CN113901595A - Design method for aircraft APU (auxiliary Power Unit) exhaust system in laboratory - Google Patents

Design method for aircraft APU (auxiliary Power Unit) exhaust system in laboratory Download PDF

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CN113901595A
CN113901595A CN202111507177.7A CN202111507177A CN113901595A CN 113901595 A CN113901595 A CN 113901595A CN 202111507177 A CN202111507177 A CN 202111507177A CN 113901595 A CN113901595 A CN 113901595A
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laboratory
pipeline
apu
aircraft
water
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CN113901595B (en
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强宝平
王彬文
成竹
李剑
任战鹏
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AVIC Aircraft Strength Research Institute
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AVIC Aircraft Strength Research Institute
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K13/00—Thermometers specially adapted for specific purposes
    • G01K13/02—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow
    • G01K13/024—Thermometers specially adapted for specific purposes for measuring temperature of moving fluids or granular materials capable of flow of moving gases
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
    • G01L11/00—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2113/00—Details relating to the application field
    • G06F2113/08—Fluids
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/08—Thermal analysis or thermal optimisation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/14—Force analysis or force optimisation, e.g. static or dynamic forces

Abstract

The invention discloses a design method of an APU (auxiliary Power Unit) exhaust system of an airplane in a laboratory, which comprises the following steps: firstly, determining the diameter of an initial adjusting pipeline; secondly, setting the length of an initial adjusting pipeline; thirdly, determining the diameter of the drainage pipeline; judging whether the tail gas is completely stored in the exhaust equipment of the aircraft APU; fifthly, selecting the type of the fan; sixthly, determining the mass flow of water for spraying and cooling; and seventhly, determining the number of the spraying cooling mechanisms. The invention provides a basis for the model selection design of an APU (auxiliary Power Unit) exhaust system of an airplane in a laboratory, saves material resources and manpower, solves the problem of driving the APU in the laboratory, lays an important foundation for the development of a climate test in the laboratory, can completely discharge the tail gas of the APU with high temperature and high pressure, ensures the stability of the temperature and the pressure in the laboratory, ensures the safety of the airplane and testers, performs cooling treatment on the high-temperature tail gas, and ensures that the tail gas discharged outside the laboratory cannot cause harm to the personnel outside the laboratory.

Description

Design method for aircraft APU (auxiliary Power Unit) exhaust system in laboratory
Technical Field
The invention belongs to the technical field of design of an APU (auxiliary Power Unit) drainage and exhaust system in the starting process of an APU (auxiliary Power Unit) of an airplane in a closed laboratory, and particularly relates to a design method of an APU exhaust system of an airplane in the laboratory.
Background
The weather experiment is carried out in a full-aircraft climate laboratory, and an aircraft APU needs to be started to provide power for the aircraft. If the high-temperature and high-pressure tail gas discharged by the APU is directly discharged into a laboratory, the temperature and pressure environment in the laboratory can be damaged, and meanwhile, the tail gas is accumulated in the laboratory, so that the safety of the laboratory, an airplane and even testing personnel can be threatened. Therefore, when the aircraft APU is turned on in a laboratory, the exhaust gas needs to be discharged outside the laboratory. The laboratory aircraft APU exhaust equipment comprises an initial adjustment pipeline, a drainage pipeline used for discharging gas out of a laboratory and a fan installed at an exhaust end of the drainage pipeline, spray cooling equipment is arranged in the initial adjustment pipeline, the construction of the existing laboratory aircraft APU exhaust system is all according to experience, random parameters are selected to construct the laboratory aircraft APU exhaust system, the pipeline size is larger, the fresh air supplement capacity is exceeded, the fan power consumption is large, the spray cooling equipment has huge spray water quantity, and resources are wasted.
Disclosure of Invention
The invention aims to solve the technical problem that the defects in the prior art are overcome, and provides a design method of an APU (auxiliary Power Unit) exhaust system of a laboratory aircraft, which provides a basis for the model selection design of the APU exhaust system of the laboratory aircraft, saves material resources and manpower, solves the problem of driving the APU in the laboratory, lays an important foundation for the development of climate tests in the laboratory, can completely discharge high-temperature and high-pressure APU tail gas, ensures the stability of temperature and pressure in the laboratory, ensures the safety of the aircraft and testers, performs cooling treatment on the high-temperature tail gas, ensures that the tail gas outside the laboratory is discharged, does not harm the personnel outside the laboratory, and is convenient to popularize and use.
In order to solve the technical problems, the invention adopts the technical scheme that: the design method of the indoor airplane APU exhaust system comprises a laboratory for accommodating an airplane and airplane APU exhaust equipment for outputting the exhaust of the airplane APU to the outside, wherein the airplane APU exhaust equipment comprises an initial adjusting pipeline, a drainage pipeline, a butterfly valve and a fan which are sequentially connected, a spray cooler is arranged on the initial adjusting pipeline and comprises a plurality of spray cooling mechanisms which are uniformly arranged along the length direction of the initial adjusting pipeline, each spray cooling mechanism comprises a water supply pipe arranged outside the initial adjusting pipeline and a plurality of spray ring pipes which are uniformly arranged on the inner wall of the initial adjusting pipeline along the length direction of the initial adjusting pipeline, and a plurality of water spray holes are uniformly formed in the side wall of each spray ring pipe facing the inner center direction of the initial adjusting pipeline;
the water supply pipe is provided with an input pipe and a plurality of output pipes, the number of the output pipes on the water supply pipe is equal to the number of the spraying ring pipes in the spraying and cooling mechanism and corresponds to the number of the spraying ring pipes one by one, and the output pipes are provided with valves and flow sensors;
an exhaust port temperature sensor is arranged in the position, which is close to the 3m position of the airplane APU exhaust in the laboratory, and a laboratory environment temperature sensor and a laboratory environment pressure sensor are arranged in the position, which is located in the non-working area of the airplane, in the laboratory;
the initial adjusting pipeline and the drainage pipeline are both round pipes;
the method is characterized by comprising the following steps:
step one, determining the diameter of an initial adjusting pipeline: establishing three-dimensional models of the distribution of airflow structures at the air outlet of the aircraft APU and around the air outlet of the aircraft APU by using CATIA software, meshing the three-dimensional models in a mixed mesh form, introducing the three-dimensional models into FLUENT software, acquiring the distribution of the airflow structures around the air outlet of the aircraft APU in a natural jet state, and acquiring the maximum boundary of the airflow in three directions; calculating the diameter D of the initial adjusting pipeline according to a formula D = L + DeltaL, wherein L is the maximum boundary in the airflow jet width or height direction, and DeltaL is the boundary safety reserved value in the airflow jet width or height direction;
step two, setting the length of an initial adjusting pipeline: giving the length of an initial adjustment pipeline according to the distance between the air outlet of the aircraft APU and the side wall of the laboratory chamber opposite to the air outlet of the aircraft APU, wherein the initial adjustment pipeline is a straight pipe, and the joint section of the drainage pipeline and the initial adjustment pipeline is a straight pipe;
step three, determining the diameter of the drainage pipeline: setting the diameter of the drainage pipeline to be smaller than the diameter of the initial adjustment pipeline, inputting the diameter of the initial adjustment pipeline and the set diameter of the drainage pipeline in FLUENT software, and performing numerical calculation to obtain a pressure field in the drainage pipeline;
adjusting the turning radius of the drainage pipeline and the internal smoothness of the pipeline for multiple times in FLUENT software, and performing numerical calculation to obtain the diameter of the drainage pipeline meeting the requirement of a pressure field;
step four, judging whether the aircraft APU exhaust equipment completely stores tail gas: acquiring whether the tail gas is completely stored in the aircraft APU exhaust equipment in a natural jet state or not in FLUENT software by utilizing the determined initial adjusting pipeline diameter and the determined drainage pipeline diameter, and executing a fifth step when the tail gas can be completely stored in the aircraft APU exhaust equipment; when the tail gas can not be completely stored in the exhaust equipment of the aircraft APU, adjusting a boundary safety reserved value in the airflow jet width or height direction, and executing the second step and the third step until the tail gas can be completely stored in the exhaust equipment of the aircraft APU;
step five, fan type selection: the temperature of the position 3m outside the exhaust port of the airplane APU is collected in real time by using an exhaust port temperature sensor, and the environmental temperature in a laboratory is collected in real time by using a laboratory environmental temperature sensor;
gradually increasing the frequency of the fan, increasing and then reducing the temperature value at the position of the exhaust port temperature sensor in the laboratory, wherein the temperature value at the position of the exhaust port temperature sensor in the laboratory is the same as the temperature value at the position of the laboratory environment temperature sensor in the laboratory, the pressure at the position of the laboratory environment pressure sensor in the laboratory meets the micro-positive pressure index, stopping adjusting the frequency of the fan, and selecting the fan type meeting the requirement;
step six, determining the mass flow of water for spraying and cooling: according to the formula
Figure 673834DEST_PATH_IMAGE001
Determining the mass flow of water for spraying and cooling
Figure 958185DEST_PATH_IMAGE002
Wherein, in the step (A),
Figure 370712DEST_PATH_IMAGE003
to initially adjust the mass flow rate of the gas stream in the duct,
Figure 84196DEST_PATH_IMAGE004
to initially adjust the average specific heat capacity of the air flow in the duct,
Figure 265779DEST_PATH_IMAGE005
to initially adjust the temperature of the air flow within the duct,
Figure 455452DEST_PATH_IMAGE006
the temperature is set for the safety of the tail gas emission,
Figure 355275DEST_PATH_IMAGE007
the percentage of water evaporation is used for spray cooling, the beta is the safety coefficient of water consumption,
Figure 921385DEST_PATH_IMAGE008
the specific heat capacity of water, delta T is the temperature variation of the water vapor changed from the initial temperature by the spraying cooling water, and delta Q is the specific latent heat of vaporization of the water;
seventhly, determining the number of the spraying cooling mechanisms: the number of the spraying and cooling mechanisms is determined according to the length of the initial adjustment pipeline, the number of the plurality of spraying and cooling mechanisms is uniformly distributed on the initial adjustment pipeline, and the number of the water spraying holes in each spraying ring pipe is determined according to the mass flow of water for spraying and cooling, so that the mass flow of the water sprayed by the plurality of spraying and cooling mechanisms meets the requirement.
The design method of the aircraft APU exhaust system in the laboratory is characterized in that: the water consumption safety coefficient beta is 1.5-2.
The design method of the aircraft APU exhaust system in the laboratory is characterized in that: the micro-positive pressure index is 10 Pa-80 Pa.
The design method of the aircraft APU exhaust system in the laboratory is characterized in that: the safe set temperature of the exhaust emission
Figure 223054DEST_PATH_IMAGE006
Not more than 80 ℃.
The design method of the aircraft APU exhaust system in the laboratory is characterized in that: the water supply pipe is a water supply pipe having one input pipe and two to four output pipes.
Compared with the prior art, the invention has the following advantages:
1. according to the method, the FLUENT software is used for obtaining the distribution of the airflow organization around the air outlet of the aircraft APU in a natural jet state, the maximum boundaries of the airflow in three directions are obtained, the basis is provided for selecting the initial adjustment pipeline diameter, the initial adjustment pipeline length is given, the tail gas amount which can be accommodated by the initial adjustment pipeline is determined by the initial adjustment pipeline length, the water spraying amount of the spraying and cooling mechanism is further determined, whether the indoor environment is balanced under the driving condition of the APU is detected by using the indoor air outlet temperature sensor, the laboratory environment temperature sensor and the laboratory environment pressure sensor, the fan type meeting the requirement is further selected, the stability of the temperature and the pressure in the laboratory is ensured, the safety of the aircraft and testers is ensured, and the method is convenient to popularize and use.
2. According to the invention, the turning radius of the drainage pipeline and the smoothness degree of the interior of the pipeline are adjusted for multiple times in FLUENT software, numerical calculation is carried out, the diameter of the drainage pipeline meeting the requirement of a pressure field is obtained, whether tail gas is completely stored in the exhaust equipment of the aircraft APU is checked, the size and the type selection of the exhaust equipment of the aircraft APU are determined according to the size and the type selection of the exhaust equipment of the aircraft APU, and the effect is good.
3. The method provided by the invention has simple steps, provides a basis for the model selection design of the airplane APU exhaust system in the laboratory, saves material resources and manpower, solves the problem of driving the APU in the laboratory, lays an important foundation for the development of climate tests in the laboratory, and is convenient to popularize and use.
In conclusion, the invention provides a basis for the model selection design of the APU exhaust system of the airplane in the laboratory, saves material resources and manpower, solves the problem of driving the APU in the laboratory, lays an important foundation for the development of climate tests in the laboratory, can completely discharge the tail gas of the APU with high temperature and high pressure, ensures the stability of temperature and pressure in the laboratory, ensures the safety of the airplane and testers, performs cooling treatment on the high-temperature tail gas, ensures that the tail gas discharged outside the laboratory does not cause harm to the personnel outside the laboratory, and is convenient for popularization 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 layout diagram of an aircraft APU exhaust system in a laboratory of the present invention.
Fig. 2 is a schematic structural view of the exhaust mechanism of the present invention.
FIG. 3 is a schematic view of the connection between the spray cooler and the initial adjustment pipe according to the present invention.
FIG. 4 is a block diagram of a method flow of the present invention.
Description of reference numerals:
1-initial adjustment of the pipeline; 2-a drainage pipeline; 3, a butterfly valve;
4, a fan; 5, a spray cooler; 5-1-spraying ring pipe;
5-2-water supply pipe; 5-3-valve; 5-4-flow sensor;
6-laboratory; 7-an airplane; 8-exhaust port temperature sensor;
9-a laboratory ambient temperature sensor; 10-laboratory ambient pressure sensor.
Detailed Description
As shown in fig. 1 to 4, the method for designing the exhaust system of the APU of the laboratory aircraft according to the present invention, the laboratory aircraft APU exhaust system comprises a laboratory 6 for accommodating an aircraft 7 and aircraft APU exhaust equipment for outputting the exhaust of the aircraft APU to the outside, the aircraft APU exhaust equipment comprises an initial adjusting pipeline 1, a drainage pipeline 2, a butterfly valve 3 and a fan 4 which are sequentially connected, a spray cooler 5 is arranged on the initial adjusting pipeline 1, the spray cooler 5 comprises a plurality of spray cooling mechanisms which are uniformly arranged along the length direction of the initial adjusting pipeline 1, the spraying cooling mechanism comprises a water supply pipe 5-2 arranged outside the initial adjusting pipeline 1 and a plurality of spraying ring pipes 5-1 which are uniformly arranged on the inner wall of the initial adjusting pipeline 1 along the length direction of the initial adjusting pipeline 1, a plurality of water spray holes are uniformly formed in the side wall of the spray ring pipe 5-1 facing the inner center direction of the initial adjustment pipeline 1;
the water supply pipe 5-2 is provided with an input pipe and a plurality of output pipes, the number of the output pipes on the water supply pipe 5-2 is equal to the number of the spray ring pipes 5-1 in the spray cooling mechanism and corresponds to one, and the output pipes are provided with valves 5-3 and flow sensors 5-4;
an exhaust port temperature sensor 8 is arranged in the position, close to the 3m position of the airplane APU exhaust, in the laboratory 6, and a laboratory environment temperature sensor 9 and a laboratory environment pressure sensor 10 are arranged in the position, located in the airplane non-working area, in the laboratory 6;
the initial adjusting pipeline 1 and the drainage pipeline 2 are both round pipes;
the method comprises the following steps:
step one, determining the diameter of an initial adjusting pipeline: establishing three-dimensional models of the distribution of airflow structures at the air outlet of the aircraft APU and around the air outlet of the aircraft APU by using CATIA software, meshing the three-dimensional models in a mixed mesh form, introducing the three-dimensional models into FLUENT software, acquiring the distribution of the airflow structures around the air outlet of the aircraft APU in a natural jet state, and acquiring the maximum boundary of the airflow in three directions; calculating the diameter D of the initial adjusting pipeline according to a formula D = L + DeltaL, wherein L is the maximum boundary in the airflow jet width or height direction, and DeltaL is the boundary safety reserved value in the airflow jet width or height direction;
step two, setting the length of an initial adjusting pipeline: giving the length of an initial adjustment pipeline according to the distance between the air outlet of the aircraft APU and the side wall of the laboratory chamber opposite to the air outlet of the aircraft APU, wherein the initial adjustment pipeline 1 is a straight pipe, and the connection section of the drainage pipeline and the initial adjustment pipeline 1 is a straight pipe;
step three, determining the diameter of the drainage pipeline: setting the diameter of the drainage pipeline to be smaller than the diameter of the initial adjustment pipeline, inputting the diameter of the initial adjustment pipeline and the set diameter of the drainage pipeline in FLUENT software, and performing numerical calculation to obtain a pressure field in the drainage pipeline;
adjusting the turning radius of the drainage pipeline and the internal smoothness of the pipeline for multiple times in FLUENT software, and performing numerical calculation to obtain the diameter of the drainage pipeline meeting the requirement of a pressure field;
step four, judging whether the aircraft APU exhaust equipment completely stores tail gas: acquiring whether the tail gas is completely stored in the aircraft APU exhaust equipment in a natural jet state or not in FLUENT software by utilizing the determined initial adjusting pipeline diameter and the determined drainage pipeline diameter, and executing a fifth step when the tail gas can be completely stored in the aircraft APU exhaust equipment; when the tail gas can not be completely stored in the exhaust equipment of the aircraft APU, adjusting a boundary safety reserved value in the airflow jet width or height direction, and executing the second step and the third step until the tail gas can be completely stored in the exhaust equipment of the aircraft APU;
step five, fan type selection: the temperature of the position 3m outside the exhaust port of the airplane APU is collected in real time by using an exhaust port temperature sensor 8, and the environment temperature in a laboratory is collected in real time by using a laboratory environment temperature sensor 9;
gradually increasing the frequency of the fan 4, increasing and then reducing the temperature value at the position of the exhaust port temperature sensor 8 in the laboratory, wherein the temperature value at the position of the exhaust port temperature sensor 8 in the laboratory is the same as the temperature value at the position of the laboratory environment temperature sensor 9 in the laboratory, the pressure at the position of the laboratory environment pressure sensor 10 in the laboratory meets the micro-positive pressure index, stopping adjusting the frequency of the fan 4, and selecting the fan type meeting the requirement;
step six, determining the mass flow of water for spraying and cooling: according to the formula
Figure 521311DEST_PATH_IMAGE001
Determining the mass flow of water for spraying and cooling
Figure 908430DEST_PATH_IMAGE002
Wherein, in the step (A),
Figure 278231DEST_PATH_IMAGE003
to initially adjust the mass flow rate of the gas stream in the duct,
Figure 168827DEST_PATH_IMAGE004
to initially adjust the average specific heat capacity of the air flow in the duct,
Figure 965882DEST_PATH_IMAGE005
to initially adjust the temperature of the air flow within the duct,
Figure 574718DEST_PATH_IMAGE006
the temperature is set for the safety of the tail gas emission,
Figure 935161DEST_PATH_IMAGE007
the percentage of water evaporation is used for spray cooling, the beta is the safety coefficient of water consumption,
Figure 945842DEST_PATH_IMAGE008
the specific heat capacity of water, delta T is the temperature variation of the water vapor changed from the initial temperature by the spraying cooling water, and delta Q is the specific latent heat of vaporization of the water;
seventhly, determining the number of the spraying cooling mechanisms: the number of the spraying and cooling mechanisms is determined according to the length of the initial adjusting pipeline, the number of the plurality of spraying and cooling mechanisms is uniformly distributed on the initial adjusting pipeline 1, and the number of the water spraying holes in each spraying ring pipe 5-1 is determined according to the mass flow of water for spraying and cooling, so that the mass flow of the water sprayed by the plurality of spraying and cooling mechanisms meets the requirement.
In the embodiment, the water consumption safety coefficient beta is 1.5-2.
In this embodiment, the micro positive pressure index is 10 to 80 Pa.
In this embodiment, theSafe set temperature for tail gas emission
Figure 913798DEST_PATH_IMAGE006
Not more than 80 ℃.
In this embodiment, the water supply pipe 5-2 is a water supply pipe having one input pipe and two to four output pipes.
When the system is used, the FLUENT software is used for acquiring the distribution of airflow organization around the air outlet of the aircraft APU in a natural jet state, acquiring the maximum boundary of the airflow in three directions, providing a basis for selecting the diameter of an initial adjusting pipeline, giving the length of the initial adjusting pipeline, determining the tail gas amount which can be accommodated by the initial adjusting pipeline by the length of the initial adjusting pipeline, further determining the water spraying amount of a spraying and cooling mechanism, detecting whether the indoor environment is balanced under the driving condition of the APU by using a temperature sensor of the air outlet in a laboratory, a temperature sensor of the environment in the laboratory and a pressure sensor of the environment in the laboratory, further selecting the type of a fan meeting the requirement, ensuring the stability of the temperature and the pressure in the laboratory and ensuring the safety of the aircraft and testers; the method comprises the steps that in FLUENT software, the turning radius of a drainage pipeline and the smoothness degree of the interior of the pipeline are adjusted for multiple times, numerical calculation is carried out, the diameter of the drainage pipeline meeting the requirement of a pressure field is obtained, and whether tail gas is completely stored in an airplane APU exhaust device or not is checked, so that the size and the type selection of the airplane APU exhaust device are determined; the method provides a basis for the model selection design of the airplane APU exhaust system in the laboratory, saves material resources and manpower, solves the problem of driving the APU in the laboratory, and lays an important foundation for the development of climate tests in the laboratory.
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 (5)

1. The design method of the indoor aircraft APU exhaust system comprises a laboratory (6) for containing an aircraft (7) and aircraft APU exhaust equipment for outputting exhaust of the aircraft APU to the outside, wherein the aircraft APU exhaust equipment comprises an initial adjusting pipeline (1), a drainage pipeline (2), a butterfly valve (3) and a fan (4) which are sequentially connected, a spray cooler (5) is arranged on the initial adjusting pipeline (1), the spray cooler (5) comprises a plurality of spray cooling mechanisms which are uniformly arranged along the length direction of the initial adjusting pipeline (1), each spray cooling mechanism comprises a water supply pipe (5-2) arranged outside the initial adjusting pipeline (1) and a plurality of spray ring pipes (5-1) which are uniformly arranged on the inner wall of the initial adjusting pipeline (1) along the length direction of the initial adjusting pipeline (1), and the spray ring pipes (5-1) are uniformly arranged on the side wall of the initial adjusting pipeline (1) towards the inner center direction A plurality of water spray holes are uniformly formed;
the water supply pipe (5-2) is provided with an input pipe and a plurality of output pipes, the number of the output pipes on the water supply pipe (5-2) is equal to the number of the spray ring pipes (5-1) in the spray cooling mechanism and corresponds to one another, and the output pipes are provided with valves (5-3) and flow sensors (5-4);
an exhaust port temperature sensor (8) is arranged in the laboratory (6) at a position which is close to the 3m exhaust position of the airplane APU, and a laboratory environment temperature sensor (9) and a laboratory environment pressure sensor (10) are arranged in the laboratory (6) at a position which is in the non-working area of the airplane;
the initial adjusting pipeline (1) and the drainage pipeline (2) are both round pipes;
the method is characterized by comprising the following steps:
step one, determining the diameter of an initial adjusting pipeline: establishing three-dimensional models of the distribution of airflow structures at the air outlet of the aircraft APU and around the air outlet of the aircraft APU by using CATIA software, meshing the three-dimensional models in a mixed mesh form, introducing the three-dimensional models into FLUENT software, acquiring the distribution of the airflow structures around the air outlet of the aircraft APU in a natural jet state, and acquiring the maximum boundary of the airflow in three directions; calculating the diameter D of the initial adjusting pipeline according to a formula D = L + DeltaL, wherein L is the maximum boundary in the airflow jet width or height direction, and DeltaL is the boundary safety reserved value in the airflow jet width or height direction;
step two, setting the length of an initial adjusting pipeline: giving the length of an initial adjustment pipeline according to the distance between the air outlet of the aircraft APU and the side wall of the laboratory chamber opposite to the air outlet of the aircraft APU, wherein the initial adjustment pipeline (1) is a straight pipe, and the connection section of the drainage pipeline and the initial adjustment pipeline (1) is a straight pipe;
step three, determining the diameter of the drainage pipeline: setting the diameter of the drainage pipeline to be smaller than the diameter of the initial adjustment pipeline, inputting the diameter of the initial adjustment pipeline and the set diameter of the drainage pipeline in FLUENT software, and performing numerical calculation to obtain a pressure field in the drainage pipeline;
adjusting the turning radius of the drainage pipeline and the internal smoothness of the pipeline for multiple times in FLUENT software, and performing numerical calculation to obtain the diameter of the drainage pipeline meeting the requirement of a pressure field;
step four, judging whether the aircraft APU exhaust equipment completely stores tail gas: acquiring whether the tail gas is completely stored in the aircraft APU exhaust equipment in a natural jet state or not in FLUENT software by utilizing the determined initial adjusting pipeline diameter and the determined drainage pipeline diameter, and executing a fifth step when the tail gas can be completely stored in the aircraft APU exhaust equipment; when the tail gas can not be completely stored in the exhaust equipment of the aircraft APU, adjusting a boundary safety reserved value in the airflow jet width or height direction, and executing the second step and the third step until the tail gas can be completely stored in the exhaust equipment of the aircraft APU;
step five, fan type selection: the temperature of the position 3m outside the exhaust port of the airplane APU is collected in real time by using an exhaust port temperature sensor (8), and the environmental temperature in a laboratory is collected in real time by using a laboratory environmental temperature sensor (9);
gradually increasing the frequency of the fan (4), increasing and then reducing the temperature value at the position of the exhaust port temperature sensor (8) in the laboratory, wherein the temperature value at the position of the exhaust port temperature sensor (8) in the laboratory is the same as the temperature value at the position of the laboratory environment temperature sensor (9), the pressure at the position of the laboratory environment pressure sensor (10) in the laboratory meets the micro-positive pressure index, stopping adjusting the frequency of the fan (4), and selecting the fan type meeting the requirement;
step six, determining the water quality for spraying and coolingFlow rate: according to the formula
Figure 835317DEST_PATH_IMAGE001
Determining the mass flow of water for spraying and cooling
Figure 187801DEST_PATH_IMAGE002
Wherein, in the step (A),
Figure 130349DEST_PATH_IMAGE003
to initially adjust the mass flow rate of the gas stream in the duct,
Figure 568284DEST_PATH_IMAGE004
to initially adjust the average specific heat capacity of the air flow in the duct,
Figure 988901DEST_PATH_IMAGE005
to initially adjust the temperature of the air flow within the duct,
Figure 399154DEST_PATH_IMAGE006
the temperature is set for the safety of the tail gas emission,
Figure 512603DEST_PATH_IMAGE007
the percentage of water evaporation is used for spray cooling, the beta is the safety coefficient of water consumption,
Figure 437834DEST_PATH_IMAGE008
the specific heat capacity of water, delta T is the temperature variation of the water vapor changed from the initial temperature by the spraying cooling water, and delta Q is the specific latent heat of vaporization of the water;
seventhly, determining the number of the spraying cooling mechanisms: the number of the spraying and cooling mechanisms is determined according to the length of the initial adjusting pipeline, the number of the plurality of spraying and cooling mechanisms is uniformly distributed on the initial adjusting pipeline (1), and the number of the water spraying holes in each spraying ring pipe (5-1) is determined according to the mass flow of water for spraying and cooling, so that the mass flow of the water sprayed by the plurality of spraying and cooling mechanisms meets the requirement.
2. A design method for an APU exhaust system of a laboratory aircraft according to claim 1, wherein: the water consumption safety coefficient beta is 1.5-2.
3. A design method for an APU exhaust system of a laboratory aircraft according to claim 1, wherein: the micro-positive pressure index is 10 Pa-80 Pa.
4. A design method for an APU exhaust system of a laboratory aircraft according to claim 1, wherein: the safe set temperature of the exhaust emission
Figure 662142DEST_PATH_IMAGE006
Not more than 80 ℃.
5. A design method for an APU exhaust system of a laboratory aircraft according to claim 1, wherein: the water supply pipe (5-2) is a water supply pipe having one input pipe and two to four output pipes.
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