CN114837854B - Low-cost test device and method for simulating slow baking combustion of engine - Google Patents
Low-cost test device and method for simulating slow baking combustion of engine Download PDFInfo
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- CN114837854B CN114837854B CN202210411891.4A CN202210411891A CN114837854B CN 114837854 B CN114837854 B CN 114837854B CN 202210411891 A CN202210411891 A CN 202210411891A CN 114837854 B CN114837854 B CN 114837854B
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- combustion chamber
- thermocouple
- propellant
- temperature measuring
- side wall
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 110
- 238000012360 testing method Methods 0.000 title claims abstract description 41
- 238000000034 method Methods 0.000 title claims abstract description 13
- 239000003380 propellant Substances 0.000 claims abstract description 53
- 239000007921 spray Substances 0.000 claims abstract description 35
- 238000009529 body temperature measurement Methods 0.000 claims abstract description 12
- 239000007769 metal material Substances 0.000 claims abstract description 5
- 238000007789 sealing Methods 0.000 claims abstract 2
- 230000000712 assembly Effects 0.000 claims description 23
- 238000000429 assembly Methods 0.000 claims description 23
- 239000000565 sealant Substances 0.000 claims description 19
- 230000001681 protective effect Effects 0.000 claims description 16
- 230000000903 blocking effect Effects 0.000 claims description 15
- 239000000523 sample Substances 0.000 claims description 14
- 238000010438 heat treatment Methods 0.000 claims description 11
- 229920000742 Cotton Polymers 0.000 claims description 6
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 6
- -1 polytetrafluoroethylene Polymers 0.000 claims description 6
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 6
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 6
- 238000010998 test method Methods 0.000 claims description 4
- 230000003247 decreasing effect Effects 0.000 claims description 3
- 239000002904 solvent Substances 0.000 claims description 3
- 239000003292 glue Substances 0.000 claims 1
- 239000007787 solid Substances 0.000 abstract description 8
- 238000012545 processing Methods 0.000 abstract description 2
- 238000006243 chemical reaction Methods 0.000 description 8
- 238000012544 monitoring process Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000002474 experimental method Methods 0.000 description 3
- 229910052782 aluminium Inorganic materials 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 239000011888 foil Substances 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000004449 solid propellant Substances 0.000 description 2
- 238000009736 wetting Methods 0.000 description 2
- 239000002390 adhesive tape Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004200 deflagration Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000004321 preservation Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/96—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by specially adapted arrangements for testing or measuring
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Testing Of Engines (AREA)
Abstract
The invention discloses a low-cost test device and a method for simulating slow baking and burning of an engine, wherein the test device comprises an end cover, a combustion chamber, a spray pipe, a blanking cover and a thermocouple assembly; the combustion chamber is provided with a plurality of temperature measuring channels, and the thermocouple assembly is embedded into the propellant in the combustion chamber through the temperature measuring channels; the spray pipe and the blanking cover can be made of all-metal materials, so that the test device is in a sealing state in the storage and transportation processes, and the propellant is prevented from being affected with damp. The invention can realize the accurate control of the thermocouples by controlling the length of the thermocouple assembly stretching into the combustion chamber, can meet the temperature measurement requirement of multiple channels by changing the processing number of the temperature measurement channels, has better operability and low cost, can effectively collect the temperature of the internal characteristic points of the propellant, and is suitable for the slow burning test of the simulated solid rocket engine.
Description
Technical Field
The invention relates to a low-cost test device for simulating slow baking combustion of an engine, in particular to a simulated engine for composite solid propellant charge.
Background
When the thermal safety of the solid rocket engine is evaluated, a baking and burning experiment is a main evaluation means, wherein the slow baking and burning safety experiment is the most visual and effective means for evaluating the thermal safety of the solid rocket engine and the propellant, and is also one of the items which are most difficult to pass in the vulnerability assessment of the solid rocket engine. The composite solid propellant is the most widely applied charge of medium-large solid rocket engines, however, if an engine with an actual size is adopted for a slow burning test, the test cost is high, and available data is less, so that most of the slow burning tests at present generally adopt a small-sized simulation piece for a shrinkage ratio test.
Most of the existing baking and burning test pieces adopt the same top cover form from front to back, and the fact that the tail part of an actual solid rocket engine is generally a spray pipe is not considered, so that the constraint forms of the front and back positions of the engine are different; and most experiments do not monitor the temperature inside the propellant, or only a few thermocouples are arranged, so that the temperature rise process inside the propellant cannot be obtained, the actual condition of the propellant under the condition of slow burning is difficult to reflect, and the reaction temperature of the engine charge is unreasonable only by using the surface temperature of the shell. In order to understand the influence of the self-heating reaction process of the propellant and the constraint condition of the engine on the baking reaction degree in the slow baking environment, the baking device needs to simulate the actual solid rocket engine for design, can monitor the temperature of the internal characteristic points of the propellant in a multi-channel manner, and has good operability and low cost.
Disclosure of Invention
Aiming at the defects of the prior art, the invention aims to provide a low-cost test device and method for simulating slow baking and burning of an engine, so as to solve the problems that temperature measurement data in a propellant is missing, baking and burning characteristics of a solid rocket engine cannot be represented and the like in the existing baking and burning test.
In order to solve the technical problems, the invention adopts the following technical scheme:
the low-cost test device for simulating slow baking and burning of the engine comprises a combustion chamber, end covers and spray pipes which are arranged at two ends of the combustion chamber, a blanking cover which is arranged on the spray pipes, a plurality of thermocouple assemblies which can be inserted into the combustion chamber along the side wall of the combustion chamber, and a closed cavity which is enclosed by the combustion chamber, the end covers, the spray pipes and the blanking cover, wherein propellant is poured into the closed cavity;
the thermocouple assembly comprises a thermocouple, a thermocouple protective sleeve sleeved outside the thermocouple and a thermocouple probe positioned at the end part of the thermocouple; the thermocouple assembly is embedded in the propellant in the closed cavity, so that the multipoint temperature measurement of the inside of the propellant can be realized; the number, the length and the position of the thermocouple assemblies extending into the combustion chamber are set according to the requirement of multipoint temperature measurement.
The invention also comprises the following technical characteristics:
specifically, the combustion chamber is of a cylindrical structure, a plurality of side wall through holes are formed in the side wall of the combustion chamber, a plurality of positioning bosses are welded on the side wall of the combustion chamber, the side wall through holes are opposite to the positioning bosses one by one, and the center through holes of the positioning bosses are coaxially communicated with the side wall through holes to form a temperature measuring channel; the thermocouple assembly can enter the combustion chamber through the temperature measuring channel.
Specifically, the thermocouple assembly is inserted into the combustion chamber in a radial direction of the combustion chamber.
Specifically, the end cover is of a round groove structure, the end cover is arranged at an opening at one end of the combustion chamber, and sealant is arranged at the joint of the combustion chamber and the end cover;
the spray pipe is of an integrated structure and comprises a cylindrical connecting end, a conical section and a cylindrical blocking end, wherein the diameter of the cylindrical connecting end is larger than that of the cylindrical blocking end; the cylindrical connecting end of the spray pipe is arranged at the opening of the other end of the combustion chamber, the joint of the combustion chamber and the cylindrical connecting end of the spray pipe is provided with sealant, and the cylindrical blocking end of the spray pipe is provided with the blocking cover.
Specifically, the end cover is connected with the combustion chamber, the combustion chamber is connected with the spray pipe and the spray pipe is connected with the blanking cover through screw threads or flanges; the joint is all equipped with the sealant in order to guarantee that test device is in sealed state in storage and transportation, prevents that the propellant from wetting.
Specifically, the thermocouple protective sleeve is made of polytetrafluoroethylene, the thermocouple is a K-type thermocouple, the thermocouple protective sleeve and the thermocouple are fixed through sealant, and the thermocouple probe is flush with the inner end surface of the thermocouple protective sleeve.
Specifically, after the thermocouple assembly stretches into the temperature measuring channel, the outer end face of the thermocouple protective sleeve is flush with the positioning boss, and a high-temperature-resistant aluminum foil adhesive tape is wound on the thermocouple positioned outside the combustion chamber to fix the thermocouple.
Specifically, the end cover, the combustion chamber, the spray pipe and the blanking cover are all made of metal materials.
Specifically, the number of the thermocouple assemblies is six, and the number of the corresponding positioning bosses, the corresponding side wall through holes and the corresponding temperature measuring channels formed by the positioning bosses and the corresponding side wall through holes are six; wherein, three temperature measuring channels are arranged as a group, the group of temperature measuring channels are positioned on the side wall of the lower part of the combustion chamber and are distributed at equal intervals along the axial direction in turn; the other three temperature measuring channels are a group, the group of temperature measuring channels are positioned on the upper side wall of the combustion chamber and are respectively opposite to the three temperature measuring channels on the lower side wall one by one;
the three thermocouple assemblies are correspondingly inserted into one group of temperature measuring channels, the lengths of the three thermocouple assemblies extending into the combustion chamber are the same, and the thermocouple probes extend to the central axis of the combustion chamber; the other three thermocouple assemblies are correspondingly inserted into another group of temperature measuring channels, and the lengths of the three thermocouple assemblies extending into the combustion chamber are sequentially increased or decreased.
A low-cost test method for simulating slow baking combustion of an engine is realized by the low-cost test device for simulating slow baking combustion of the engine; the method comprises the following steps:
step 1, connecting an end cover with a combustion chamber, smearing sealant at the joint, after the sealant is solidified for 24 hours at normal temperature, wiping dirt on the inner surfaces of the combustion chamber and the end cover by using solvents such as ethanol and the like, and temporarily blocking a temperature measuring channel by using cotton;
step 2, pouring the propellant into a combustion chamber, vacuumizing, taking down cotton at a temperature measuring channel before the propellant is not solidified, smearing a proper amount of sealant on the tail part of a thermocouple protective sleeve, and embedding a thermocouple assembly into the propellant; when the thermocouple protective sleeve is level with the outer surface of the temperature measuring channel, the thermocouple assembly is pre-buried in place;
step 3, after the propellant is solidified, the external surface of the propellant is trimmed; then assembling the spray pipe and the blanking cover in sequence until the whole test device is assembled;
and 4, heating the test device, and performing multi-point temperature measurement on the inside of the propellant through each thermocouple assembly.
Compared with the prior art, the invention has the following beneficial technical effects:
(1) According to the invention, the K-type thermocouple is fixed by using the polytetrafluoroethylene pipeline, and the thermocouple is pre-buried in the propellant internal monitoring area through the temperature measuring channel arranged on the side surface of the combustion chamber shell, so that multichannel temperature monitoring of the propellant in the baking and burning process is realized.
(2) The invention adopts common metal materials and connection forms, and has simple processing forms; the temperature measurement requirement can be met by adopting the K-type thermocouple and the polytetrafluoroethylene tube with lower economy, so that the whole baking and burning device has better low cost.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a schematic view of a thermocouple assembly according to the present invention;
FIG. 3 is a schematic diagram of the distribution of the test points of the thermocouple probe according to the embodiment of the present invention;
fig. 4 is an enlarged view of a temperature rise curve of an internal monitoring point of an engine simulated according to an embodiment of the present invention, (a) is a whole process temperature rise curve, and (b) is a temperature rise curve of a part of characteristic points at an end stage.
The meaning of each reference numeral in the figures is:
1. the device comprises a combustion chamber, an end cover, a spray pipe, a plug cover, a thermocouple assembly, a propellant, a positioning boss, a cylindrical connecting end, a conical section, a cylindrical plugging end, a thermocouple protective sleeve and a thermocouple probe.
Detailed Description
The invention provides a low-cost test device and a low-cost test method for simulating slow baking and burning of an engine, wherein a temperature measuring channel is formed in the surface of a combustion chamber, a low-cost polytetrafluoroethylene tube is used as a thermocouple protective sleeve for fixing a K-type thermocouple, the thermocouple is embedded in a propellant through the temperature measuring channel, so that multipoint temperature measurement of the inside of the propellant is realized, the self-heating reaction progress of the inside of the propellant is analyzed, and the position of a baking and burning response area can be obtained relatively accurately by utilizing acquired temperature data.
As shown in figures 1 and 2, the low-cost test device for simulating slow baking and combustion of the engine provided by the invention comprises a combustion chamber 1, end covers 2 and spray pipes 3 arranged at two ends of the combustion chamber 1, a blanking cover 4 arranged on the spray pipes 3, a plurality of thermocouple assemblies 5 which can be inserted into the combustion chamber 1 along the side wall of the combustion chamber 1, and a closed cavity surrounded by the combustion chamber 1, the end covers 2, the spray pipes 3 and the blanking cover 4, wherein propellant is poured into the closed cavity.
The thermocouple assembly 5 comprises a thermocouple 51, a thermocouple protective sleeve 52 sleeved outside the thermocouple 51 and a thermocouple probe 53 positioned at the end part of the thermocouple 51; the thermocouple assembly 5 is pre-buried in the propellant in the closed cavity, so that the multipoint temperature measurement of the inside of the propellant can be realized; the number, length and position of the thermocouple assembly 5 extending into the combustion chamber 1 are set according to the requirement of multipoint temperature measurement.
The combustion chamber 1 is of a cylindrical structure, a plurality of side wall through holes are formed in the side wall of the combustion chamber 1, a plurality of positioning bosses 11 are welded on the side wall of the combustion chamber 1, the side wall through holes are opposite to the positioning bosses 11 one by one, and the center through hole of the positioning boss 11 is coaxially communicated with the side wall through holes to form a temperature measuring channel; the thermocouple assembly 5 can enter the combustion chamber 1 through a temperature measuring channel.
The thermoelement assembly 5 is inserted into the combustion chamber 1 in the radial direction of the combustion chamber 1.
The end cover 2 is of a round groove structure, the end cover 2 is arranged at an opening at one end of the combustion chamber 1, and sealant is arranged at the joint of the combustion chamber 1 and the end cover 2;
the spray pipe 3 is of an integrated structure and comprises a cylindrical connecting end 31, a conical section 32 and a cylindrical blocking end 33, wherein the diameter of the cylindrical connecting end 31 is larger than that of the cylindrical blocking end 33; the tubular connecting end 31 of the spray pipe 3 is arranged at the opening of the other end of the combustion chamber 1, the joint of the combustion chamber 1 and the tubular connecting end 31 of the spray pipe 3 is provided with sealant, and the tubular blocking end 33 of the spray pipe 3 is provided with a blocking cover 4.
The end cover 2 is connected with the combustion chamber 1, the combustion chamber 1 is connected with the spray pipe 3 and the spray pipe 3 is connected with the blanking cover 4 through screw threads or flanges; the joint is all equipped with the sealant in order to guarantee that test device is in sealed state in storage and transportation, prevents that the propellant from wetting.
The thermocouple protection sleeve 52 is made of polytetrafluoroethylene, the thermocouple 51 is a K-type thermocouple, the thermocouple protection sleeve 52 and the thermocouple 51 are fixed through sealant, and the thermocouple probe 53 is flush with the inner end surface of the thermocouple protection sleeve 52.
After the thermocouple assembly 5 stretches into the temperature measuring channel, the outer end face of the thermocouple protective sleeve 52 is flush with the positioning boss 11, and a high-temperature-resistant aluminum foil tape is wound on the thermocouple 51 positioned outside the combustion chamber 1 to fix the thermocouple 51.
The end cover 2, the combustion chamber 1, the spray pipe 3 and the blanking cover 4 are all made of metal materials.
The low-cost test method for simulating the slow baking combustion of the engine is realized by the low-cost test device for simulating the slow baking combustion of the engine; the method comprises the following steps:
step 1, connecting an end cover with a combustion chamber, smearing sealant at the joint, after the sealant is solidified for 24 hours at normal temperature, wiping dirt on the inner surfaces of the combustion chamber and the end cover by using solvents such as ethanol and the like, and temporarily blocking a temperature measuring channel by using cotton;
step 2, pouring the propellant into a combustion chamber, vacuumizing, taking down cotton at a temperature measuring channel before the propellant is not solidified, smearing a proper amount of sealant on the tail part of a thermocouple protective sleeve, and embedding a thermocouple assembly into the propellant; when the thermocouple protective sleeve is level with the outer surface of the temperature measuring channel, the thermocouple assembly is pre-buried in place;
step 3, after the propellant is solidified, the external surface of the propellant is trimmed; then assembling the spray pipe and the blanking cover in sequence until the whole test device is assembled;
and 4, heating the test device by adopting a slow baking and burning test system, and measuring the temperature of the inside of the propellant at multiple points by using each thermocouple assembly.
Examples:
as shown in FIG. 3, the low-cost test device for simulating slow baking and burning of the engine in the embodiment has six thermocouple assemblies 5, and six corresponding positioning bosses 11, side wall through holes and temperature measuring channels formed by the positioning bosses and the side wall through holes; wherein, three temperature measuring channels are a group, the group of temperature measuring channels are positioned on the side wall of the lower part of the combustion chamber 1 and are distributed at equal intervals along the axial direction in turn; the other three temperature measuring channels are a group, the group of temperature measuring channels are positioned on the upper side wall of the combustion chamber 1 and are respectively opposite to the three temperature measuring channels on the lower side wall one by one; three thermocouple assemblies 5 are correspondingly inserted into one group of temperature measuring channels, the lengths of the three thermocouple assemblies 5 extending into the combustion chamber 1 are the same, and the thermocouple probes 53 extend to the central axis of the combustion chamber 1; the other three thermocouple assemblies 5 are correspondingly inserted into another group of temperature measuring channels, and the lengths of the three thermocouple assemblies 5 extending into the combustion chamber 1 are sequentially increased or decreased.
Specifically, the charging diameter of the combustion chamber is 100mm, and the charging length is 200mm;
the distances between the three temperature measuring channels positioned on the side wall of the lower part of the combustion chamber and the end cover are sequentially 50mm, 100mm and 150mm, the lengths of thermocouple assemblies inserted into the three temperature measuring channels are the same, thermocouple probes of the three thermocouple assemblies extend to the central axis of the combustion chamber, and the measured positions of the three thermocouple probes are sequentially a No. 3 point, a No. 2 point and a No. 1 point;
the distances between the three temperature measuring channels positioned on the side wall of the upper part of the combustion chamber and the end cover are sequentially 50mm, 100mm and 150mm, the lengths of the thermocouple assemblies inserted into the three temperature measuring channels are sequentially increased, the positions of the thermocouple probes of the three thermocouple assemblies are sequentially 6 # point, 5 # point and 4 # point, and the distances between the 6 # point, the 5 # point and the 4 # point and the central axis of the combustion chamber are respectively 5, 15 and 25mm.
The test device of the embodiment is adopted to carry out multipoint temperature measurement on the inside of the propellant to obtain a temperature rise curve of monitoring points in a 100mm simulated engine, as shown in fig. 4, wherein fig. 4 (a) is a whole process temperature rise curve, and fig. 4 (b) is an enlarged diagram of the temperature rise curve of partial characteristic points at the final stage, and the heating rate of the test is as follows: in the first 1 hour, the surface temperature of the shell of the simulated engine is increased from room temperature to about 180 ℃, then the shell is kept for 2 hours, and then the shell is heated at a heating rate of 3.3K/h until the simulated engine generates a baking combustion response. From these two figures it can be seen that: in the first 60min, the temperature of the outer surface of the shell is highest, and the temperature difference between the No. 1 point and the No. 6 point in the propulsion interior is larger, because the simulated engine has no heat insulation layer, external heat can be quickly transferred to the propulsion interior through the metal shell, and the heat conductivity of the propellant is far lower than that of the metal shell, so that a larger temperature gradient exists in the propellant. When the heat preservation stage is finished, namely the heating time is 180min, the maximum temperature difference between the No. 1 point and the No. 6 point is 6 ℃, wherein the temperature of the No. 4 point and the No. 5 point which are close to the surface of the shell is higher, which indicates that the temperature difference of each characteristic point inside the propellant is gradually reduced. The temperature rise of each point is more consistent in the earlier stage of the heating stage of 3.3K/h; when heated to 560min, the temperatures of points No. 1, no. 2 and No. 5 gradually exceeded points No. 4, no. 3 and No. 6, and the temperature rise rates of points No. 1, no. 2 and No. 5 increased significantly, after which the temperatures exceeded the surface temperature of the housing. This phenomenon indicates that: the propellant forms a distinct high temperature zone near the areas near points 1, 2 and 5, indicating that the self-heating reaction has occurred within the propellant and that the reaction progress is significantly accelerated. At 612min, the temperature of the point No. 2 is highest, the maximum temperature difference between the point No. 1 and the point No. 6 is about 15 ℃, and the propellant is subjected to deflagration reaction, so that the test device with the charge diameter of 100mm is illustrated, and the baking and burning response area of the test device is near the point No. 2, namely near the center of the propellant. Through the data analysis, the test device can analyze the self-heating reaction progress in the propellant by utilizing the acquired temperature data, and relatively accurately obtain the position of the baking combustion response area of the simulated engine.
Claims (6)
1. The low-cost test device for simulating slow baking and burning of the engine is characterized by comprising a combustion chamber (1), end covers (2) and spray pipes (3) arranged at two ends of the combustion chamber (1), a blanking cover (4) arranged on the spray pipes (3), a plurality of thermocouple assemblies (5) capable of being inserted into the combustion chamber (1) along the side wall of the combustion chamber (1), and a closed cavity surrounded by the combustion chamber (1), the end covers (2), the spray pipes (3) and the blanking cover (4), wherein propellant is poured into the combustion chamber (1);
the thermocouple assembly (5) comprises a thermocouple (51), a thermocouple protective sleeve (52) sleeved outside the thermocouple (51) and a thermocouple probe (53) positioned at the end part of the thermocouple (51); embedding the thermocouple assembly (5) in the propellant in the closed cavity;
the combustion chamber (1) is of a cylindrical structure, a plurality of side wall through holes are formed in the side wall of the combustion chamber (1), a plurality of positioning bosses (11) are welded on the side wall of the combustion chamber (1), the side wall through holes are opposite to the positioning bosses (11) one by one, and the center through holes of the positioning bosses (11) are coaxially communicated with the side wall through holes to form a temperature measuring channel; the thermocouple assembly (5) can enter the combustion chamber (1) through a temperature measuring channel;
the thermocouple assembly (5) is inserted into the combustion chamber (1) along the radial direction of the combustion chamber (1);
the end cover (2) is of a round groove structure, the end cover (2) is arranged at an opening at one end of the combustion chamber (1), and sealant is arranged at the joint of the combustion chamber (1) and the end cover (2);
the spray pipe (3) is of an integrated structure and comprises a cylindrical connecting end (31), a conical section (32) and a cylindrical blocking end (33) which are sequentially connected, wherein the diameter of the cylindrical connecting end (31) is larger than that of the cylindrical blocking end (33); the cylindrical connecting end (31) of the spray pipe (3) is arranged at the opening of the other end of the combustion chamber (1), sealing glue is arranged at the joint of the combustion chamber (1) and the cylindrical connecting end (31) of the spray pipe (3), and the blocking cover (4) is arranged on the cylindrical blocking end (33) of the spray pipe (3);
the number of the thermocouple assemblies (5) is six, and the number of the corresponding positioning bosses (11), the side wall through holes and the temperature measuring channels formed by the positioning bosses and the side wall through holes are six; wherein three temperature measuring channels are arranged as a group and are positioned on the side wall of the lower part of the combustion chamber (1) and are distributed at equal intervals along the axial direction in turn; the other three temperature measuring channels are in a group and are positioned on the upper side wall of the combustion chamber (1) and are respectively opposite to the three temperature measuring channels on the lower side wall one by one;
three thermocouple assemblies (5) are correspondingly inserted into one group of temperature measuring channels, the lengths of the three thermocouple assemblies (5) extending into the combustion chamber (1) are the same, and thermocouple probes (53) extend to the central axis of the combustion chamber (1); the other three thermocouple assemblies (5) are correspondingly inserted into another group of temperature measuring channels, and the lengths of the other three thermocouple assemblies (5) extending into the combustion chamber (1) are sequentially increased or decreased.
2. A low cost test apparatus for simulating slow burn of an engine according to claim 1, wherein the end cap (2) and the combustion chamber (1), the combustion chamber (1) and the nozzle (3) and the blanking cover (4) are connected by screw threads or flanges.
3. The low-cost test device for simulating slow baking combustion of an engine according to claim 1, wherein the thermocouple protection sleeve (52) is made of polytetrafluoroethylene, the thermocouple (51) is a K-type thermocouple, the thermocouple protection sleeve (52) and the thermocouple (51) are fixed through sealant, and the thermocouple probe (53) is flush with the inner end surface of the thermocouple protection sleeve (52).
4. The low-cost test device for simulating slow combustion of an engine according to claim 1, wherein the outer end surface of the thermocouple protecting sleeve (52) is flush with the positioning boss (11) after the thermocouple assembly (5) extends into the temperature measuring channel.
5. The low-cost test device for simulating slow combustion of an engine according to claim 1, wherein the end cover (2), the combustion chamber (1), the spray pipe (3) and the plug cover (4) are all made of metal materials.
6. A low-cost test method for simulating slow baking combustion of an engine, which is characterized in that the method is realized by the low-cost test device for simulating slow baking combustion of an engine according to any one of claims 1 to 5; the method comprises the following steps:
step 1, connecting an end cover with a combustion chamber, smearing sealant at the joint, after the sealant is solidified for 24 hours at normal temperature, wiping dirt on the inner surfaces of the combustion chamber and the end cover by using an ethanol solvent, and temporarily blocking a temperature measuring channel by using cotton;
step 2, pouring the propellant into a combustion chamber, vacuumizing, taking down cotton at a temperature measuring channel before the propellant is not solidified, smearing a proper amount of sealant on the tail part of a thermocouple protective sleeve, and embedding a thermocouple assembly into the propellant; when the thermocouple protective sleeve is level with the outer surface of the temperature measuring channel, the thermocouple assembly is pre-buried in place;
step 3, after the propellant is solidified, the external surface of the propellant is trimmed; then assembling the spray pipe and the blanking cover in sequence until the whole test device is assembled;
and 4, heating the test device, and performing multi-point temperature measurement on the inside of the propellant through each thermocouple assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210411891.4A CN114837854B (en) | 2022-04-19 | 2022-04-19 | Low-cost test device and method for simulating slow baking combustion of engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210411891.4A CN114837854B (en) | 2022-04-19 | 2022-04-19 | Low-cost test device and method for simulating slow baking combustion of engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114837854A CN114837854A (en) | 2022-08-02 |
| CN114837854B true CN114837854B (en) | 2023-12-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210411891.4A Active CN114837854B (en) | 2022-04-19 | 2022-04-19 | Low-cost test device and method for simulating slow baking combustion of engine |
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