CN114486265A - Cold carrying system for aircraft extreme temperature test and parameter design method thereof - Google Patents

Cold carrying system for aircraft extreme temperature test and parameter design method thereof Download PDF

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CN114486265A
CN114486265A CN202210339074.2A CN202210339074A CN114486265A CN 114486265 A CN114486265 A CN 114486265A CN 202210339074 A CN202210339074 A CN 202210339074A CN 114486265 A CN114486265 A CN 114486265A
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tank
secondary refrigerant
heat exchanger
temperature
shunt
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CN114486265B (en
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任战鹏
徐健
田培强
王博言
张惠
吴敬涛
李玄
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AVIC Aircraft Strength Research Institute
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AVIC Aircraft Strength Research Institute
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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
    • 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
    • B64F5/60—Testing or inspecting aircraft components or systems
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25D—REFRIGERATORS; COLD ROOMS; ICE-BOXES; COOLING OR FREEZING APPARATUS NOT OTHERWISE PROVIDED FOR
    • F25D16/00—Devices using a combination of a cooling mode associated with refrigerating machinery with a cooling mode not associated with refrigerating machinery
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F25—REFRIGERATION OR COOLING; COMBINED HEATING AND REFRIGERATION SYSTEMS; HEAT PUMP SYSTEMS; MANUFACTURE OR STORAGE OF ICE; LIQUEFACTION SOLIDIFICATION OF GASES
    • F25D—REFRIGERATORS; COLD ROOMS; ICE-BOXES; COOLING OR FREEZING APPARATUS NOT OTHERWISE PROVIDED FOR
    • F25D17/00—Arrangements for circulating cooling fluids; Arrangements for circulating gas, e.g. air, within refrigerated spaces
    • F25D17/02—Arrangements for circulating cooling fluids; Arrangements for circulating gas, e.g. air, within refrigerated spaces for circulating liquids, e.g. brine
    • 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
    • G01M99/002—Thermal testing

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  • Combustion & Propulsion (AREA)
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  • General Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Testing Resistance To Weather, Investigating Materials By Mechanical Methods (AREA)

Abstract

The invention discloses a secondary cooling system for an aircraft extreme temperature test and a parameter design method thereof, belonging to the technical field of aircraft testing and comprising a secondary cooling tank set, a primary cooling zone and a secondary cooling zone, wherein the secondary cooling tank set comprises a first secondary cooling tank and a second secondary cooling tank which are arranged side by side from top to bottom, a heat insulation plate is arranged in the middle of the secondary cooling tank set between the first secondary cooling tank and the second secondary cooling tank, a temporary storage tank is arranged at the tail end of the secondary cooling tank set, and 4 groups of shunt tanks are symmetrically arranged in the temporary storage tank at the center. The parameter design method comprises the following steps: s1, wet air treatment; s2: carrying out secondary cooling treatment; s3, recycling the refrigerating medium; and S4, cleaning. The cold carrying system disclosed by the invention can be used for carrying out sectional cooling on externally input wet air through two kinds of cold carrying agents, can be used for efficiently cooling the air temperature to the required temperature, can be used for providing a large amount of dry air meeting the temperature requirement for a laboratory, and further meets the temperature requirement of an aeroengine test.

Description

Cold carrying system for aircraft extreme temperature test and parameter design method thereof
Technical Field
The invention relates to the technical field of airplane testing, in particular to a cold carrying system for airplane extreme temperature testing and a parameter design method thereof.
Background
In an aircraft environment test experiment, because an engine needs to consume a large amount of air and generate a large amount of heat during driving in a laboratory environment, an air compensation system in the laboratory is needed to provide external air to ensure that the pressure difference between the inside and the outside of the laboratory and the ambient temperature are normal, and the external air needs to be processed into low-temperature air through low temperature to enter the laboratory space. However, the conventional direct refrigeration or heating method for treating the outside air cannot meet the time requirement of the laboratory, and the secondary refrigerant is required to transfer cold or heat to the outside air transmitted in, so as to achieve the purpose of rapidly treating the outside air.
According to the requirement of the external air temperature of an engine environment experiment, namely the lowest-55 ℃ environment temperature, the secondary refrigerant needs to cool the normal-temperature external air to the required cold quantity and then transmits the cold quantity to a laboratory, and the conventional secondary refrigerant flow control or storage device is difficult to reduce the air temperature to-55 ℃ in a short time, so that the flow and storage device of the secondary refrigerant need to be improved to ensure that the environment temperature of the laboratory is controlled to be the required value, so that the secondary refrigerant flow control or storage device can accord with the extreme environment of an airplane environment test experiment.
Disclosure of Invention
Aiming at the problems, the invention provides a cold carrying system for an aircraft extreme temperature test and a parameter design method thereof.
The technical scheme of the invention is as follows:
a cold carrying system for testing extreme temperatures of an airplane comprises a secondary refrigerant tank set for providing secondary refrigerant, and a primary cooling area and a secondary cooling area which are respectively communicated with the secondary refrigerant tank set;
the secondary cooling area comprises a third heat exchanger for carrying out secondary cooling on dry air obtained by primary cooling;
the first secondary refrigerant tank is connected with the first heat exchanger and the second heat exchanger through a first pipeline respectively, a first valve is arranged at the joint of the first pipeline and the first heat exchanger, a second valve is arranged at the joint of the first pipeline and the second heat exchanger, outlet ends of the first heat exchanger and the second heat exchanger are connected with the third heat exchanger through a first air duct, the second secondary refrigerant tank is connected with the third heat exchanger through a second pipeline, and a second air duct is arranged at the outlet end of the third heat exchanger.
Furthermore, an air inlet pipe for inputting external air is arranged at the inlet end of the first heat exchanger and the inlet end of the second heat exchanger, a third valve is arranged at the joint of the air inlet pipe and the first heat exchanger, a fourth valve is arranged at the joint of the air inlet pipe and the second heat exchanger, first secondary refrigerant return pipes are arranged at the tail ends of the bottoms of the first heat exchanger and the second heat exchanger, and a second secondary refrigerant return pipe is arranged at the tail end of the bottom of the third heat exchanger. The used secondary refrigerant can be recycled through the first secondary refrigerant return pipe and the second secondary refrigerant return pipe, so that the secondary refrigerant can be reused.
Furthermore, the end of the second heat exchanger is provided with a third air duct connected with the first air duct, and the third air duct is provided with a fifth valve. When air with various temperatures needs to be provided for the experimental environment, the fifth valve can be opened to use the third air duct.
Further, a first secondary refrigerant tank and a second secondary refrigerant tank are arranged side by side from top to bottom, the middle of a secondary refrigerant tank group between the first secondary refrigerant tank and the second secondary refrigerant tank is provided with a heat insulation plate, the front ends of the first secondary refrigerant tank and the second secondary refrigerant tank are respectively provided with an input pipe for inputting secondary refrigerant, the tail end of the secondary refrigerant tank group is provided with a rotating shaft, the outer portion of the rotating shaft is provided with a temporary storage tank which is rotatably connected with the rotating shaft in a sleeved mode, the inner center of the temporary storage tank is symmetrically provided with 4 groups of shunt tanks which are respectively a first shunt tank, a second shunt tank, a third shunt tank and a fourth shunt tank. The laboratory work efficiency is improved by integrating the two secondary refrigerants in the same tank, and the temperature exchange of the two secondary refrigerants is avoided.
Furthermore, the tail end of the first secondary refrigerant tank is connected with a first shunt tank, the tail end of the second secondary refrigerant tank is connected with a second shunt tank, the front ends of the 4-component shunt tanks are respectively provided with a cover plate, the cover plates are in fit sealing with the front side wall of the temporary storage tank, the centers of the cover plates of the first shunt tank and the second shunt tank are provided with openings, the back surface of the first shunt tank is provided with a first branch pipe, the tail end of the first branch pipe is respectively connected with a third shunt tank and a first pipeline, the joint of the tail end of the first branch pipe and the third shunt tank is provided with a sixth valve, the first shunt tank is internally provided with a first temperature sensor, the first temperature sensor is electrically connected with a first controller arranged outside the first shunt tank, the first controller is used for controlling the opening and closing of the sixth valve, the back surface of the second shunt tank is provided with a second branch pipe, the tail end of the second branch pipe is respectively connected with the fourth shunt tank and the second pipeline, the joint of the tail end of the second branch pipe and the fourth shunt tank is provided with a seventh valve, and a second temperature sensor is arranged in the second shunt tank and electrically connected with a second controller arranged outside the second shunt tank, and the second controller is used for controlling the opening and closing of the seventh valve. Can carry out real time monitoring to the secondary refrigerant temperature through the setting of jar of keeping in, can shunt partly secondary refrigerant when the temperature does not reach operation requirement, avoid causing great deviation influence to the experimental result.
Furthermore, the outer side wall of the temporary storage tank is provided with a tooth socket, the bottom of the temporary storage tank is provided with a gear which is rotationally connected with the tooth socket in a meshing way, the gear is driven to rotate by a driving motor positioned on one side of the temporary storage tank, the front end of the second secondary refrigerant tank is provided with a push rod motor positioned on the upper part of the input pipe, the output end of the push rod motor penetrates through the second secondary refrigerant tank and is connected with a cleaning plate, the cleaning plate is connected with the inner wall of the second secondary refrigerant tank in a sliding way, the center of the upper end and the center of the lower end of the cleaning plate are both provided with a slide block, and the slide block is connected with the second secondary refrigerant tank, the spout sliding connection that the inner wall was equipped with down, the cleaning plate middle part is rotated and is equipped with the rotor plate, and the rotor plate front end is equipped with a plurality of water jets along its circumference, and the rotor plate rear end is equipped with the water storage disk, and rotor plate and water storage disk rotate in step, and the water storage disk rear end is rotated and is connected and be equipped with the steam pipeline, and the steam pipeline cover is established in the input tube and the steam pipeline can be dismantled. Can wash second secondary refrigerant jar and reposition of redundant personnel jar fast through the cleaning plate to realize the purpose of quick replacement secondary refrigerant and regular maintenance.
Preferably, the both sides of the slider below the cleaning plate are provided with idler wheels, a groove is formed in one side face, opposite to the water storage disc, of the slider below the cleaning plate, the outer wall of the water storage disc is in transmission connection with a belt pulley located in the groove through a group of belts, the idler wheels are embedded inside the sliding groove and can roll inside the sliding groove, the two groups of idler wheels are connected through a connecting rod penetrating through the slider and roll synchronously, a threaded connecting block is sleeved in the middle of the connecting rod, the upper portion of the threaded connecting block is in threaded rotation connection with a bevel gear, and a connecting shaft at the back of the bevel gear penetrates through the groove and then is connected with the middle of the belt pulley. The threaded connecting block and the bevel gear are driven to synchronously rotate through the movement of the sliding block to realize the rotation of the rotating plate, so that the inner wall of the tank is efficiently cleaned through the rotating water jet.
The invention also provides a parameter design method of the cold carrying system for the aircraft extreme temperature test, which comprises the following steps:
s1, wet air treatment: introducing wet air into the air inlet pipe, cooling through the first heat exchanger, wherein the wet air is changed into water vapor and dry air in the cooling process, and the mass of the water vapor is mWater (W)Dry air mass mDry matter；
S1-1, water vapor treatment: the LM-8 secondary refrigerant in the first secondary refrigerant tank provides cold energy to reduce the temperature of the water vapor to 0 ℃, and the required cold energy is Q1Then the water vapor is gradually liquefied into water, the heat released in the liquefaction process is absorbed by the low-temperature LM-8 refrigerating medium, and the required cold quantity is Q2The water is condensed into ice by continuously reducing the temperature, the heat released in the condensation process is absorbed by the low-temperature LM-8 secondary refrigerant, and the required cold quantity is Q3And the LM-8 secondary refrigerant continuously provides cold energy for heat exchange, the temperature of the ice is reduced to-25 ℃, and the required cold energy is Q4；
S1-2, dry air treatment: the LM-8 secondary refrigerant in the first secondary refrigerant tank provides cold energy to reduce the temperature of the dry air to-25 ℃, and the required cold energy is Q5To obtain saturated air with the temperature of-25 ℃,inputting the saturated air at the temperature of-25 ℃ into a third heat exchanger through a first air duct;
s1-3, LM-8 refrigerating medium volume flow calculation: according to the density rho of LM-8 secondary refrigerant when the secondary refrigerant is discharged from the tank0Specific heat C0Delta T of temperature difference between the tank and the tank0Calculating the volume flow V of the needed LM-8 refrigerating medium1：
Figure DEST_PATH_IMAGE002
S2: secondary cooling treatment: the CH-90 secondary refrigerant in the second secondary refrigerant tank provides cold energy to cool the saturated air at the temperature of-25 ℃ to-55 ℃ in the third heat exchanger, and the required cold energy is Q6；
And (3) calculating the volume flow of the S2-1 and CH-90 refrigerating medium: according to the density rho of the CH-90 secondary refrigerant when the secondary refrigerant is discharged from the tank1Specific heat C1Delta T of temperature difference between the tank and the tank1Calculating the volume flow V of the required CH-90 refrigerating medium2：
Figure DEST_PATH_IMAGE004
S2-2, calculating the total volume flow of the secondary refrigerant: according to the volume flow V of the LM-8 secondary refrigerant1Volume flow V of CH-90 secondary refrigerant2And calculating the total volume flow of the secondary refrigerant according to the number n of the secondary refrigerant tank groups, thereby obtaining the volume V of the required secondary refrigerant tank group:
Figure DEST_PATH_IMAGE006
s3, secondary refrigerant recovery: the secondary refrigerants flowing out of the first secondary refrigerant return pipe and the second secondary refrigerant return pipe are recycled and reused;
s4, cleaning: hot steam is introduced into the cleaning plate through a steam pipe line to clean the second secondary refrigerant tank, and meanwhile, the temporary storage tank is driven by the driving motor to enable the 4 component flow tanks to be sequentially butted with the tail end of the second secondary refrigerant tank so as to clean the 4 component flow tanks.
Further, the number n of the groups of the refrigerant tanks in the step S2-2 is 4 or 8. The convenience is put in the laboratory.
The invention has the beneficial effects that:
(1) the cold carrying system disclosed by the invention adopts two cold carrying agents, namely LM-8 and CH-90, to carry out sectional cooling on external wet air, can efficiently cool the air temperature to the required temperature, can provide a large amount of dry air meeting the temperature requirement for a laboratory, and further meets the temperature requirement of an aeroengine test.
(2) The secondary cooling system integrates the storage of two secondary refrigerants through the arrangement of the secondary refrigerant tank set, improves the working efficiency, can provide dry air for secondary cooling through the primary cooling area, can provide dry air with various temperatures so as to meet different temperature requirements of laboratory aeroengines, and has high operable space.
(3) The secondary cooling system can rapidly clean the second secondary refrigerant tank and each shunt tank through the cleaning plate, the threaded connecting block and the bevel gear are driven to synchronously rotate along with the sliding of the sliding block to realize the rotation of the rotating plate during cleaning, so that the inner wall of the tank is efficiently cleaned through the rotating water spraying port, the shunt tank and the second secondary refrigerant tank have the same inner diameter, the synchronous cleaning is conveniently completed, the secondary refrigerant in the second secondary refrigerant tank can be rapidly replaced by the secondary refrigerant which is the same as that in the first secondary refrigerant tank, and the efficiency of periodic maintenance can also be improved.
(4) The cold-carrying system can monitor the temperature of the secondary refrigerant in real time through the temperature sensor and the controller arranged in the shunting tank, and can shunt a part of the secondary refrigerant when the temperature does not meet the use requirement, so that the large deviation influence on the experimental result is avoided, and the shunted secondary refrigerant can be recycled after being recycled and cooled.
(5) The cold carrying system parameter design method is beneficial to strengthening the humidity control of the test by calculating the cold quantity required for removing the water vapor in the humid air and the sum of the cold quantities of the two cold carrying agents, is convenient to calculate the volume of each cold carrying agent tank, can ensure sufficient supply of the cold carrying agents and does not generate a large amount of stock, thereby avoiding unnecessary consumption.
Drawings
FIG. 1 is a schematic view of the overall structure of the cooling system of the present invention;
FIG. 2 is a side view of the cold carrier system of the present invention;
FIG. 3 is a schematic external structural view of a coolant tank cluster of the cold carrier system of the present invention;
FIG. 4 is a schematic top plan view and connection of the coolant tank cluster of the refrigeration system of the present invention;
FIG. 5 is a schematic diagram of the front side of the cleaning plate of the cooling system of the present invention;
FIG. 6 is a schematic view of the back side of the cleaning plate of the cooling system of the present invention;
FIG. 7 is a cross-sectional view of a second coolant tank of the cold carrier system of the present invention;
FIG. 8 is a schematic view of the internal structure of the roller and the slider cooperating therewith of the cooling system of the present invention;
FIG. 9 is a schematic front view of the internal distribution tank of the temporary storage tank of the cold-carrying system of the present invention;
FIG. 10 is a schematic view of the back side of the internal diversion tank of the temporary storage tank of the cold-carrying system of the present invention;
FIG. 11 is a schematic view of the internal structure of the diversion tank inside the temporary storage tank of the cold-carrying system of the present invention;
FIG. 12 is a process flow diagram of the design method of the parameters of the cooling system of the present invention.
Wherein, 1-refrigerating medium tank group, 11-first refrigerating medium tank, 12-second refrigerating medium tank, 121-chute, 13-first pipeline, 131-first valve, 132-second valve, 14-second pipeline, 15-thermal insulation plate, 16-input pipe, 17-rotating shaft, 2-primary cooling zone, 21-first heat exchanger, 22-second heat exchanger, 23-first air duct, 24-air inlet pipe, 241-third valve, 242-fourth valve, 25-first refrigerating medium return pipe, 26-third air duct, 261-fifth valve, 3-secondary cooling zone, 31-third heat exchanger, 32-second air duct, 33-second refrigerating medium return pipe, 4-temporary storage tank, 41-first shunt tank, 411-first temperature sensor, 412-first controller, 42-second split tank, 421-second temperature sensor, 422-second controller, 43-third split tank, 44-fourth split tank, 45-cover plate, 46-opening, 47-first branch pipe, 471-sixth valve, 48-second branch pipe, 481-seventh valve, 49-tooth space, 5-driving motor, 51-gear, 6-push rod motor, 7-cleaning plate, 71-slide block, 711-groove, 72-rotating plate, 73-water jet, 74-water storage disc, 75-steam pipeline, 76-roller, 77-belt, 78-connecting rod, 79-threaded connecting block, 8-belt pulley, 81-bevel gear, 82-connecting shaft.
Detailed Description
Example 1
As shown in fig. 1, a cold carrying system for testing extreme temperatures of an aircraft comprises a secondary refrigerant tank set 1 for providing secondary refrigerant, a primary cooling area 2 and a secondary cooling area 3 which are respectively communicated with the secondary refrigerant tank set 1;
as shown in fig. 2, the coolant tank group 1 includes a first coolant tank 11 and a second coolant tank 12, the primary cooling zone 2 includes a first heat exchanger 21 and a second heat exchanger 22 for cooling the external input air, and the secondary cooling zone 3 includes a third heat exchanger 31 for performing secondary cooling on the dry air obtained by the primary cooling;
as shown in fig. 1 and 2, the first coolant tank 11 is connected to the first heat exchanger 21 and the second heat exchanger 22 through a first pipeline 13, a first valve 131 is arranged at the joint of the first pipeline 13 and the first heat exchanger 21, a second valve 132 is arranged at the joint of the first pipeline 13 and the second heat exchanger 22, the outlet ends of the first heat exchanger 21 and the second heat exchanger 22 are connected to a third heat exchanger 31 through a first air duct 23, the second coolant tank 12 is connected to the third heat exchanger 31 through a second pipeline 14, a second air duct 32 is arranged at the outlet end of the third heat exchanger 31, an air inlet pipe 24 for inputting outside air is arranged at the inlet ends of the first heat exchanger 21 and the second heat exchanger 22, a third valve 241 is arranged at the joint of the air inlet pipe 24 and the first heat exchanger 21, a fourth valve 242 is arranged at the joint of the air inlet pipe 24 and the second heat exchanger 22, a first coolant return pipe 25 is arranged at the bottom ends of the first heat exchanger 21 and the second heat exchanger 22, the tail end of the bottom of the third heat exchanger 31 is provided with a second secondary refrigerant return pipe 33, the tail end of the second heat exchanger 22 is provided with a third air duct 26 connected with the first air duct 23, and the third air duct 26 is provided with a fifth valve 261;
as shown in fig. 3, 4, 9, 10, and 11, a first coolant tank 11 and a second coolant tank 12 are arranged side by side from top to bottom, a thermal insulation plate 15 is arranged in the middle of a coolant tank set 1 between the first coolant tank 11 and the second coolant tank 12, an input pipe 16 for inputting coolant is arranged at the front ends of the first coolant tank 11 and the second coolant tank 12, a rotating shaft 17 is arranged at the tail end of the coolant tank set 1, a temporary storage tank 4 rotatably connected with the rotating shaft 17 is sleeved outside the rotating shaft 17, 4 sets of shunt tanks are symmetrically arranged in the center of the interior of the temporary storage tank 4 and are respectively a first shunt tank 41, a second shunt tank 42, a third shunt tank 43, and a fourth shunt tank 44, the tail end of the first coolant tank 11 is connected with the first shunt tank 41, the tail end of the second coolant tank 12 is connected with the second shunt tank 42, a cover plate 45 is arranged at the front ends of the 4 sets of shunt tanks, the cover plate 45 is attached to and sealed with the front side wall of the temporary storage tank 4, an opening 46 is arranged at the center of the cover plate 45 of the first shunt tank 41 and the second shunt tank 42, a first branch pipe 47 is arranged on the back of the first shunt tank 41, the end of the first branch pipe 47 is respectively connected with the third shunt tank 43 and the first pipeline 13, a sixth valve 471 is arranged at the joint of the end of the first branch pipe 47 and the third shunt tank 43, a first temperature sensor 411 is arranged in the first shunt tank 41, the first temperature sensor 411 is electrically connected with a first controller 412 arranged outside the first shunt tank 41, the first controller 412 is used for controlling the opening and closing of the sixth valve 471, a second branch pipe 48 is arranged on the back of the second shunt tank 42, the end of the second branch pipe 48 is respectively connected with the fourth shunt tank 44 and the second pipeline 14, a seventh valve 481 is arranged at the joint of the end of the second branch pipe 48 and the fourth shunt tank 44, a second temperature sensor 421 is arranged in the second shunt tank 42, the second temperature sensor 421 is electrically connected with a second controller 422 arranged outside the second shunt tank 42, the second controller 422 is used for controlling the opening and closing of the seventh valve 481, the two groups of temperature sensors and controllers are all commercial products;
as shown in fig. 5-8, the outer side wall of the temporary storage tank 4 is provided with a tooth socket 49, the bottom of the temporary storage tank 4 is provided with a gear 51 which is in meshed rotary connection with the tooth socket 49, the gear 51 is driven to rotate by a driving motor 5 which is arranged at one side of the temporary storage tank 4, the driving motor 5 is a commercially available speed reducing motor, the front end of the second secondary refrigerant tank 12 is arranged at the upper part of the input pipe 16 and is provided with a push rod motor 6, the push rod motor 6 is a commercially available industrial push rod motor, the output end of the push rod motor 6 penetrates through the second secondary refrigerant tank 12 and is connected with a cleaning plate 7, the cleaning plate 7 is in sliding connection with the inner wall of the second secondary refrigerant tank 12, the upper end center and the lower end center of the cleaning plate 7 are both provided with a slider 71, the slider 71 is in sliding connection with a sliding groove 121 which is arranged on the upper inner wall and the lower inner wall of the second secondary refrigerant tank 12, the middle part of the cleaning plate 7 is rotatably provided with a rotating plate 72, the front end of which is provided with a plurality of water spray nozzles 73 along the circumference, the rear end of the rotating plate 72 is provided with a water storage disc 74, the rotating plate 72 and the water storage disc 74 rotate synchronously, a steam pipeline 75 is rotatably connected to the rear end of the water storage disc 74, the steam pipeline 75 is sleeved in the input pipe 16, the steam pipeline 75 can be detached, rollers 76 are arranged on two sides of a sliding block 71 below the cleaning plate 7, a groove 711 is formed in one side face, opposite to the water storage disc 74, of the sliding block 71 below the cleaning plate 7, the outer wall of the water storage disc 74 is in transmission connection with a belt pulley 8 located in the groove 711 through a group of belts 77, the rollers 76 are embedded in a sliding groove 121 and can roll in the sliding groove 121, the two groups of rollers 76 are connected through a connecting rod 78 penetrating through the sliding block 71 and roll synchronously, a threaded connecting block 79 is sleeved in the middle of the connecting rod 78, a bevel gear 81 is rotatably connected to the upper portion of the threaded connecting block 79 through threads, and a connecting shaft 82 on the back of the bevel gear 81 penetrates through the groove 711 and then is connected with the middle of the belt pulley 8.
The parameter design method of the cold carrying system for the aircraft extreme temperature test comprises the following steps:
s1, wet air treatment: introducing wet air into the air inlet pipe 24, cooling by the first heat exchanger 21, wherein the wet air is changed into water vapor and dry air in the cooling process, and the mass of the water vapor is mWater (W)Dry air mass mDry matter；
S1-1, water vapor treatment: the temperature of the vapor is reduced to 0 ℃ by the cold energy provided by the LM-8 secondary refrigerant in the first secondary refrigerant tank 11, and the required cold energy is Q1Then the water vapor is gradually liquefied into water, the heat released in the liquefaction process is absorbed by the low-temperature LM-8 refrigerating medium, and the required cold quantity is Q2The water is condensed into ice by continuously reducing the temperature, the heat released in the condensation process is absorbed by the low-temperature LM-8 secondary refrigerant, and the required cold quantity is Q3And the LM-8 secondary refrigerant continuously provides cold energy for heat exchange, the temperature of the ice is reduced to-25 ℃, and the required cold energy is Q4；
S1-2. Dry air treatment: the LM-8 secondary refrigerant in the first secondary refrigerant tank 11 provides cold energy to reduce the temperature of the dry air to-25 ℃, and the required cold energy is Q5To obtain saturated air at the temperature of-25 ℃, and then inputting the saturated air at the temperature of-25 ℃ into the third heat exchanger 31 through the first air duct 23;
s1-3, LM-8 refrigerating medium volume flow calculation: according to the density rho of LM-8 secondary refrigerant when the secondary refrigerant is discharged from the tank0Specific heat C0Delta T of temperature difference between the tank and the tank0Calculating the volume flow V of the needed LM-8 refrigerating medium1：
Figure DEST_PATH_IMAGE002A
S2: secondary cooling treatment: the CH-90 secondary refrigerant in the second secondary refrigerant tank 12 provides cold energy to cool the saturated air at the temperature of-25 ℃ to-55 ℃ in the third heat exchanger 31, and the required cold energy is Q6；
And (3) calculating the volume flow of the S2-1 and CH-90 refrigerating medium: according to the density rho of the CH-90 secondary refrigerant when the secondary refrigerant is discharged from the tank1Specific heat C1Delta T of temperature difference between the tank and the tank1Calculating the volume flow V of the required CH-90 refrigerating medium2：
Figure DEST_PATH_IMAGE004A
S2-2, calculating the total volume flow of the secondary refrigerant: the number n of the refrigerating medium tank groups 1 is 8 according to the volume flow V of LM-8 refrigerating medium1Volume flow V of CH-90 secondary refrigerant2And calculating the total volume flow of the secondary refrigerant according to the number n of the secondary refrigerant tank sets 1, thereby obtaining the volume V of the required secondary refrigerant tank set 1:
Figure DEST_PATH_IMAGE006A
s3, secondary refrigerant recovery: the secondary refrigerants flowing out of the first secondary refrigerant return pipe 25 and the second secondary refrigerant return pipe 33 are recycled after recovery treatment;
s4, cleaning: hot steam is introduced into the cleaning plate 7 through a steam pipeline 75 to clean the second secondary refrigerant tank 12, and meanwhile, the temporary storage tank 4 is driven by the driving motor 5 to enable the 4 groups of flow tanks to be sequentially butted with the tail end of the second secondary refrigerant tank 12 so as to clean the 4 groups of flow tanks.
Example 2
The present embodiment is different from embodiment 1 in that: the number n of the coolant tank groups 1 is 4.
The working principle is as follows: the working principle of the cooling system of the present invention will be briefly described below with reference to the parameter design method of the present invention.
When dry air at two different temperatures, such as-55 ℃ and-15 ℃, is required to be provided, the supply of dry air at-55 ℃ is completed by the method in steps S1 and S2, and the second valve 132, the fourth valve 242 and the fifth valve 261 are opened, a part of the coolant LM-8 is fed into the second heat exchanger 22 through the first pipe 13, the wet air therein is cooled to-15 ℃, and then discharged to the laboratory through the third air duct 26.
When the temperature of the secondary refrigerant is reduced, if the first temperature sensor 411 detects that the temperature of the secondary refrigerant LM-8 in the first shunting tank 41 is lower than the tank outlet temperature of-35 ℃, the sixth valve 471 is controlled to be opened by the first controller 412, and a part of the secondary refrigerant LM-8 is discharged into the third shunting tank 43, so that the flow of the secondary refrigerant LM-8 with the temperature not reaching the standard is reduced until the temperature of the secondary refrigerant LM-8 in the first shunting tank 41 is qualified; if the second temperature sensor 421 detects that the temperature of the coolant CH-90 in the second split tank 42 is lower than the outlet temperature of-63 ℃, the seventh valve 481 is controlled by the second controller 422 to open, a part of the coolant CH-90 is discharged into the fourth split tank 44, so as to reduce the flow of the coolant CH-90 with the temperature not up to the standard until the temperature of the coolant CH-90 in the second split tank 42 is up to the standard, and the coolant collected in the second split tank 42 and the fourth split tank 44 is recycled for reuse.
When the laboratory environment needs to be changed after the steps S1-S3 are completed, the required dry air is changed from-55 to-25 ℃, the second coolant supply is not needed, at this time, the interior of the second coolant tank 12 needs to be cleaned quickly to load the first coolant, the coolant in the second coolant tank 12 and each split-flow tank is firstly emptied, a steam pipeline 75 is installed on the back of the water storage disc 74, the push rod motor 6 is opened to push the cleaning plate 7 to slide along the interior of the second coolant tank 12, during the sliding process, the lower slider 71 drives the roller 76 to roll in the chute 121, meanwhile, the connecting rod 78 rotates to drive the threaded connecting block 79 to rotate, the bevel gear 81 meshed and connected with the connecting rod rotates to drive the belt pulley 8 to rotate through the connecting shaft 82, the water storage disc 74 is driven to synchronously rotate through the belt 77, so as to drive the rotating plate 72 to rotate, and the water spray nozzle 73 to realize rotary water spray cleaning, when the cleaning plate 7 moves to the end of the second secondary refrigerant tank 12, the cover plate 45 of the group of shunt tanks is taken down, the driving motor 5 is started to drive the gear 51 and the temporary storage tank 4 which are meshed with each other to rotate, the shunt tanks with the cover plates 45 taken down are rotated to be in butt joint with the second secondary refrigerant tank 12, then the cleaning plate 7 is moved to the inside of the shunt tanks to be cleaned, and the cleaning of the 4 shunt tanks is completed in sequence.
Examples of the experiments
Taking the parameters in example 1 as an example, the parameter design method of the present invention is simulated, and the results are as follows:
(1) volume flow V of LM-8 refrigerating medium1Computing
Given that after wet air at 35 ℃ is treated into saturated air at-25 ℃ by LM-8 coolant at-35 ℃, the temperature of the LM-8 coolant exiting the first heat exchanger 21 is-7.07 ℃, and the relevant parameters are calculated as shown in Table 1:
TABLE 1 LM-8 cold-carrying agent volume flow rate calculation essential parameter table
Parameter name Parameter value
Humid air to be treated The temperature is 35 DEG C
-25 ℃ saturated air Moisture content of d1=0.38g/kg
Latent heat of water to steam Q0=2257KJ/s
Heat of fusion of ice QFusion furnace=334.72KJ/s
Flow rate of air 200kg/s
Specific heat capacity of air C0=1.005KJ/s
Moisture content of 200kg/s of humid air d0=16.7g/kg
Calculating the volume V of the LM-8 refrigerating medium according to the basic parameters1The flow rate steps are as follows:
1) the moisture content in the humid air is:
Figure DEST_PATH_IMAGE008
2) the dry air content in the humid air is:
Figure DEST_PATH_IMAGE010
3) the cold quantity required by the water vapor from 35 ℃ to 0 ℃ is as follows:
Figure DEST_PATH_IMAGE012
4) the cold energy required for changing water vapor into water is as follows:
Figure DEST_PATH_IMAGE014
5) the latent heat of water to ice is:
Figure DEST_PATH_IMAGE016
6) the cooling capacity required for changing the temperature of ice from 0 ℃ to-25 ℃ is as follows:
Figure DEST_PATH_IMAGE018
7) the dry air is from 35 ℃ to-25 ℃, and the absorbed cold energy is as follows:
Figure DEST_PATH_IMAGE020
the total cold absorbed by the air from 35 ℃ to-25 ℃ is:
Figure DEST_PATH_IMAGE022
the density of the LM-8 refrigerating medium at-35 ℃ is rho0=1378kg/m3The specific heat is:
Figure DEST_PATH_IMAGE024
the temperature difference between the LM-8 secondary refrigerant entering and exiting the first heat exchanger 21 is as follows:
Figure DEST_PATH_IMAGE026
volume flow V of LM-8 secondary refrigerant1Comprises the following steps:
Figure DEST_PATH_IMAGE028
(2) volume flow V of CH-90 secondary refrigerant2And (3) calculating:
it is known that after-63 ℃ saturated air is treated with-25 ℃ CH-90 coolant to-55 ℃, the temperature of the CH-90 coolant exiting the third heat exchanger 31 is-41.96 ℃.
1) The flow rate of air was 200kg/s and the temperature difference before and after the air was treated was
55-25=30℃
2) The cold energy required for treating air is:
Figure DEST_PATH_IMAGE030
3) the density of the CH-90 refrigerating medium at the temperature of minus 63 ℃ is rho1=1487kg/m3
4) Specific heat C of CH-90 secondary refrigerant at-63 DEG C1=0.903KJ/（kgK）
5) The temperature difference between the CH-90 secondary refrigerant before and after air treatment is as follows:
Figure DEST_PATH_IMAGE032
6) volume flow V of CH-90 secondary refrigerant2：
Figure DEST_PATH_IMAGE034
(3) Refrigerant tank set 1 sizing
The coolant tank cluster 1 was designed to provide 20 minutes of testing requirements, assuming only 90% of the coolant in the cluster 1 is available for testing due to incomplete stratification and inlet and outlet disturbances, and the other 10% offsets the energy losses due to startup, pumps, fans, and plumbing fixtures.
The design flow of the LM-8 coolant is 211.93L/s, and the required volume of the LM-8 coolant is:
Figure DEST_PATH_IMAGE036
4 first coolant tanks 11, each first coolant tank 11 having a volume of 305.18/4=76.29m3。
The design flow rate of the CH-90 coolant is 213.4L/s, and the required volume of the CH-90 coolant is as follows:
Figure DEST_PATH_IMAGE038
4 second coolant tanks 12, each second coolant tank 12 having a volume of 307.29/4=76.82m3。
The volume of each coolant tank group 1 is 76.29+76.82=153.11m3。
If the air supplement amount required by the engine start test of the environmental laboratory is 400kg/s, the number of the first refrigerating medium tanks 11 of the LM-8 refrigerating medium of the laboratory is 8, and each tank has the volume of 78m3(ii) a The number of the second coolant tanks 12 of the CH-90 coolant is 8, and each tank has a capacity of 78m3(ii) a Each coolant tank group 1 has a volume of 78 × 2=156m3。

Claims (9)

1. A cold carrying system for testing extreme temperatures of an airplane is characterized by comprising a secondary refrigerant tank set (1) for providing secondary refrigerant, and a primary cooling area (2) and a secondary cooling area (3) which are respectively communicated with the secondary refrigerant tank set (1);
the secondary cooling area (3) comprises a third heat exchanger (31) for carrying out secondary cooling on dry air obtained by primary cooling;
the first secondary refrigerant tank (11) is connected with the first heat exchanger (21) and the second heat exchanger (22) through a first pipeline (13), a first valve (131) is arranged at the joint of the first pipeline (13) and the first heat exchanger (21), a second valve (132) is arranged at the joint of the first pipeline (13) and the second heat exchanger (22), outlet ends of the first heat exchanger (21) and the second heat exchanger (22) are connected with the third heat exchanger (31) through a first air guide pipe (23), the second secondary refrigerant tank (12) is connected with the third heat exchanger (31) through a second pipeline (14), and an outlet end of the third heat exchanger (31) is provided with a second air guide pipe (32).
2. The cold carrier system for aircraft extreme temperature tests according to claim 1, wherein an inlet pipe (24) for inputting external air is arranged at the inlet ends of the first heat exchanger (21) and the second heat exchanger (22), a third valve (241) is arranged at the joint of the inlet pipe (24) and the first heat exchanger (21), a fourth valve (242) is arranged at the joint of the inlet pipe (24) and the second heat exchanger (22), a first secondary refrigerant return pipe (25) is arranged at the bottom tail end of the first heat exchanger (21) and the second heat exchanger (22), and a second secondary refrigerant return pipe (33) is arranged at the bottom tail end of the third heat exchanger (31).
3. The aircraft extreme temperature test cold carrying system according to claim 1, wherein a third air duct (26) connected with the first air duct (23) is arranged at the tail end of the second heat exchanger (22), and a fifth valve (261) is arranged on the third air duct (26).
4. The cold-carrying system for the aircraft extreme temperature test according to claim 1, wherein the first secondary refrigerant tank (11) and the second secondary refrigerant tank (12) are arranged side by side from top to bottom, a heat insulation plate (15) is arranged in the middle of a secondary refrigerant tank set (1) between the first secondary refrigerant tank (11) and the second secondary refrigerant tank (12), an input pipe (16) for inputting secondary refrigerant is arranged at each of the front ends of the first secondary refrigerant tank (11) and the second secondary refrigerant tank (12), a rotating shaft (17) is arranged at the tail end of the secondary refrigerant tank set (1), a temporary storage tank (4) rotatably connected with the rotating shaft (17) is sleeved outside the rotating shaft (17), and 4 sets of flow distribution tanks are symmetrically arranged in the center inside of the temporary storage tank (4) and are respectively a first flow distribution tank (41), a second flow distribution tank (42), a third flow distribution tank (43) and a fourth flow distribution tank (44).
5. The cold-carrying system for the aircraft extreme temperature test according to claim 4, wherein the end of the first secondary refrigerant tank (11) is connected with the first shunt tank (41), the end of the second secondary refrigerant tank (12) is connected with the second shunt tank (42), the front ends of the 4-component shunt tanks are respectively provided with a cover plate (45), the cover plates (45) are in fit sealing with the front side wall of the temporary storage tank (4), the centers of the cover plates (45) of the first shunt tank (41) and the second shunt tank (42) are provided with an opening (46), the back of the first shunt tank (41) is provided with a first branch pipe (47), the ends of the first branch pipes (47) are respectively connected with the third shunt tank (43) and the first pipeline (13), the joint of the ends of the first branch pipes (47) and the third shunt tank (43) is provided with a sixth valve (471), and a first temperature sensor (411) is arranged in the first shunt tank (41), the first temperature sensor (411) is electrically connected with a first controller (412) arranged outside the first shunt tank (41), the first controller (412) is used for controlling the opening and closing of the sixth valve (471), a second branch pipe (48) is arranged on the back face of the second shunt tank (42), the tail end of the second branch pipe (48) is respectively connected with the fourth shunt tank (44) and the second pipeline (14), a seventh valve (481) is arranged at the joint of the tail end of the second branch pipe (48) and the fourth shunt tank (44), a second temperature sensor (421) is arranged in the second shunt tank (42), the second temperature sensor (421) is electrically connected with a second controller (422) arranged outside the second shunt tank (42), and the second controller (422) is used for controlling the opening and closing of the seventh valve (481).
6. The cold-carrying system for the aircraft extreme temperature test according to claim 5, wherein a tooth socket (49) is arranged on the outer side wall of the temporary storage tank (4), a gear (51) in meshed rotary connection with the tooth socket (49) is arranged at the bottom of the temporary storage tank (4), the gear (51) is driven to rotate by a driving motor (5) located on one side of the temporary storage tank (4), a push rod motor (6) is arranged at the upper part of the input pipe (16) at the front end of the second secondary refrigerant tank (12), a cleaning plate (7) is connected to the output end of the push rod motor (6) after penetrating through the second secondary refrigerant tank (12), the cleaning plate (7) is in sliding connection with the inner wall of the second secondary refrigerant tank (12), sliders (71) are arranged at the upper end center and the lower end center of the cleaning plate (7), and the sliders (71) and the second secondary refrigerant tank (12) are connected with each other, Sliding chute (121) sliding connection that the inner wall was equipped with down, wash board (7) middle part and rotate and be equipped with rotor plate (72), rotor plate (72) front end is equipped with a plurality of water jets (73) along its circumference, and rotor plate (72) rear end is equipped with water storage disc (74), rotor plate (72) with water storage disc (74) rotate in step, and water storage disc (74) rear end rotates to be connected and is equipped with steam pipeline (75), steam pipeline (75) cover is established in input tube (16) and steam pipeline (75) can be dismantled.
7. The aircraft extreme temperature test cold carrying system as claimed in claim 6, wherein rollers (76) are arranged on two sides of a sliding block (71) below the cleaning plate (7), a groove (711) is formed in one side surface, opposite to the water storage disc (74), of the sliding block (71) below the cleaning plate (7), the outer wall of the water storage disc (74) is in transmission connection with a belt pulley (8) located in the groove (711) through a group of belts (77), the rollers (76) are embedded in the sliding groove (121) and can roll in the sliding groove (121), the two groups of rollers (76) are connected and synchronously roll through connecting rods (78) penetrating through the sliding block (71), a threaded connecting block (79) is sleeved in the middle of each connecting rod (78), a bevel gear (81) is rotatably connected to the upper portion of each threaded connecting block (79), and a connecting shaft (82) on the back of the bevel gear (81) penetrates through the groove (711) and then is connected with the middle of the belt pulley (8).
8. The method for designing the parameters of the cooling system for the aircraft extreme temperature test according to any one of claims 1 to 7, characterized by comprising the following steps:
s1, wet air treatment: introducing wet air into the air inlet pipe (24), cooling by the first heat exchanger (21), wherein the wet air is changed into water vapor and dry air in the cooling process, and the mass of the water vapor is mWater (W)Dry air mass mDry matter；
S1-1, water vapor treatment: the LM-8 secondary refrigerant in the first secondary refrigerant tank (11) provides cold energy to reduce the temperature of the vapor to 0 ℃, and the required cold energy is Q1Then the water vapor is gradually liquefied into water, the heat released in the liquefaction process is absorbed by the low-temperature LM-8 refrigerating medium, and the required cold quantity is Q2The water is condensed into ice by continuously reducing the temperature, the heat released in the condensation process is absorbed by the low-temperature LM-8 secondary refrigerant, and the required cold quantity is Q3And the LM-8 secondary refrigerant continuously provides cold energy for heat exchange, the temperature of the ice is reduced to-25 ℃, and the required cold energy is Q4；
S1-2, dry air treatment: the LM-8 secondary refrigerant in the first secondary refrigerant tank (11) provides cold energy to reduce the temperature of the dry air to-25 ℃, and the required cold energy is Q5Obtaining saturated air at the temperature of minus 25 ℃, and inputting the saturated air at the temperature of minus 25 ℃ into a third heat exchanger (31) through a first air duct (23);
s1-3, LM-8 refrigerating medium volume flow calculation: according to the density rho of LM-8 secondary refrigerant when the secondary refrigerant is discharged from the tank0Specific heat C0Delta T of temperature difference between the tank and the tank0Calculating the volume flow V1 of the needed LM-8 refrigerating medium:
Figure DEST_PATH_IMAGE001
s2: secondary cooling treatment: the CH-90 secondary refrigerant in the second secondary refrigerant tank (12) provides cold energy to cool the saturated air at the temperature of-25 ℃ to-55 ℃ in the third heat exchanger (31), and the required cold energy is Q6；
And (3) calculating the volume flow of the S2-1 and CH-90 refrigerating medium: according to the density rho of CH-90 secondary refrigerant when the secondary refrigerant is discharged from a tank1Specific heat C1Delta T of temperature difference between the tank and the tank1Calculation of the required CH-9Volume flow V of 0 secondary refrigerant2：
Figure 77603DEST_PATH_IMAGE002
S2-2, calculating the total volume flow of the secondary refrigerant: according to the volume flow V of the LM-8 secondary refrigerant1Volume flow V of CH-90 secondary refrigerant2And calculating the total volume flow of the secondary refrigerant according to the number n of the secondary refrigerant tank groups (1), thereby obtaining the volume V of the required secondary refrigerant tank group (1):
Figure DEST_PATH_IMAGE003
s3, secondary refrigerant recovery: the secondary refrigerants flowing out of the first secondary refrigerant return pipe (25) and the second secondary refrigerant return pipe (33) are recycled after recovery treatment;
s4, cleaning: hot steam is introduced into the cleaning plate (7) through a steam pipeline (75) to clean the second secondary refrigerant tank (12), and meanwhile, the temporary storage tank (4) is driven by the driving motor (5) to enable the 4 groups of flow tanks to be butted with the tail end of the second secondary refrigerant tank (12) successively so as to clean the 4 groups of flow tanks.
9. The method as claimed in claim 8, wherein the number n of the coolant tank groups (1) in step S2-2 is 4 or 8.
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