CN113899555B - Balance control system for slow-vehicle running environment field of laboratory aircraft engine - Google Patents
Balance control system for slow-vehicle running environment field of laboratory aircraft engine Download PDFInfo
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- CN113899555B CN113899555B CN202111507582.9A CN202111507582A CN113899555B CN 113899555 B CN113899555 B CN 113899555B CN 202111507582 A CN202111507582 A CN 202111507582A CN 113899555 B CN113899555 B CN 113899555B
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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
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
- G05D27/00—Simultaneous control of variables covered by two or more of main groups G05D1/00 - G05D25/00
- G05D27/02—Simultaneous control of variables covered by two or more of main groups G05D1/00 - G05D25/00 characterised by the use of electric means
Abstract
The invention discloses a balance control system for a slow-vehicle running environment field of an aircraft engine in a laboratory, which comprises an environment acquisition mechanism arranged in the laboratory, an air supply temperature control mechanism arranged on one side outside the laboratory and communicated with the laboratory, and an exhaust mechanism arranged on the other side outside the laboratory and communicated with the laboratory. The invention has novel design, and ensures that the temperature and the pressure of an environmental field are kept unchanged before and after the airplane engine slow running test when the airplane performs the engine slow running test in a closed space laboratory through the cooperative work of the environment acquisition mechanism, the air supply temperature control mechanism and the exhaust mechanism which are arranged inside and outside the laboratory, so as to ensure the effectiveness of the airplane engine slow running test and the building safety of the laboratory.
Description
Technical Field
The invention belongs to the technical field of balance control of an aircraft engine slow-speed operation environment field, and particularly relates to a balance control system of a laboratory aircraft engine slow-speed operation environment field.
Background
With the rapid development of the modern aviation industry, an aircraft needs to operate in various climatic environments on the earth, and faces extreme climatic environments such as high temperature, high cold, damp heat, icing and the like, and the extreme climatic environments are one of main factors causing civil aircraft failure and function loss, so that the performance of the aircraft is degraded and the function of the aircraft is limited. In order to ensure the safe operation of the airplane, the airplane needs to carry out a climate environment adaptability verification test in the development process, and the test is generally carried out in an outfield natural climate environment or artificial climate environment laboratory. Based on the advantages of accurate and controllable environmental conditions, reachable extreme values, reproducible environment and the like of the laboratory, system verification and detection subjects in the outfield ground and flight tests are generally planned to the laboratory for carrying out, and the airplane is subjected to edge touch and bottom detection on the functions and the performance of the airplane in the laboratory before the outfield extreme natural climate test so as to ensure the safety of the outfield climate test of the airplane.
The airplane climate environment adaptability verification test items are multiple, and most verification items are carried out in the engine slow running state, such as airplane environmental control system ground heating and cooling tests, hydraulic system tests, flight control system tests and the like. In addition, the aircraft engine itself also needs to perform a plurality of engine slow vehicle operation climate environment adaptability verification tests, such as a combined test of an air source system and an engine starting system, an engine reverse thrust test, and the like. The climate environment adaptability verification tests related to the slow vehicle running of the engine require that the temperature of an environment field is kept constant when the engine runs slowly. If the test is carried out in a climate laboratory in a closed space, the temperature in the climate laboratory is kept unchanged before and after the engine slow running, and meanwhile, in order to ensure the test safety and the laboratory building safety, the pressure difference between the inside and the outside of the laboratory is required to be micro-positive pressure, and the micro-positive pressure is kept consistent before and after the engine slow running. Therefore, a balance control system for the slow-running environmental field of the laboratory aircraft engine, which has the capability of testing the slow-running of the laboratory aircraft engine, is lacked nowadays.
Disclosure of Invention
The invention aims to solve the technical problem that the prior art is not enough, and provides a balance control system for an environmental field of a slow-vehicle running of an aircraft engine in a laboratory, which is novel and reasonable in design, and ensures that the temperature and the pressure of the environmental field are kept unchanged before and after the slow-vehicle running of the aircraft engine when the aircraft performs an engine slow-vehicle test in a closed space laboratory through the cooperative work of an environment acquisition mechanism, an air supply temperature control mechanism and an exhaust mechanism which are arranged inside and outside the laboratory, so that the effectiveness of the aircraft engine slow-vehicle test is ensured, meanwhile, the building safety of the laboratory is ensured, and the balance control system is convenient to popularize and use.
In order to solve the technical problems, the invention adopts the technical scheme that: the utility model provides a laboratory aircraft engine slow moving operation environmental field balance control system which characterized in that: the device comprises an environment acquisition mechanism arranged in a laboratory, an air supplementing and temperature controlling mechanism arranged on one side outside the laboratory and communicated with the laboratory, and an exhaust mechanism arranged on the other side outside the laboratory and communicated with the laboratory;
the environment acquisition mechanism comprises a test area temperature sensor and a test area pressure sensor which are arranged in a test area of a laboratory far away from an aircraft engine tail gas discharge port, and an indoor outlet area temperature sensor which is arranged in a position close to a tail gas discharge pipeline in the laboratory;
the air supplementing temperature control mechanism comprises an air supplementing pipeline, a filter, an air supplementing inlet temperature sensor, an air supplementing air quantity measurer, an air supplementing fan, a temperature regulating heat exchanger, an air supplementing outlet temperature sensor and an air supplementing air valve, wherein the filter, the air supplementing inlet temperature sensor, the air supplementing air quantity measurer, the air supplementing fan, the temperature regulating heat exchanger, the air supplementing outlet temperature sensor and the air supplementing air valve are sequentially arranged in the air supplementing pipeline along the air flow direction;
the exhaust mechanism comprises a tail gas exhaust pipeline, and an exhaust inlet temperature sensor, an exhaust air volume measurer, a sprayer, an exhaust air valve, an exhaust fan and an exhaust outlet temperature sensor which are sequentially arranged in the tail gas exhaust pipeline along the airflow direction, wherein a tail gas exhaust differential pressure sensor which is matched with the exhaust air volume measurer to measure the air volume is arranged on the tail gas exhaust pipeline.
The balance control system for the slow-vehicle running environment field of the aircraft engine in the laboratory is characterized in that: and a refrigerating unit evaporator connected with the temperature-adjusting heat exchanger is arranged outside the air supplementing pipeline, and a secondary refrigerant adjusting valve is arranged on a pipeline for supplying secondary refrigerant to the temperature-adjusting heat exchanger by the refrigerating unit evaporator.
The balance control system for the slow-vehicle running environment field of the aircraft engine in the laboratory is characterized in that: the structure of the air supply quantity measurer is the same as that of the exhaust air quantity measurer, and the air supply quantity measurer and the exhaust air quantity measurer respectively comprise a first temperature sensor, a second temperature sensor, a third temperature sensor, a fourth temperature sensor, a fifth temperature sensor and a sixth temperature sensor which are arranged in a coplanar manner.
The balance control system for the slow-vehicle running environment field of the aircraft engine in the laboratory is characterized in that: the first temperature sensor, the second temperature sensor, the third temperature sensor, the fourth temperature sensor, the fifth temperature sensor and the sixth temperature sensor are arranged at every 1/6 radius widths and 60-degree corners along the radius direction of the pipeline by taking the central point of the pipeline as a starting point, pitot tube mounting holes are formed in the side wall of the pipeline, one end of the pitot tube is inserted into the pipeline and is flush with the inner wall surface of the pipeline, the other end of the pitot tube is arranged outside the pipeline, and two ends of the pitot tube are connected to an air supply differential pressure sensor or a tail gas emission differential pressure sensor.
The balance control system for the slow-vehicle running environment field of the aircraft engine in the laboratory is characterized in that: the side wall of the laboratory chamber is provided with a door body.
The balance control system for the slow-vehicle running environment field of the aircraft engine in the laboratory is characterized in that: the device is characterized by further comprising a controller, wherein the test area temperature sensor, the test area pressure sensor, the indoor outlet area temperature sensor, the air supply inlet temperature sensor, the air supply fan, the air supply outlet temperature sensor, the air supply air valve, the air supply air pressure difference sensor, the exhaust inlet temperature sensor, the exhaust air valve, the exhaust fan, the exhaust outlet temperature sensor, the tail gas exhaust pressure difference sensor, the secondary refrigerant adjusting valve, the first temperature sensor, the second temperature sensor, the third temperature sensor, the fourth temperature sensor, the fifth temperature sensor and the sixth temperature sensor are all connected with the controller.
The balance control system for the slow-vehicle running environment field of the aircraft engine in the laboratory is characterized in that: the controller is a computer or a PLC controller.
The air supply temperature control device has the advantages that the environment acquisition mechanism, the air supply temperature control mechanism and the exhaust mechanism which are arranged inside and outside the laboratory work cooperatively, so that when the aircraft performs the engine slow-moving test in the closed space laboratory, the temperature and the pressure of an environment field are kept unchanged before and after the aircraft engine slow-moving test, the effectiveness of the aircraft engine slow-moving test is ensured, meanwhile, the building safety of the laboratory is ensured, and the air supply temperature control device is convenient to popularize and use.
The technical solution of the present invention is further described in detail by the accompanying drawings and embodiments.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic structural view of the air supply quantity measurer or the exhaust air quantity measurer of the present invention.
Description of reference numerals:
1-laboratory; 2, an airplane; 3-test area temperature sensor;
4-test area pressure sensor; 5-indoor exit area temperature sensor;
6-air supplementary pipeline; 7, a filter;
8-inlet temperature sensor for make-up air; 9-air supply quantity measurer;
10-air supply air pressure difference sensor; 11-air supply fan;
12-temperature regulating heat exchanger; 13-coolant regulating valve;
14-temperature sensor of air supply outlet; 15-air supply air valve;
16-a tail gas discharge pipeline; 17-exhaust inlet temperature sensor;
18-exhaust air volume measurer; 19-tail gas discharge differential pressure sensor;
20-a sprayer; 21-exhaust air valve;
22-exhaust fan; 23-exhaust outlet temperature sensor;
24 — a first temperature sensor; 25-a second temperature sensor; 26-a third temperature sensor;
27-a fourth degree sensor; 28-a fifth temperature sensor; 29-sixth temperature sensor;
30-pitot tube mounting hole.
Detailed Description
As shown in fig. 1 and fig. 2, the present invention comprises an environment collecting mechanism disposed in a laboratory 1, an air supply temperature control mechanism disposed at one side outside the laboratory 1 and communicated with the laboratory 1, and an exhaust mechanism disposed at the other side outside the laboratory 1 and communicated with the laboratory 1;
the environment acquisition mechanism comprises a test area temperature sensor 3 and a test area pressure sensor 4 which are arranged in a test area of a laboratory far away from an engine tail gas discharge port of the airplane 2, and an indoor outlet area temperature sensor 5 which is arranged in a position close to a tail gas discharge pipeline in the laboratory;
the air supplementing temperature control mechanism comprises an air supplementing pipeline 6, a filter 7, an air supplementing inlet temperature sensor 8, an air supplementing quantity measurer 9, an air supplementing fan 11, a temperature-adjusting heat exchanger 12, an air supplementing outlet temperature sensor 14 and an air supplementing air valve 15, wherein the filter 7, the air supplementing inlet temperature sensor 8, the air supplementing air quantity measurer 9, the air supplementing fan 11, the temperature-adjusting heat exchanger 12, the air supplementing outlet temperature sensor 14 and the air supplementing air valve 15 are sequentially arranged in the air supplementing pipeline 6 along the air flow direction, and an air supplementing air pressure difference sensor 10 which is matched with the air supplementing quantity measurer 9 to measure air quantity is arranged on the air supplementing pipeline 6;
the exhaust mechanism comprises a tail gas exhaust pipeline 16, and an exhaust inlet temperature sensor 17, an exhaust air volume measurer 18, a sprayer 20, an exhaust air valve 21, an exhaust fan 22 and an exhaust outlet temperature sensor 23 which are sequentially arranged in the tail gas exhaust pipeline 16 along the airflow direction, wherein a tail gas exhaust differential pressure sensor 19 which is matched with the exhaust air volume measurer 18 to measure the air volume is arranged on the tail gas exhaust pipeline 16.
It should be noted that, when an airplane performs an engine slow-running test in a laboratory in a closed space, the temperature of the tail gas of the airplane engine is extremely high, and in order to maintain the temperature in the laboratory to be stable and ensure that the pressure difference inside and outside the laboratory is consistent with that before the engine slow-running, the high-temperature tail gas of the airplane engine needs to be discharged outdoors and compensation air with the same exhaust flow rate needs to be supplemented, and meanwhile, the temperature of the compensation air needs to be the same as the temperature of the air in the laboratory. The balance of the environmental field of the slow vehicle running of the aircraft engine in the laboratory is realized by the cooperative control of the exhaust emission control, the compensation air temperature control and the exhaust supplementing flow.
In this embodiment, a refrigeration unit evaporator connected to the temperature-adjusting heat exchanger 12 is disposed outside the air supply duct 6, and a refrigerant adjusting valve 13 is installed on a duct through which the refrigeration unit evaporator supplies the secondary refrigerant to the temperature-adjusting heat exchanger 12.
In this embodiment, the air supply volume measurer 9 and the exhaust air volume measurer 18 have the same structure, and the air supply volume measurer 9 and the exhaust air volume measurer 18 each include a first temperature sensor 24, a second temperature sensor 25, a third temperature sensor 26, a fourth temperature sensor 27, a fifth temperature sensor 28, and a sixth temperature sensor 29, which are arranged in a coplanar manner.
In this embodiment, the first temperature sensor 24, the second temperature sensor 25, the third temperature sensor 26, the fourth temperature sensor 27, the fifth temperature sensor 28, and the sixth temperature sensor 29 are arranged at every 1/6 radius widths and 60 ° rotation angles along the radius direction of the pipeline with the central point of the pipeline as a starting point, a pitot tube mounting hole 30 is formed in the side wall of the pipeline, one end of the pitot tube is inserted into the pipeline and flush with the inner wall surface of the pipeline, the other end of the pitot tube is outside the pipeline, and the two ends of the pitot tube are connected to the air supply differential pressure sensor 10 or the exhaust emission differential pressure sensor 19.
In this embodiment, a door is disposed on a side wall of the laboratory 1.
In this embodiment, the device further comprises a controller, and the test area temperature sensor 3, the test area pressure sensor 4, the indoor outlet area temperature sensor 5, the air supply inlet temperature sensor 8, the air supply fan 11, the air supply outlet temperature sensor 14, the air supply air valve 15, the air supply air pressure difference sensor 10, the exhaust inlet temperature sensor 17, the exhaust air valve 21, the exhaust fan 22, the exhaust outlet temperature sensor 23, the tail gas discharge pressure difference sensor 19, the coolant adjusting valve 13, the first temperature sensor 24, the second temperature sensor 25, the third temperature sensor 26, the fourth temperature sensor 27, the fifth temperature sensor 28 and the sixth temperature sensor 29 are all connected with the controller.
In this embodiment, the controller is a computer or a PLC controller.
When the invention is used, the method comprises the following steps:
step one, measuring the maximum operating frequency of an exhaust fan in a non-closed state of a laboratory: enabling the laboratory 1 to be in an unclosed state, enabling the laboratory 1 to be communicated with outside air, opening an exhaust air valve 21 and a sprayer 20, enabling an aircraft engine to run slowly, gradually increasing the frequency of an exhaust air fan 22, enabling the measurement value of an indoor outlet area temperature sensor 5 to be increased and then decreased until the measurement value of the indoor outlet area temperature sensor 5 is the same as that of a test area temperature sensor 3, and stopping adjusting the running frequency of the exhaust air fan 22, wherein at the moment, the running frequency of the exhaust air fan 22 is the maximum running frequency fm of the exhaust air fan 22;
step two, under the closed and experimental temperature state of laboratory, the tonifying qi fan begins to operate and the synchronous control compensation air temperature with the frequency of 10 Hz: adjusting the temperature of a laboratory test area to reach the temperature required by the slow-vehicle test of the aircraft engine
The air supply fan 11 starts to operate at a frequency of 10Hz, the temperature of the compensation air is synchronously controlled, and the temperature of the compensation air entering the laboratory 1 is measured by the air supply outlet temperature sensor 14
Adjusting the opening degree of the secondary refrigerant adjusting valve 13 when
When the temperature of the compensation air is reduced, the secondary refrigerant adjusting valve 13 is fully opened, and the temperature adjusting heat exchanger 12 cools the compensation air
When the temperature of the compensation air is increased, the secondary refrigerant adjusting valve 13 is closed, and the temperature adjusting heat exchanger 12 heats the compensation air until the temperature is increased
The temperature of a laboratory test area meets the precision required by the aircraft engine slow-speed test temperature;
step three, starting an exhaust fan, and cooperatively controlling and compensating the air flow and the temperature: under the closed and test temperature state of the laboratory, opening the exhaust air valve 21 and the sprayer 20, and starting to operate the exhaust fan 22 at the frequency of 10 Hz;
according to the formula
And calculates the exhaust gas velocity when the exhaust fan 22 is operated at a frequency of 10Hz
Wherein, in the step (A),
the micro-positive pressure measured by the exhaust emission differential pressure sensor 19 when the exhaust fan 22 operates at a frequency of 10Hz, m is the pitot tube coefficient, i is the serial number of the temperature sensor in the exhaust air quantity measurer 18, and
i=1,2，...，6，
，
is the indoor pressure value collected by the test area pressure sensor 4,
is the value of the standard atmospheric pressure,
a temperature value measured by the ith temperature sensor in the exhaust air volume measurer 18 for the exhaust fan 22 operating at a frequency of 10 Hz;
according to the formula
And calculates the amount of exhaust emissions when the exhaust fan 22 is operated at a frequency of 10Hz
Wherein, in the step (A),
the cross-sectional area of the exhaust gas discharge pipe 16;
step four, increasing air supply and exhaust flow in a stepped manner, and synchronously controlling and compensating air temperature: increasing the operating frequency of the exhaust fan 22 by 1Hz step length, and when the operating frequency of the exhaust fan 22 is increased by 1Hz, acquiring the tail gas emission amount under the corresponding operating frequency according to the method in the third step, and adjusting the operating frequency of the air supply fan 11 so as to control the compensation air flow rate, so that the compensation air flow rate is the same as the tail gas emission amount of the exhaust fan 22 under the corresponding operating frequency, and simultaneously, synchronously controlling the compensation air temperature according to the method in the second step, so that the temperature of a laboratory test area meets the temperature requirement precision of the aircraft engine slow-speed test;
step five, carrying out an airplane engine slow-vehicle running test in a laboratory: the method comprises the following steps of (1) running the aircraft engine slowly, starting a climate environment adaptability verification test of the running of the aircraft engine slowly, running the exhaust fan 22 at fm frequency, adjusting the running frequency of the exhaust fan 22 according to a laboratory micro-positive pressure design value in the test process, ensuring that the laboratory micro-positive pressure is maintained between 10Pa and 30Pa, adjusting the running frequency of the exhaust fan 22, obtaining the tail gas emission amount under the current corresponding running frequency according to a mode in the step three, adjusting the running frequency of the air supply fan 11 so as to control the compensation air flow, enabling the compensation air flow to be the same as the tail gas emission amount of the exhaust fan 22 under the current corresponding running frequency, and synchronously controlling a compensation air temperature mode according to the step two so that the temperature of a laboratory test area meets the temperature requirement precision of the aircraft engine slowly running test;
step six, stopping the slow operation of the engine of the airplane, and reducing the air supplement and exhaust flow in a stepped mode: completing a slow-vehicle operation weather environment adaptability verification test of the aircraft engine, stopping the operation of the aircraft engine, reducing the operation frequency of the exhaust fan 22 by 5Hz step length, obtaining the tail gas emission amount under the current corresponding operation frequency in a three-step mode when the operation frequency of the exhaust fan 22 is reduced by 5Hz, adjusting the operation frequency of the air supply fan 11 so as to control the compensation air flow, enabling the compensation air flow to be the same as the tail gas emission amount of the exhaust fan 22 under the current corresponding operation frequency, enabling the compensation air flow to be synchronously reduced in a stepped mode with the exhaust flow until the exhaust fan 22 and the air supply fan 11 stop operating, and closing the tail gas emission pipeline 16 and the air supplement pipeline 6.
The environment acquisition mechanism, the air supply temperature control mechanism and the exhaust mechanism which are arranged inside and outside the laboratory work in a cooperative mode to ensure that the temperature and the pressure of an environmental field are kept unchanged before and after the airplane engine is slowly run when the airplane performs the engine slow running test in the closed space laboratory, the compensation air flow is increased step by step, and the compensation air temperature is synchronously controlled to be the temperature of a test area at each stage of flow, so that the temperature of the laboratory cannot be severely fluctuated due to compensation air supplement, the temperature of the test area of the laboratory meets the temperature requirement precision of the airplane engine slow running test, and the effectiveness of the airplane engine slow running test is ensured; the air flow rate of the exhaust and compensation is cooperatively controlled in a stepped manner, the micro-positive pressure of a closed space laboratory is maintained between 10Pa and 30Pa, and the building safety of the laboratory is ensured.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and all simple modifications, changes and equivalent structural changes made to the above embodiment according to the technical spirit of the present invention still fall within the protection scope of the technical solution of the present invention.
Claims (6)
1. The utility model provides a laboratory aircraft engine slow moving operation environmental field balance control system which characterized in that: comprises an environment acquisition mechanism arranged in a laboratory (1), an air supply and temperature control mechanism arranged at one side outside the laboratory (1) and communicated with the laboratory (1), and an exhaust mechanism arranged at the other side outside the laboratory (1) and communicated with the laboratory (1);
the environment acquisition mechanism comprises a test area temperature sensor (3) and a test area pressure sensor (4) which are arranged in a test area of a laboratory far away from an engine tail gas discharge port of the airplane (2), and an indoor outlet area temperature sensor (5) which is arranged in a position close to a tail gas discharge pipeline in the laboratory;
the air supplementing temperature control mechanism comprises an air supplementing pipeline (6), a filter (7), an air supplementing inlet temperature sensor (8), an air supplementing air quantity measurer (9), an air supplementing fan (11), a temperature regulating heat exchanger (12), an air supplementing outlet temperature sensor (14) and an air supplementing air valve (15), wherein the filter (7), the air supplementing inlet temperature sensor, the air supplementing air quantity measurer (9), the air supplementing fan (11), the temperature regulating heat exchanger (12), the air supplementing outlet temperature sensor (14) and the air supplementing air valve (15) are sequentially arranged in the air supplementing pipeline (6) along the air flow direction, and an air supplementing air pressure difference sensor (10) which is matched with the air supplementing air quantity measurer (9) to measure the air quantity is arranged on the air supplementing pipeline (6);
the exhaust mechanism comprises a tail gas exhaust pipeline (16) and an exhaust inlet temperature sensor (17), an exhaust air volume measurer (18), a sprayer (20), an exhaust air valve (21), an exhaust fan (22) and an exhaust outlet temperature sensor (23) which are sequentially arranged in the tail gas exhaust pipeline (16) along the airflow direction, wherein a tail gas exhaust differential pressure sensor (19) which is matched with the exhaust air volume measurer (18) to measure the air volume is arranged on the tail gas exhaust pipeline (16);
a door body is arranged on the side wall of the laboratory (1);
when in use, the method comprises the following steps:
step one, measuring the maximum operating frequency of an exhaust fan in a non-closed state of a laboratory: enabling the laboratory (1) to be in an unclosed state, enabling the laboratory (1) to be communicated with outside air, opening an exhaust air valve (21) and a sprayer (20), enabling an aircraft engine to run slowly, gradually increasing the frequency of an exhaust fan (22), enabling the measurement value of an indoor outlet area temperature sensor (5) to increase and then decrease until the measurement value of the indoor outlet area temperature sensor (5) is the same as that of a test area temperature sensor (3), stopping adjusting the operation frequency of the exhaust fan (22), and enabling the operation frequency of the exhaust fan (22) to be the maximum operation frequency fm of the exhaust fan (22);
step two, under the closed and experimental temperature state of laboratory, the tonifying qi fan begins to operate and the synchronous control compensation air temperature with the frequency of 10 Hz: adjusting the temperature of a laboratory test area to reach the temperature required by the slow-vehicle test of the aircraft engine
The air supply fan (11) starts to run at the frequency of 10Hz, the temperature of the compensation air is synchronously controlled, and the temperature of the compensation air entering the laboratory 1 is measured by the air supply outlet temperature sensor (14)
Adjusting the opening degree of a secondary refrigerant adjusting valve (13) when
When the temperature of the compensation air is reduced, the secondary refrigerant adjusting valve (13) is fully opened, and the temperature adjusting heat exchanger (12) cools the compensation air
When the temperature of the compensation air is increased, the secondary refrigerant adjusting valve (13) is closed, and the temperature adjusting heat exchanger (12) heats the compensation air until the temperature is increased
The temperature of a laboratory test area meets the precision required by the aircraft engine slow-speed test temperature;
step three, starting an exhaust fan, and cooperatively controlling and compensating the air flow and the temperature: under the closed and test temperature state of a laboratory, an exhaust air valve (21) and a sprayer (20) are opened, and an exhaust fan (22) starts to operate at the frequency of 10 Hz;
according to the formula
And calculating the exhaust gas velocity when the exhaust fan (22) is operated at a frequency of 10Hz
Wherein, in the step (A),
the micro-positive pressure measured by a tail gas discharge differential pressure sensor (19) when an exhaust fan (22) operates at the frequency of 10Hz, m is the pitot tube coefficient, i is the serial number of a temperature sensor in an exhaust air quantity measurer (18)
i=1,2，...，6，
，
Is an indoor pressure value collected by a pressure sensor (4) in a test area,
is the value of the standard atmospheric pressure,
the temperature value measured by the ith temperature sensor in the exhaust air volume measurer (18) when the exhaust fan (22) operates at the frequency of 10 Hz;
according to the formula
And calculating the exhaust emission of the exhaust fan (22) when the exhaust fan operates at a frequency of 10Hz
Wherein, in the step (A),
the cross-sectional area of the exhaust gas discharge pipeline (16);
step four, increasing air supply and exhaust flow in a stepped manner, and synchronously controlling and compensating air temperature: increasing the operating frequency of the exhaust fan (22) by 1Hz step length, obtaining the tail gas discharge amount under the corresponding operating frequency according to the mode in the third step when the operating frequency of the exhaust fan (22) is increased by 1Hz, adjusting the operating frequency of the air supply fan (11) so as to control the compensation air flow rate, enabling the compensation air flow rate to be the same as the tail gas discharge amount of the exhaust fan (22) under the corresponding operating frequency, and simultaneously synchronously controlling the compensation air temperature mode according to the second step so as to enable the temperature of a laboratory test area to meet the temperature requirement precision of the aircraft engine slow-speed test;
step five, carrying out an airplane engine slow-vehicle running test in a laboratory: the method comprises the following steps of (1) enabling an aircraft engine to run slowly, starting a climate environment adaptability verification test of the running of the aircraft engine slow, enabling an exhaust fan (22) to run at the frequency of fm, adjusting the running frequency of the exhaust fan (22) according to a laboratory micro-positive pressure design value in the test process, ensuring that the laboratory micro-positive pressure is maintained between 10Pa and 30Pa, adjusting the running frequency of the exhaust fan (22), obtaining the tail gas emission amount under the current corresponding running frequency according to a three-step mode, adjusting the running frequency of an air supply fan (11) so as to control the compensation air flow, enabling the compensation air flow to be the same as the tail gas emission amount of the exhaust fan (22) under the current corresponding running frequency, and synchronously controlling the compensation air temperature according to a two-step mode so that the temperature of a test area of a laboratory meets the requirement precision of the temperature of the aircraft engine slow test;
step six, stopping the slow operation of the engine of the airplane, and reducing the air supplement and exhaust flow in a stepped mode: the method comprises the steps of completing a slow-vehicle running weather environment adaptability verification test of the aircraft engine, stopping the aircraft engine, reducing the running frequency of an exhaust fan (22) by 5Hz steps, obtaining the tail gas emission amount under the current corresponding running frequency in a three-step mode when the running frequency of the exhaust fan (22) is reduced by 5Hz, adjusting the running frequency of an air supply fan (11) so as to control the compensation air flow, enabling the compensation air flow to be the same as the tail gas emission amount of the exhaust fan (22) under the current corresponding running frequency, enabling the compensation air flow and the exhaust flow to be reduced in a stepped mode and synchronously until the exhaust fan (22) and the air supply fan (11) stop running, and closing a tail gas emission pipeline (16) and an air supplement pipeline (6).
2. The laboratory aircraft engine slow vehicle operation environmental field balance control system according to claim 1, wherein: a refrigerating unit evaporator connected with the temperature adjusting heat exchanger (12) is arranged outside the air supplementing pipeline (6), and a secondary refrigerant adjusting valve (13) is arranged on a pipeline for supplying secondary refrigerant to the temperature adjusting heat exchanger (12) by the refrigerating unit evaporator.
3. The laboratory aircraft engine slow vehicle operation environmental field balance control system according to claim 2, characterized in that: the structure of the air supply quantity measurer (9) is the same as that of the exhaust air quantity measurer (18), and the air supply quantity measurer (9) and the exhaust air quantity measurer (18) respectively comprise a first temperature sensor (24), a second temperature sensor (25), a third temperature sensor (26), a fourth temperature sensor (27), a fifth temperature sensor (28) and a sixth temperature sensor (29) which are arranged in a coplanar manner.
4. The laboratory aircraft engine slow vehicle operation environmental field balance control system according to claim 3, wherein: the first temperature sensor (24), the second temperature sensor (25), the third temperature sensor (26), the fourth temperature sensor (27), the fifth temperature sensor (28) and the sixth temperature sensor (29) are arranged at every 1/6 radius widths and 60-degree corners along the radius direction of the pipeline by taking the central point of the pipeline as a starting point, pitot tube mounting holes (30) are formed in the side wall of the pipeline, one end of a pitot tube is inserted into the pipeline and is level with the inner wall surface of the pipeline, the other end of the pitot tube is arranged outside the pipeline, and the two ends of the pitot tube are connected to the air supply pressure difference sensor (10) or the tail gas discharge pressure difference sensor (19).
5. The laboratory aircraft engine slow vehicle operation environmental field balance control system according to claim 4, wherein: the device is characterized by further comprising a controller, wherein the test area temperature sensor (3), the test area pressure sensor (4), the indoor outlet area temperature sensor (5), the air supply inlet temperature sensor (8), the air supply fan (11), the air supply outlet temperature sensor (14), the air supply air valve (15), the air supply air pressure difference sensor (10), the exhaust inlet temperature sensor (17), the exhaust air valve (21), the exhaust fan (22), the exhaust outlet temperature sensor (23), the tail gas exhaust pressure difference sensor (19), the secondary refrigerant adjusting valve (13), the first temperature sensor (24), the second temperature sensor (25), the third temperature sensor (26), the fourth temperature sensor (27), the fifth temperature sensor (28) and the sixth temperature sensor (29) are connected with the controller.
6. The laboratory aircraft engine slow vehicle operation environmental field balance control system according to claim 5, wherein: the controller is a computer or a PLC controller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111507582.9A CN113899555B (en) | 2021-12-10 | 2021-12-10 | Balance control system for slow-vehicle running environment field of laboratory aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111507582.9A CN113899555B (en) | 2021-12-10 | 2021-12-10 | Balance control system for slow-vehicle running environment field of laboratory aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN113899555A CN113899555A (en) | 2022-01-07 |
| CN113899555B true CN113899555B (en) | 2022-04-08 |
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| CN114577504B (en) * | 2022-05-07 | 2022-07-12 | 中国飞机强度研究所 | Anti-freezing pressure adjusting system for aircraft test and adjusting method thereof |
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