 | A kind of cooling turbine unit equivalent lifetime testing equipment |
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Application publication date: 20201120 |
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| RJ01 | Rejection of invention patent application after publication |