CN106769133A - A kind of the atomized water spray pilot system and its application method of test flight device hot junction portion structure part thermal shock resistance - Google Patents
A kind of the atomized water spray pilot system and its application method of test flight device hot junction portion structure part thermal shock resistance Download PDFInfo
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- CN106769133A CN106769133A CN201611096987.7A CN201611096987A CN106769133A CN 106769133 A CN106769133 A CN 106769133A CN 201611096987 A CN201611096987 A CN 201611096987A CN 106769133 A CN106769133 A CN 106769133A
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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- G01M99/002—Thermal testing
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Abstract
A kind of the atomized water spray pilot system and its application method of test flight device hot junction portion structure part thermal shock resistance, are related to the pilot system and its application method of hot junction portion structure part thermal shock resistance.Solve the problems, such as that the thermal shock resistance wire examination method of existing aircraft hot junction portion structure part is not enough.Pilot system includes heating device of muffle furnace, hydraulic test stage apparatus, atomized water spray fast cooling device, hot junction portion structure part clamping tooling, frock mobile bar and temperature measuring equipment；Method：First, thermocouple is placed in ceramic protecting pipe, is fixed on the portion structure part of aircraft hot junction, connect electric wire connecting junction and data collecting instrument；2nd, fastening clips are connected with base, then will be pasted with pyrometer fire-end portion structure part and be placed in fastening clips, be subsequently placed on locating slot, adjusting position；3rd, hot junction portion structure part is heated, taking-up is placed on locating slot, and atomized water spray thermal shock simultaneously measures temperature lowering curve；4th, observation macroscopic cracking judges whether structural member fails.
Description
Technical field
The present invention relates to the pilot system and its application method of hot junction portion structure part thermal shock resistance.
Background technology
The thermal shock resistance of hot junction portion structure part is the important indicator of vehicle reliability, its reliability direct relation
To the safety of whole aerocraft system.Carrying out examination to the thermal shock resistance of hot junction portion structure part can effectively instruct heat
The optimization design of end bit architecture part material and hot junction portion structure part.
The thermal shock resistance of hot junction portion structure part can be examined by wind tunnel test, but wind-tunnel checking system is non-
It is often complicated and cost is high, therefore the only a few countries such as the U.S., Russia, France and China possess this kind equipment.
The U.S. established the first in the world seat wind-tunnel in 1945, had then built large quantities of various again in the 1950's
The wind-tunnel of the Mach number 6 of the wind-tunnel of distribution form, such as NASA Langley Research Centers, No. 8 wind-tunnel of NSWC, Sang Diya National Laboratories
Room Ma=5,8,14 wind-tunnel and the B wind-tunnel (Ma=6,8) in Feng's AEDC toll bar laboratory and C wind-tunnel (Ma=4,8,10) etc..
Russia has also built up large quantities of wind-tunnel, the T-116 wind-tunnel (Ma=1.8~10) of such as TSAGI, U- from the fifties
U-306-3 wind-tunnel (Ma=2~10) of 12 wind-tunnel (Ma=4~10) and center air mechanical investigations institute etc..
Europe and Japan greatly develop from the sixties and have built up a collection of wind-tunnel, such as：S4-MA (the Ma=of French ONERA
6,10,12), the H2K (Ma=4.5~11.2) of Germany DLR, the Mach number of Japanese national NAL (NAL)
5,7,9,11 wind-tunnel.
Domestic wind-tunnel mainly has the FD-20A (Ma=4~8) and FL-31 (Ma=5~11.7), the FD- of CAAA of CARDC
NHW (Ma=5~8) of 07 (Ma=5~12) and NUAA etc..
Although wind-tunnel can accurately simulate hot junction portion structure part under arms under the conditions of true environment, due to
The complexity of such system causes switching and debugging between different test modes extremely complex, less efficient and during examination
Easily there is the damage of the parts such as frock and cause examination to be interrupted.
Quenching method is used as a kind of the most commonly used research material and the method for part thermal shock resistance, although with operation
Simply, advantage with low cost, but its thermal shock environments is larger with the true environment difference of aircraft hot junction portion structure part, and
Examination state can only be adjusted by changing hardening media species and medium temperature in a small range.
Therefore in the urgent need to condition close to aircraft hot junction portion structure part true environment, examination ring is examined in a kind of thermal shock
Border is adjustable on a large scale, test method simple to operate and with low cost.
The content of the invention
It is an object of the invention to provide a kind of atomized water spray examination of test flight device hot junction portion structure part thermal shock resistance
Check system and its application method；Not enough with the thermal shock resistance wire examination method for solving existing aircraft hot junction portion structure part
Problem.
A kind of atomized water spray pilot system of test flight device hot junction portion structure part thermal shock resistance adds including Muffle furnace
Thermal, hydraulic test stage apparatus, atomized water spray fast cooling device, hot junction portion structure part clamping tooling, frock mobile bar
And temperature measuring equipment；
Described hydraulic test stage apparatus include objective table and spray gun secured adjusted bar；
Described atomized water spray fast cooling device includes airless sprayer, spray gun and water tank；
Described hot junction portion structure part clamping tooling includes base, support and fastening clips；
Described temperature measuring equipment includes thermocouple, ceramic protecting pipe, electric wire connecting junction and data collecting instrument；
Heating device of muffle furnace reclines with objective table, and heating device of muffle furnace fire door lower edge is higher than objective table upper table
Face, objective table upper surface is provided with spray gun secured adjusted bar and locating slot, and spray gun secured adjusted bar is provided with spray gun, and spray gun is by height
Pressure flexible pipe is connected with airless sprayer, and airless sprayer is connected by water pipe with water tank；And the nozzle center of spray gun with fly
Row device hot junction portion structure part front end center keeps level；Wherein, the nozzle of spray gun and aircraft hot junction portion structure part front end
Distance ensure that water smoke uniform fold hot junction portion structure part；
Locating slot is provided with base, and base upper surface is connected by support with the lower surface of fastening clips, frock mobile bar
Coordinate with base gap, fastening clips are provided with aircraft hot junction portion structure part, and thermocouple is fixed on aircraft hot junction position
Structural member surface or inside, thermocouple are externally provided with ceramic protecting pipe, and thermocouple afterbody both positive and negative polarity is connected with electric wire connecting junction, and electric wire connecting junction leads to
Data wire is crossed to be connected with data collecting instrument.
A kind of application method of the atomized water spray pilot system of test flight device hot junction portion structure part thermal shock resistance, be
Carry out according to the following steps：
First, thermocouple is placed in ceramic protecting pipe, and aircraft hot junction portion structure part is fixed on by high-temp glue
Surface or inside, are stood after after thermocouple fixation, and then thermocouple afterbody both positive and negative polarity is connected with electric wire connecting junction, and electric wire connecting junction is again
It is connected with data collecting instrument by data wire, obtains being pasted with the aircraft hot junction portion structure part of thermocouple；
2nd, fastening clips lower surface is connected and is fixed with base upper surface by support, then will be pasted with thermocouple
Aircraft hot junction portion structure part be placed in fastening clips clamp, obtain being pasted with the folder of the hot junction portion structure part of thermocouple
Frock is held, the clamping tooling that will be pasted with the hot junction portion structure part of thermocouple is placed on locating slot, in the nozzle of regulation spray gun
The heart keeps level with aircraft hot junction portion structure part front end center, adjusts the nozzle and aircraft hot junction portion structure part of spray gun
Front end distance, to water is added in water tank, opens airless sprayer and spray gun, adjusts irrigation pressure, from top surface and side observation simultaneously
Ensure aircraft hot junction portion structure part by water smoke uniform fold；
3rd, the clamping tooling of the hot junction portion structure part for being pasted with thermocouple is removed from locating slot, and heat will be pasted with
The clamping tooling of the hot junction portion structure part of galvanic couple is placed in heating device of muffle furnace and heats and by temperature measuring equipment thermometric, control
Heating rate is less than 30 DEG C/min, and the clamping tooling for being equipped with hot junction portion structure part after being heated after heating, opens horse
Not the fire door of stove heat device, frock mobile bar and base gap is coordinated and is installed, and using frock mobile bar by after heating
The clamping tooling for being equipped with hot junction portion structure part is placed on locating slot, opens spray gun, starts atomized water spray thermal shock and by surveying
Warm device thermometric, atomized water spray is stopped after hot junction portion structure part is cooled down completely；And from utilization frock mobile bar by after heating
Be equipped with hot junction portion structure part clamping tooling be placed in locating slot up to start time used by atomized water spray thermal shock for 2s~
3s；
4th, after atomized water spray thermal shock terminates, aircraft hot junction portion structure part is removed from fastening clips, is dried,
The slabbing line developer of aircraft hot junction portion structure part surface even application one, stands 1min~3min, and then crackle develops
Agent is cleaned up and stood, and waits crackle to observe crack morphology after manifesting, that is, complete a kind of test flight device hot junction portion structure
The application method of the atomized water spray pilot system of part thermal shock resistance.
The beneficial effects of the invention are as follows：Compared with the high wind tunnel test of existing complexity, test flight of the present invention
The atomized water spray pilot system and application method of device hot junction portion structure part thermal shock resistance have miniaturization, low cost, Gao Ke
By property, it is easy to operate the advantages of, it is adaptable to the research of different shape and size hot junction portion structure part thermal shock resistance.Using this
Invention, can simulated flight device hot junction portion structure part under arms under the conditions of adverse circumstances when being subjected to thermal shock, and examination ring
Border can regulate and control in a wider context compared to wind-tunnel method.Additionally, using the destruction side of hot junction portion structure part after the method examination
Formula is coincide with the actual wind-tunnel result of appraisal.
The present invention for a kind of test flight device hot junction portion structure part thermal shock resistance atomized water spray pilot system and
Its application method.
Brief description of the drawings
Fig. 1 is a kind of atomized water spray pilot system of test flight device hot junction portion structure part thermal shock resistance of the invention
Structural representation；
Fig. 2 is that the length-width ratio of embodiment one is 1:The crack morphology figure of upper surface after 1 nose of wing structural member thermal shock；
Fig. 3 is that the length-width ratio of embodiment one is 1:The crack morphology figure of lower surface after 1 nose of wing structural member thermal shock；
Fig. 4 is that the length-width ratio of embodiment two is 1:The crack morphology figure of upper surface after 2 nose of wing structural member thermal shock；
Fig. 5 is that the length-width ratio of embodiment two is 1:The crack morphology figure of lower surface after 2 nose of wing structural member thermal shock；
Fig. 6 is that the length-width ratio of embodiment one is 1:Thermocouple diverse location schematic diagram on 1 nose of wing structural member；Point 1~6
For thermocouple is located at nose of wing structural member surface position, point 7 is that thermocouple is located at nose of wing structural member interior location；
Fig. 7 is that the length-width ratio of embodiment one is 1:The drop of diverse location during 1 nose of wing structural member atomized water spray thermal shock
Warm curve map；
Fig. 8 is the A areas enlarged drawing of Fig. 7, and 1 is the temperature lowering curve figure of the position of Fig. 6 midpoints 1, and 2 is the cooling of the position of Fig. 6 midpoints 2
Curve map, 3 is the temperature lowering curve figure of the position of Fig. 6 midpoints 3, and 4 is the temperature lowering curve figure of the position of Fig. 6 midpoints 4, and 5 is 5, Fig. 6 midpoints
The temperature lowering curve figure put, 6 is the temperature lowering curve figure of the position of Fig. 6 midpoints 6, and 7 is the temperature lowering curve figure of the position of Fig. 6 midpoints 7.
Specific embodiment
Technical solution of the present invention is not limited to the specific embodiment of act set forth below, also including each specific embodiment it
Between any combination.
Specific embodiment one：Present embodiment is illustrated with reference to Fig. 1.A kind of test flight of present embodiment
The atomized water spray pilot system of device hot junction portion structure part thermal shock resistance includes heating device of muffle furnace 1, hydraulic test platform
Device, atomized water spray fast cooling device, hot junction portion structure part clamping tooling, frock mobile bar 11 and temperature measuring equipment；
Described hydraulic test stage apparatus include objective table 2 and spray gun secured adjusted bar 3；
Described atomized water spray fast cooling device includes airless sprayer 5, spray gun 6 and water tank 7；
Described hot junction portion structure part clamping tooling includes base 8, support 9 and fastening clips 10；
Described temperature measuring equipment includes thermocouple 14, ceramic protecting pipe 15, electric wire connecting junction 16 and data collecting instrument 17；
Heating device of muffle furnace 1 reclines with objective table 2, and the fire door lower edge of heating device of muffle furnace 1 is higher than on objective table 2
Surface, the upper surface of objective table 2 is provided with spray gun secured adjusted bar 3 and locating slot 4, and spray gun secured adjusted bar 3 is provided with spray gun 6, spray
Rifle 6 is connected by high-pressure hose with airless sprayer 5, and airless sprayer 5 is connected by water pipe with water tank 7；And spray gun 6
Nozzle center keeps level with aircraft hot junction portion structure part front end center；Wherein, the nozzle of spray gun 6 and aircraft hot junction portion
Bit architecture part front end distance ensure that water smoke uniform fold hot junction portion structure part；
Locating slot 4 is provided with base 8, and the upper surface of base 8 is connected by support 9 with the lower surface of fastening clips 10, frock
Mobile bar 11 coordinates with the gap of base 8, and fastening clips 10 are provided with aircraft hot junction portion structure part, and thermocouple 14 is fixed on winged
Row device hot junction portion structure part surface or inside, thermocouple 14 are externally provided with ceramic protecting pipe 15, the afterbody both positive and negative polarity of thermocouple 14 with
Electric wire connecting junction 16 is connected, and electric wire connecting junction 16 is connected by data wire with data collecting instrument 17.
This specific embodiment heating device of muffle furnace 1 is abutted with objective table 2, for uniformly and quickly heating test examination
Sample, the fire door lower surface of heating device of muffle furnace 1 is slightly above the upper surface of objective table 2, smooth to ensure fire door ON/OFF；
Described hot junction portion structure part clamping tooling, for clamping hot junction portion structure part to be examined, leads to after heating
Cross the frock mobile bar 11 to remove heating device of muffle furnace 1 and be placed on locating slot 4, entered by hydraulic test stage apparatus
Row positioning；
Described temperature measuring equipment is connected with aircraft hot junction portion structure part, for measuring hot junction position during thermal shock
The temperature variations of structural member.The temperature that data collecting instrument 17 is used to record and store hot junction portion structure part diverse location becomes
Change data.
Spray gun secured adjusted bar 3 can adjust the position in the horizontal and vertical directions of spray gun 6, it is ensured that hot junction portion structure
Part is in the middle of uniform range of atomization；
The nozzle and aircraft hot junction portion structure part front end distance of spray gun 6 are adjusted, according to aircraft hot junction portion structure
The size and dimension of part is reasonably adjusted, it is ensured that water smoke uniform fold aircraft hot junction portion structure part；
Described locating slot 4 is embedded in objective table 2, for the positioning of hot junction portion structure part clamping tooling.
Described airless sprayer 5 is connected with spray gun 6 by high-pressure hose, is pressurized water using plunger displacement pump, obtains high pressure
Water spray gun 6 is transported to by high-pressure hose, via spray gun 6 nozzle discharge pressure, the water under high pressure that airless sprayer 5 is conveyed
Uniform range of atomization is formed, and the nozzle center of spray gun 6 keeps level, regulation with aircraft hot junction portion structure part front end center
The nozzle of spray gun 6 and aircraft hot junction portion structure part front end distance, to ensure the uniform of water smoke around the portion structure part of hot junction
Property, nozzle can be changed according to structural member cross sectional shape.
Described base 8 is connected with support 9, as be reused in firm hot junction portion structure part and facilitate hot junction position tie
The quick mobile and positioning of component；
Described support 9 is connected with base 8 and fastening clips 10, provides empty for the placement to hot junction portion structure part
Between, the fastening clips 10 are used to fasten part to be tested, and the size of fastening clips 10 can be changed according to testpieces size.
Described frock mobile bar 11 coordinates with the gap of base 8, facilitates the rapid assembly or disassembly of frock mobile bar 11.
Thermocouple 14 is fixed on aircraft hot junction portion structure part surface or inside, and thermocouple 14 is externally provided with ceramic protecting pipe
15, ceramic protecting pipe 15 can anti-thermocouple 14 there is short trouble when being heated in heating device of muffle furnace 1.
The operation principle of this specific embodiment：By airless sprayer 5 combine nozzle of different shapes manufacture it is uniform and
The thermal shock environments that the water smoke environmental simulation aircraft hot junction portion structure part of controlled shape is subjected to, by heating device of muffle furnace
The 1 uniform heating for realizing hot junction portion structure part, the locating slot 4 in frock mobile bar 11 and hydraulic test stage apparatus is real respectively
Show the rapid taking-up of hot junction portion structure part and be accurately positioned, the macroscopic view on hot junction portion structure part surface after observing thermal shock
Crackle judges whether it fails, using dichotomy design examination temperature so as to approach certain material and size hot junction position rapidly
The critical slope langth temperature of structural member, is carried out by temperature measuring equipment to the temperature lowering curve of portion structure part in hot junction at a temperature of critical slope langth
Accurately determine so as to obtain the use border of the hot junction portion structure part under thermal shock environments.
The beneficial effect of this specific embodiment：Compared with the high wind tunnel test of existing complexity, this specific embodiment
The atomized water spray pilot system and application method of described test flight device hot junction portion structure part thermal shock resistance have small-sized
Change, low cost, high reliability, it is easy to operate the advantages of, it is adaptable to different shape and size hot junction portion structure part thermal-shock resistance
The research of energy.Using this specific embodiment, can simulated flight device hot junction portion structure part under arms under the conditions of be subjected to hot punching
Adverse circumstances when hitting, and examination environment can regulate and control in a wider context compared to wind-tunnel method.Additionally, after being examined using the method
The failure mode of hot junction portion structure part coincide with the actual wind-tunnel result of appraisal.
Specific embodiment two：Present embodiment from unlike specific embodiment one：Described thermocouple 14 is K-type
Thermocouple.Other are identical with specific embodiment one.
Specific embodiment three：Unlike one of present embodiment and specific embodiment one or two：When described flies
When row device hot junction portion structure part is flat nose of wing structural member, the nozzle of spray gun 6 can use rectangle.Other and specific implementation
Mode one or two is identical.
Specific embodiment four：Unlike one of present embodiment and specific embodiment one to three：When described flies
When row device hot junction portion structure part is circular Nose structure part, the nozzle of spray gun 6 can be using circle.Other and specific embodiment party
Formula one to three is identical.
Specific embodiment five：A kind of test flight device hot junction portion structure part thermal shock resistance of present embodiment
The application method of atomized water spray pilot system, is carried out according to the following steps：
First, thermocouple 14 is placed in ceramic protecting pipe 15, and aircraft hot junction portion structure is fixed on by high-temp glue
The surface or inside of part, stand after after the fixation of thermocouple 14, then connect the afterbody both positive and negative polarity of thermocouple 14 and electric wire connecting junction 16
Connect, electric wire connecting junction 16 is connected by data wire with data collecting instrument 17 again, obtain being pasted with the aircraft hot junction portion of thermocouple 14
Bit architecture part；
2nd, the lower surface of fastening clips 10 is connected and fixed with the upper surface of base 8 by support 9, then will be pasted with heat
The aircraft hot junction portion structure part of galvanic couple 14 is placed in fastening clips 10 and clamps, and obtains being pasted with the hot junction position of thermocouple 14
The clamping tooling of structural member, the clamping tooling that will be pasted with the hot junction portion structure part of thermocouple 14 is placed on locating slot 4, regulation
The nozzle center of spray gun 6 keeps level with aircraft hot junction portion structure part front end center, adjusts the nozzle and aircraft of spray gun 6
Hot junction portion structure part front end distance, to water is added in water tank 7, opens airless sprayer 5 and spray gun 6, adjusts irrigation pressure, from
Top surface and side are observed and ensure aircraft hot junction portion structure part by water smoke uniform fold；
3rd, the clamping tooling of the hot junction portion structure part for being pasted with thermocouple 14 is removed from locating slot 4, and will be pasted with
The clamping tooling of the hot junction portion structure part of thermocouple 14 is placed in heating device of muffle furnace 1 and heats and surveyed by temperature measuring equipment
Temperature, control heating rate is less than 30 DEG C/min, the clamping tooling for being equipped with hot junction portion structure part after being heated, heating
Afterwards, the fire door of heating device of muffle furnace 1 is opened, frock mobile bar 11 and the gap of base 8 is coordinated and is installed, and using frock movement
Bar 11 by heating after the clamping tooling for being equipped with hot junction portion structure part be placed on locating slot 4, open spray gun 6, start water spray
Mist thermal shock simultaneously passes through temperature measuring equipment thermometric, and atomized water spray is stopped after hot junction portion structure part is cooled down completely；And from utilizing frock
Mobile bar 11 by heating after the clamping tooling for being equipped with hot junction portion structure part be placed in locating slot 4 up to start atomized water spray heat punching
The time used is hit for 2s~3s；
4th, after atomized water spray thermal shock terminates, aircraft hot junction portion structure part is removed from fastening clips 10, is dried,
The slabbing line developer of even application one on aircraft hot junction portion structure part surface, stands 1min~3min, then shows crackle
Shadow agent is cleaned up and stood, and waits crackle to observe crack morphology after manifesting, that is, complete a kind of test flight device hot junction position knot
The application method of the atomized water spray pilot system of component thermal shock resistance.
This specific embodiment control heating rate is less than 30 DEG C/min, it is ensured that the thermally equivalent of hot junction portion structure part；
The operation principle of this specific embodiment：By airless sprayer 5 combine nozzle of different shapes manufacture it is uniform and
The thermal shock environments that the water smoke environmental simulation aircraft hot junction portion structure part of controlled shape is subjected to, by heating device of muffle furnace
The 1 uniform heating for realizing hot junction portion structure part, the locating slot 4 in frock mobile bar 11 and hydraulic test stage apparatus is real respectively
Show the rapid taking-up of hot junction portion structure part and be accurately positioned, the macroscopic view on hot junction portion structure part surface after observing thermal shock
Crackle judges whether it fails, using dichotomy design examination temperature so as to approach certain material and size hot junction position rapidly
The critical slope langth temperature of structural member, is carried out by temperature measuring equipment to the temperature lowering curve of portion structure part in hot junction at a temperature of critical slope langth
Accurately determine so as to obtain the use border of the hot junction portion structure part under thermal shock environments.
The beneficial effect of this specific embodiment：Compared with the high wind tunnel test of existing complexity, this specific embodiment
The atomized water spray pilot system and application method of described test flight device hot junction portion structure part thermal shock resistance have small-sized
Change, low cost, high reliability, it is easy to operate the advantages of, it is adaptable to different shape and size hot junction portion structure part thermal-shock resistance
The research of energy.Using this specific embodiment, can simulated flight device hot junction portion structure part under arms under the conditions of be subjected to hot punching
Adverse circumstances when hitting, and examination environment can regulate and control in a wider context compared to wind-tunnel method.Additionally, after being examined using the method
The failure mode of hot junction portion structure part coincide with the actual wind-tunnel result of appraisal.
Specific embodiment six：Present embodiment from unlike specific embodiment five：Thermoelectricity described in step one
Even 14 is K-type thermocouple.Other are identical with specific embodiment five.
Specific embodiment seven：Unlike one of present embodiment and specific embodiment five or six：When in step one
When described aircraft hot junction portion structure part is flat nose of wing structural member, the nozzle of the spray gun 6 described in step 2 can
Using rectangle.Other are identical with specific embodiment five or six.
Specific embodiment eight：Unlike one of present embodiment and specific embodiment five to seven：When in step one
When described aircraft hot junction portion structure part is circular Nose structure part, the nozzle of the spray gun 6 described in step 2 can be adopted
With circle.Other are identical with specific embodiment five to seven.
Effect of the invention is verified using following examples：
Embodiment one：
A kind of atomized water spray pilot system of test flight device hot junction portion structure part thermal shock resistance adds including Muffle furnace
Thermal 1, hydraulic test stage apparatus, atomized water spray fast cooling device, hot junction portion structure part clamping tooling, frock mobile bar
11 and temperature measuring equipment；
Described hydraulic test stage apparatus include objective table 2 and spray gun secured adjusted bar 3；
Described atomized water spray fast cooling device includes airless sprayer 5, spray gun 6 and water tank 7；
Described hot junction portion structure part clamping tooling includes base 8, support 9 and fastening clips 10；
Described temperature measuring equipment includes thermocouple 14, ceramic protecting pipe 15, electric wire connecting junction 16 and data collecting instrument 17；
Heating device of muffle furnace 1 reclines with objective table 2, and the fire door lower edge of heating device of muffle furnace 1 is higher than on objective table 2
Surface, the upper surface of objective table 2 is provided with spray gun secured adjusted bar 3 and locating slot 4, and spray gun secured adjusted bar 3 is provided with spray gun 6, spray
Rifle 6 is connected by high-pressure hose with airless sprayer 5, and airless sprayer 5 is connected by water pipe with water tank 7；And spray gun 6
Nozzle center keeps level with aircraft hot junction portion structure part front end center；Wherein, the nozzle of spray gun 6 and aircraft hot junction portion
Bit architecture part front end distance is 20cm；
Locating slot 4 is provided with base 8, and the upper surface of base 8 is connected by support 9 with the lower surface of fastening clips 10, frock
Mobile bar 11 coordinates with the gap of base 8, and fastening clips 10 are provided with aircraft hot junction portion structure part, and thermocouple 14 is fixed on winged
Row device hot junction portion structure part surface or inside, thermocouple 14 are externally provided with ceramic protecting pipe 15, the afterbody both positive and negative polarity of thermocouple 14 with
Electric wire connecting junction 16 is connected, and electric wire connecting junction 16 is connected by data wire with data collecting instrument 17.
A kind of user of the atomized water spray pilot system of above-mentioned test flight device hot junction portion structure part thermal shock resistance
Method, is carried out according to the following steps：
First, thermocouple 14 is placed in ceramic protecting pipe 15, and aircraft hot junction portion structure is fixed on by high-temp glue
The surface or inside of part, stand after after the fixation of thermocouple 14, then connect the afterbody both positive and negative polarity of thermocouple 14 and electric wire connecting junction 16
Connect, electric wire connecting junction 16 is connected by data wire with data collecting instrument 17 again, obtain being pasted with the aircraft hot junction portion of thermocouple 14
Bit architecture part；
2nd, the lower surface of fastening clips 10 is connected and fixed with the upper surface of base 8 by support 9, then will be pasted with heat
The aircraft hot junction portion structure part of galvanic couple 14 is placed in fastening clips 10 and clamps, and obtains being pasted with the hot junction position of thermocouple 14
The clamping tooling of structural member, the clamping tooling that will be pasted with the hot junction portion structure part of thermocouple 14 is placed on locating slot 4, regulation
The nozzle center of spray gun 6 keeps level, nozzle and the aircraft hot junction of spray gun 6 with aircraft hot junction portion structure part front end center
Portion structure part front end distance is 20cm, to water is added in water tank 7, opens airless sprayer 5 and spray gun 6, adjusts irrigation pressure
It is 22MPa, observes and ensure aircraft hot junction portion structure part by water smoke uniform fold from top surface and side；
3rd, the clamping tooling of the hot junction portion structure part for being pasted with thermocouple 14 is removed from locating slot 4, and will be pasted with
The clamping tooling of the hot junction portion structure part of thermocouple 14 is placed in heating device of muffle furnace 1 and heats and surveyed by temperature measuring equipment
Temperature, controls heating rate for 20 DEG C/min, is heated to temperature for 670 DEG C, and hot junction portion structure part is equipped with after being heated
Clamping tooling, after heating, open the fire door of heating device of muffle furnace 1, frock mobile bar 11 and the gap of base 8 are coordinated into peace
Dress, and using frock mobile bar 11 by heating after the clamping tooling for being equipped with hot junction portion structure part be placed on locating slot 4, beat
Spray gun 6 is driven, starts atomized water spray thermal shock and by temperature measuring equipment thermometric, water spray is stopped after hot junction portion structure part is cooled down completely
Mist；The described clamping tooling for being equipped with hot junction portion structure part from after using frock mobile bar 11 by heating is placed in locating slot
Until it is 2s~3s to start the time used by atomized water spray thermal shock on 4；
4th, after atomized water spray thermal shock terminates, aircraft hot junction portion structure part is removed from fastening clips 10, is dried,
The slabbing line developer of even application one on aircraft hot junction portion structure part surface, stands 2min, then that crackle developer is clear
Wash clean simultaneously stands, and waits crackle to observe crack morphology after manifesting, that is, complete a kind of test flight device hot junction portion structure part and resist
The application method of the atomized water spray pilot system of thermal shock resistance properties.
Described aircraft hot junction portion structure part is that length-width ratio is 1:1 ZrB2- SiC-G material nose of wing structural members,
Nose of wing structural member width is 25mm, a length of 25mm；The nozzle of spray gun 6 is rectangle.
In ZrB2Multiple thermocouples 14 are set on-SiC-G material nose of wing structural members, as shown in fig. 6, Fig. 6 is embodiment
One length-width ratio is 1:Thermocouple diverse location schematic diagram on 1 nose of wing structural member；Point 1~6 are that thermocouple is located at nose of wing
Structural member surface position, point 7 is that thermocouple is located at nose of wing structural member interior location；Then it is 22MPa, spray gun in irrigation pressure
6 nozzle and ZrB2When-SiC-G material nose of wing structural members front end distance is for 20cm, hot junction position during measurement thermal shock
The temperature variations of structural member, as illustrated in the schematic views of figures 7 and 8, Fig. 7 is the length-width ratio of embodiment one to the temperature lowering curve of diverse location thermocouple
It is 1:The temperature lowering curve figure of diverse location during 1 nose of wing structural member atomized water spray thermal shock；Fig. 8 amplifies for the A areas of Fig. 7
Figure, 1 is the temperature lowering curve figure of the position of Fig. 6 midpoints 1, and 2 is the temperature lowering curve figure of the position of Fig. 6 midpoints 2, and 3 is the position of Fig. 6 midpoints 3
Temperature lowering curve figure, 4 is the temperature lowering curve figure of the position of Fig. 6 midpoints 4, and 5 is the temperature lowering curve figure of the position of Fig. 6 midpoints 5, and 6 is Fig. 6 midpoints
The temperature lowering curve figure of 6 positions, 7 is the temperature lowering curve figure of the position of Fig. 6 midpoints 7, and its center line 2 and 3 is essentially coincided.As seen from the figure, exist
During atomized water spray thermal shock, temperature lowering curve is smoothed, and without occurring significantly fluctuating, illustrates the feasibility of temp measuring method.It is logical
The accurate measure to temperature lowering curve is crossed, help can be provided for numerical simulation.
Embodiment two：The present embodiment from unlike embodiment one：Described aircraft hot junction portion structure part is length and width
Than being 1:2 ZrB2- SiC-G material nose of wing structural members, nose of wing structural member width is 50mm, a length of 25mm.Other and reality
Apply example one identical.
Fig. 2 is that the length-width ratio of embodiment one is 1:The crack morphology figure of upper surface after 1 nose of wing structural member thermal shock；Fig. 3
For the length-width ratio of embodiment one is 1:The crack morphology figure of lower surface after 1 nose of wing structural member thermal shock；Fig. 4 grows for embodiment two
Ratio wide is 1:The crack morphology figure of upper surface after 2 nose of wing structural member thermal shock；Fig. 5 is that the length-width ratio of embodiment two is 1:2
The crack morphology figure of lower surface after nose of wing structural member thermal shock；For exemplary airfoil leading edge structure part, system is tested using embodiment
System and the failure mode on method examination rear wing leading edge structure part up/down surface, different size nose of wing structural member up/down surface
Crack morphology is essentially identical, illustrates what crackle was through, when nose of wing structural member width is 25mm, the crackle that thermal shock is produced
Extended along water spraying direction forward edge bottom, crackle is approximately linear；With the increase (50mm) of nose of wing structural member width,
The crackle that thermal shock is produced occurs the deflection of wide-angle, easily occurs peeling off so as to cause leading edge to fail.Tried using embodiment
After check system and method examination failure mode and the existing wind-tunnel result of appraisal of nose of wing are coincide, it was demonstrated that the method it is reasonable
Property.
Claims (8)
1. a kind of atomized water spray pilot system of test flight device hot junction portion structure part thermal shock resistance, it is characterised in that：One
The atomized water spray pilot system of kind of test flight device hot junction portion structure part thermal shock resistance include heating device of muffle furnace (1),
Hydraulic test stage apparatus, atomized water spray fast cooling device, hot junction portion structure part clamping tooling, frock mobile bar (11) and
Temperature measuring equipment；
Described hydraulic test stage apparatus include objective table (2) and spray gun secured adjusted bar (3)；
Described atomized water spray fast cooling device includes airless sprayer (5), spray gun (6) and water tank (7)；
Described hot junction portion structure part clamping tooling includes base (8), support (9) and fastening clips (10)；
Described temperature measuring equipment includes thermocouple (14), ceramic protecting pipe (15), electric wire connecting junction (16) and data collecting instrument (17)；
Heating device of muffle furnace (1) reclines with objective table (2), and heating device of muffle furnace (1) fire door lower edge is higher than objective table
(2) upper surface, objective table (2) upper surface is provided with spray gun secured adjusted bar (3) and locating slot (4), in spray gun secured adjusted bar (3)
Be provided with spray gun (6), spray gun (6) is connected by high-pressure hose with airless sprayer (5), airless sprayer (5) by water pipe with
Water tank (7) is connected；And the nozzle center of spray gun (6) keeps level with aircraft hot junction portion structure part front end center；Wherein,
The nozzle of spray gun (6) ensure that water smoke uniform fold hot junction portion structure with aircraft hot junction portion structure part front end distance
Part；
Locating slot (4) is provided with base (8), and base (8) upper surface is connected by support (9) with the lower surface of fastening clips (10)
Connect, frock mobile bar (11) coordinates with base (8) gap, fastening clips (10) are provided with aircraft hot junction portion structure part, heat
Galvanic couple (14) is fixed on aircraft hot junction portion structure part surface or inside, and thermocouple (14) is externally provided with ceramic protecting pipe (15),
Thermocouple (14) afterbody both positive and negative polarity is connected with electric wire connecting junction (16), and electric wire connecting junction (16) is connected by data wire with data collecting instrument (17)
Connect.
2. the atomized water spray experiment of a kind of test flight device hot junction portion structure part thermal shock resistance according to claim 1
System, it is characterised in that described thermocouple (14) is K-type thermocouple.
3. the atomized water spray experiment of a kind of test flight device hot junction portion structure part thermal shock resistance according to claim 1
System, it is characterised in that when described aircraft hot junction portion structure part is flat nose of wing structural member, the spray of spray gun (6)
Mouth can use rectangle.
4. the atomized water spray experiment of a kind of test flight device hot junction portion structure part thermal shock resistance according to claim 1
System, it is characterised in that when described aircraft hot junction portion structure part is circular Nose structure part, the nozzle of spray gun (6)
Can be using circle.
5. a kind of atomized water spray of test flight device hot junction portion structure part thermal shock resistance as claimed in claim 1 tests system
The application method of system, it is characterised in that：A kind of atomized water spray experiment of test flight device hot junction portion structure part thermal shock resistance
The application method of system, is carried out according to the following steps：
First, thermocouple (14) is placed in ceramic protecting pipe (15), and aircraft hot junction portion structure is fixed on by high-temp glue
The surface or inside of part, stand after after thermocouple (14) fixation, then by thermocouple (14) afterbody both positive and negative polarity and electric wire connecting junction
(16) connect, electric wire connecting junction (16) is connected with data collecting instrument (17) by data wire, obtains being pasted with thermocouple (14) again
Aircraft hot junction portion structure part；
2nd, fastening clips (10) lower surface is connected and fixed with base (8) upper surface by support (9), then will be pasted with
The aircraft hot junction portion structure part of thermocouple (14) is placed in fastening clips (10) and clamps, and obtains being pasted with thermocouple (14)
The clamping tooling of hot junction portion structure part, the clamping tooling that will be pasted with the hot junction portion structure part of thermocouple (14) is placed in positioning
On groove (4), nozzle center and the aircraft hot junction portion structure part front end center of regulation spray gun (6) keep level, adjust spray gun
(6) nozzle and aircraft hot junction portion structure part front end distance, to water is added in water tank (7), open airless sprayer (5) and
Spray gun (6), adjusts irrigation pressure, observes and ensure that aircraft hot junction portion structure part is uniformly covered by water smoke from top surface and side
Lid；
3rd, the clamping tooling of the hot junction portion structure part for being pasted with thermocouple (14) is removed from locating slot (4), and will be pasted with
The clamping tooling of the hot junction portion structure part of thermocouple (14) is placed in heating device of muffle furnace (1) and heats and by temperature measuring equipment
Thermometric, control heating rate is less than 30 DEG C/min, the clamping tooling for being equipped with hot junction portion structure part after being heated, heating
Afterwards, the fire door of heating device of muffle furnace (1) is opened, frock mobile bar (11) and base (8) gap is coordinated and is installed, and utilize work
The clamping tooling of hot junction portion structure part that is equipped with after mobile bar (11) is filled by heating is placed on locating slot (4), opens spray gun
(6), start atomized water spray thermal shock and by temperature measuring equipment thermometric, atomized water spray is stopped after hot junction portion structure part is cooled down completely；
And the clamping tooling of hot junction portion structure part that is equipped with from after using frock mobile bar (11) by heating is placed on locating slot (4)
It is 2s~3s to the time started used by atomized water spray thermal shock；
4th, after atomized water spray thermal shock terminates, aircraft hot junction portion structure part is removed from fastening clips (10), is dried,
The slabbing line developer of aircraft hot junction portion structure part surface even application one, stands 1min~3min, and then crackle develops
Agent is cleaned up and stood, and waits crackle to observe crack morphology after manifesting, that is, complete a kind of test flight device hot junction portion structure
The application method of the atomized water spray pilot system of part thermal shock resistance.
6. the atomized water spray experiment of a kind of test flight device hot junction portion structure part thermal shock resistance according to claim 5
The application method of system, it is characterised in that the thermocouple (14) described in step one is K-type thermocouple.
7. the atomized water spray experiment of a kind of test flight device hot junction portion structure part thermal shock resistance according to claim 5
The application method of system, it is characterised in that the aircraft hot junction portion structure part described in step one is flat nose of wing knot
During component, the nozzle of the spray gun (6) described in step 2 can use rectangle.
8. the atomized water spray experiment of a kind of test flight device hot junction portion structure part thermal shock resistance according to claim 5
The application method of system, it is characterised in that the aircraft hot junction portion structure part described in step one is circular Nose structure
During part, the nozzle of the spray gun (6) described in step 2 can be using circle.
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| CN108344655A (en) * | 2018-01-30 | 2018-07-31 | 重庆大学 | Ceramic material spray-type thermal shock rig and method under a kind of closed environment |
| CN111752315A (en) * | 2019-03-29 | 2020-10-09 | 中国科学院长春光学精密机械与物理研究所 | Temperature control method, temperature controller and temperature control system for vacuum thermal test of spacecraft |
| CN113237564A (en) * | 2021-05-07 | 2021-08-10 | 北京理工大学 | High-temperature thermocouple multi-point temperature measurement clamp for ablation examination |
| CN114544209A (en) * | 2021-12-28 | 2022-05-27 | 中核武汉核电运行技术股份有限公司 | Thermal shock test device for verifying pipe plugging process of nuclear-grade steam generator |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108344655A (en) * | 2018-01-30 | 2018-07-31 | 重庆大学 | Ceramic material spray-type thermal shock rig and method under a kind of closed environment |
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| CN113237564A (en) * | 2021-05-07 | 2021-08-10 | 北京理工大学 | High-temperature thermocouple multi-point temperature measurement clamp for ablation examination |
| CN114544209A (en) * | 2021-12-28 | 2022-05-27 | 中核武汉核电运行技术股份有限公司 | Thermal shock test device for verifying pipe plugging process of nuclear-grade steam generator |
| CN114544209B (en) * | 2021-12-28 | 2024-01-12 | 中核武汉核电运行技术股份有限公司 | Thermal shock test device for verifying pipe plugging process of nuclear-grade steam generator |
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