Structure-adjustable supercritical pressure hydrocarbon fuel jet impingement cooling experimental device

Abstract

The invention relates to a structure-adjustable supercritical pressure hydrocarbon fuel jet impingement cooling experimental device, and belongs to the technical field of high-temperature thermal protection experimental equipment. The device comprises an upper cover, a sealing gasket, an upper chamber adjusting block, a jet flow plate, a lower chamber adjusting plate, a lower cover, a fastener, a fixing screw and a temperature measuring element, and the height of an upper chamber is adjusted by replacing the upper chamber adjusting block, the jet flow plate and the lower chamber adjusting plate with different structural parameters. Key structure parameters such as the diameter, the distance, the arrangement mode and the height of jet holes and the jet impact height in a jet impact cooling experiment are adopted, and a sealing gasket wound by 310S stainless steel and stainless steel graphite is adopted as a main body of the device, so that the inlet temperature of 400 DEG C to the maximum and the outlet pressure of 6 MPa to the maximum are tolerated. According to the structure-adjustable supercritical pressure hydrocarbon fuel jet impingement cooling experimental device provided by the invention, the experimental cost is remarkably reduced through modularized replacement parts, and an efficient experimental platform is provided for thermal protection research of a scramjet engine.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of high-temperature heat protection experimental equipment, in particular to a structure-adjustable supercritical pressure carbon-hydrogen fuel jet impingement cooling experimental device. BACKGROUND

[0002] Hypersonic vehicles are one of the important development directions in the field of aerospace in nearly half a century, and are known as the third industrial revolution in aviation history. As the core device of hypersonic vehicles, the scramjet engine needs to work for a long time under extreme high-temperature conditions. For example, when the flight Mach number reaches 8, the temperature of the uncooled combustion chamber wall will exceed 3000K, far exceeding the heat resistance limit of existing aviation materials. Therefore, thermal management of the engine is crucial, and the regenerative cooling technology using supercritical pressure carbon-hydrogen fuel as the coolant is one of the effective solutions to the thermal protection problem of the scramjet engine. However, due to the cooling capacity of supercritical pressure carbon-hydrogen fuel in the single-layer micro-channel cooling structure of the scramjet engine wall, the required cooling fuel flow under high load is much higher than the combustion consumption, resulting in serious waste of fuel.

[0003] Compared with the traditional single-layer micro-channel cooling structure, jet impingement cooling can produce a stronger cooling effect on the hot wall, and has been widely used in high-power electronic component cooling, gas turbine blade cooling, material heat treatment and many other fields. However, it is not practical to conduct jet impingement cooling experiments on the hot wall of the scramjet engine at the current engineering scale, so a small experimental device that can meet the relevant experimental indicators is needed. However, the existing jet impingement cooling experimental devices mostly use low-pressure air, water and other conventional fluids as cooling media, which cannot meet the experimental requirements of supercritical pressure carbon-hydrogen fuel under the conditions of a maximum inlet temperature of 400℃ and a maximum outlet pressure of 6MPa. Moreover, the existing device structure is relatively fixed, and if different jet impingement structures are needed to study the influence on cooling performance, multiple sets of devices need to be processed, which is costly and inefficient. SUMMARY

[0004] The present application provides a structure-adjustable supercritical pressure carbon-hydrogen fuel jet impingement cooling experimental device to flexibly and efficiently carry out cooling performance research of supercritical pressure carbon-hydrogen fuel under different jet impingement structures, aiming at the problems that the existing jet impingement cooling experimental device cannot meet the experimental requirements of supercritical pressure carbon-hydrogen fuel under high temperature and high pressure, and the fixed structure leads to high experimental cost.

[0005] To achieve the above-mentioned purpose, the technical solutions of the present application are as follows:

[0006] A structure-adjustable supercritical pressure carbon-hydrogen fuel jet impingement cooling experimental device, comprising an upper cover, a sealing gasket, an upper chamber adjusting block, a jet plate, a lower chamber adjusting plate, a lower cover, a fastener, a fixing screw and a temperature measuring element.

[0007] The upper cover is equipped with a flange and an inlet pipe for connecting to a supercritical pressure hydrocarbon fuel supply system. The main body of the upper cover includes an upper cylindrical structure, a middle convex sealing surface, and a lower cuboid structure. The upper cylindrical structure has an inlet temperature measuring hole and an outlet temperature measuring hole inside. The top surface of the upper cylindrical structure is coaxially welded with the inlet and outlet temperature measuring holes and an inlet temperature measuring threaded connector and an outlet temperature measuring threaded connector. Multiple evenly distributed bolt holes are opened around the perimeter. The lower cuboid structure has a first rectangular flow channel groove on the left side. The first rectangular flow channel groove extends vertically upward, penetrates the convex sealing surface and the near end of the upper cylindrical structure, and communicates with the inlet temperature measuring hole. A rectangular first positioning groove is opened on each of the left and right sides of the first rectangular flow channel groove. A second rectangular flow channel groove is opened on the right side of the lower cuboid structure, which communicates with the outlet temperature measuring hole. Two circular countersunk holes are opened on each of the front and rear sides of the lower cuboid structure. A C-shaped upper chamber sealing groove with an opening on the left side is opened at the bottom. First screw holes are opened at the four corners, and a rectangular groove is opened in the center.

[0008] The upper chamber adjustment block is a cuboid structure with a rectangular boss at the top, which is used to cooperate with the rectangular groove at the center of the bottom of the upper cover body. There are two second screw holes on each of the front and rear sides of the upper chamber adjustment block. They are coaxial with the circular countersunk holes on the front and rear sides of the lower cuboid structure of the upper cover body, and are fixed to the bottom of the upper cover by fixing flat-head screws.

[0009] The jet plate is a cuboid structure with a C-shaped upper chamber sealing tenon with an opening on the left side at the top, which is used to mate with the upper chamber sealing groove at the bottom of the main body of the cover. The jet plate has two rectangular second positioning grooves on the left side and a third rectangular flow channel groove on the right side. The jet plate has a fourth rectangular flow channel groove extending along the length direction. The fourth rectangular flow channel groove opens from the left side and extends to the near end on the right side. Its bottom is a jet orifice plate with several jet holes. The jet plate has circular positioning holes at the four corners, which are coaxial with the first screw hole at the bottom of the main body of the cover.

[0010] The lower chamber adjustment plate is a C-shaped structure with an opening on the right side, two rectangular third positioning grooves on the left side, and circular countersunk holes at the four corners. It is coaxial with the first screw hole at the bottom of the upper cover body. The jet plate and the lower chamber adjustment plate are fixedly installed to the bottom of the upper cover body by fixing flat-head screws.

[0011] The lower cover is equipped with a flange and an outlet pipe for connecting to a supercritical pressure hydrocarbon fuel recovery system. The main body of the lower cover is a cylindrical structure with a rectangular experimental chamber in the center. Two rectangular positioning guide rails are provided on the left side of the experimental chamber. The top of the cylindrical structure is provided with a concave sealing surface, and the bottom center is provided with a rectangular heating boss. Multiple evenly distributed bolt holes are provided around the perimeter.

[0012] The assembly formed by the upper cover, upper chamber adjustment block, jet plate, and lower chamber adjustment plate is embedded in the experimental chamber. At the same time, the positioning guide rail on the left side of the experimental chamber is embedded in the positioning groove formed by the first positioning groove, the second positioning groove, and the third positioning groove. The convex sealing surface in the middle of the upper cover body matches the concave sealing surface at the top of the lower cover body. The sealing gasket is placed between the convex sealing surface and the concave sealing surface to achieve a sealing effect.

[0013] The fastener includes multiple studs and nuts for securing the upper and lower covers together.

[0014] The temperature sensing element includes an armored thermocouple, a thermocouple ferrule connector, and a thermocouple wire. The armored thermocouple is installed to the inlet temperature sensing threaded connector and the outlet temperature sensing threaded connector on the top of the upper cover body through the bottom thread of the thermocouple ferrule connector. The thermocouple wire is welded to the heat-receiving boss at the bottom of the lower cover.

[0015] The space between the first rectangular flow channel, the left wall of the upper chamber adjustment block and the experimental chamber constitutes the inlet pressure stabilizing chamber; the space between the bottom surface of the upper chamber adjustment block and the fourth rectangular flow channel constitutes the upper chamber; the space between the bottom surface of the jet plate, the lower chamber adjustment plate and the experimental chamber constitutes the lower chamber; and the space between the second rectangular flow channel, the third rectangular flow channel and the experimental chamber constitutes the outlet pressure stabilizing chamber.

[0016] As an optimization, the upper chamber adjustment block can be replaced with an upper chamber adjustment block of different thicknesses to adjust the height of the upper chamber within the range of 0.5-9mm.

[0017] As an optimization, the jet plate can be replaced with a jet plate with different jet hole diameters to adjust the jet diameter within the range of 0.2-1mm.

[0018] As an optimization, the jet plate can be replaced with a jet plate with different jet hole spacing to adjust the jet spacing to a range of 3 to 20 times the jet hole diameter.

[0019] As an optimization, the jet plate can be replaced with a jet plate in which the jet holes are arranged in a straight or staggered manner.

[0020] As an optimization, the jet plate can be replaced with a jet plate with different jet orifice plate thicknesses to adjust the jet orifice height within the range of 0.5-3mm.

[0021] As an optimization, the jet plate and lower chamber adjustment plate can be replaced with jet plates and lower chamber adjustment plates of different thicknesses to adjust the jet impact height within the range of 1-5mm.

[0022] The working process of the device is as follows: supercritical pressure hydrocarbon fuel enters the inlet pressure stabilizing chamber through the inlet pipe, then changes flow direction to enter the upper chamber, and is sprayed into the lower chamber through the jet holes on the jet plate in the upper chamber to cool the heated wall surface. Then, it changes flow direction to enter the outlet pressure stabilizing chamber, and finally flows out of the experimental device through the outlet pipe. The armored thermocouple is used to measure the inlet and outlet temperatures of the supercritical pressure hydrocarbon fuel in the experimental device, and the thermocouple wire is used to measure the wall temperature of the heated boss.

[0023] The materials selected for the device include: the upper cover flange, inlet pipe, outlet pipe, lower cover flange, inlet temperature measuring threaded connector, outlet temperature measuring threaded connector, and thermocouple ferrule connector are all made of 316L stainless steel. 316L stainless steel offers good strength at high temperatures and is of moderate cost. The upper cover body and lower cover body are made of 310S stainless steel. 310S stainless steel maintains high strength even at extreme high temperatures. The upper chamber adjusting block, jet plate, lower chamber adjusting plate, and fixing screws are all made of 304 stainless steel. 304 stainless steel offers good strength at high temperatures and is relatively inexpensive. The fasteners are made of 35CrMo. 35CrMo offers high temperature resistance and high tensile strength. The sealing gasket is a stainless steel graphite spiral wound gasket with an inner ring. Stainless steel graphite spiral wound gaskets offer high temperature resistance and high pressure resistance. The armored thermocouples and thermocouple wires are all type K thermocouples. The temperature measurement range of type K thermocouples meets the requirements of this experiment.

[0024] The beneficial effects of this invention are:

[0025] This invention provides an adjustable supercritical pressure hydrocarbon fuel jet impact cooling experimental device. Through the design of the upper and lower cover sealing structure, sealing gaskets, and fasteners, the experimental device can meet the jet impact cooling experimental requirements of supercritical pressure hydrocarbon fuel under the conditions of a maximum inlet temperature of 400℃ and a maximum outlet pressure of 6MPa. Through modular design, key parameters such as jet orifice diameter, spacing, arrangement, height, and jet impact height can be adjusted to meet diverse experimental needs. The replaceable structural components have low cost, and the overall device is easy to install, providing strong support for the efficient conduct of supercritical pressure hydrocarbon fuel jet impact cooling experiments. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0027] Figure 2 This is an exploded view of the present invention;

[0028] Figure 3a This is a front view of the top cover of the present invention;

[0029] Figure 3b For the present invention Figure 3a AA cross-section view;

[0030] Figure 4 This is a schematic diagram of the upper chamber adjustment block of the present invention;

[0031] Figure 5 This is a schematic diagram of the jet plate of the present invention;

[0032] Figure 6 This is a schematic diagram of the structure of the lower chamber adjustment plate of the present invention;

[0033] Figure 7a This is a front view of the lower cover of the present invention;

[0034] Figure 7b For the present invention Figure 7a AA cross-section view.

[0035] As shown in the figure:

[0036] 100 Top cover; 101 Flange; 102 Inlet pipe; 103 Top cover body; 104 Bolt hole; 105 Outlet temperature measuring hole; 106 Upper chamber sealing groove surface; 107 Rectangular groove; 108 First screw hole; 109 First positioning groove; 110 Inlet temperature measuring hole; 111 Inlet temperature measuring threaded connector; 112 Outlet temperature measuring threaded connector; 113 Raised sealing surface; 114 Second rectangular flow channel groove; 115 Circular countersunk hole; 116 First rectangular flow channel groove;

[0037] 200 Sealing gasket; 210 Upper chamber adjusting block; 211 Rectangular boss; 212 Second screw hole; 220 Jet plate; 221 Positioning hole; 222 Third rectangular flow channel groove; 223 Upper chamber sealing tenon; 224 Jet hole; 225 Second positioning groove; 226 Jet hole plate; 227 Fourth rectangular flow channel groove; 230 Lower chamber adjusting plate; 231 Circular countersunk hole; 232 Third positioning groove;

[0038] 300 Lower cover; 301 Lower cover body; 302 Outlet pipe; 303 Flange; 304 Bolt hole; 305 Positioning guide rail; 306 Experimental chamber; 307 Concave sealing surface; 308 Heated boss;

[0039] 400 fasteners; 410 studs; 420 nuts;

[0040] 500 fixing screw; 510 fixing flat head screw; 520 fastening flat head screw;

[0041] 600 temperature sensing element; 610 armored thermocouple; 620 thermocouple ferrule connector; 630 thermocouple wire. Detailed Implementation

[0042] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the invention, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present invention.

[0043] In the description of this invention, it should be noted that the terms "upper", "lower", "left", "right", "top", "bottom", "front", "back", "inner", "outer", "around", "four corners", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and should not be construed as limiting this invention.

[0044] like Figure 1 , 2 As shown, the present invention provides an experimental device for supercritical pressure hydrocarbon fuel jet impact cooling with adjustable structure, including an upper cover 100, a sealing gasket 200, an upper chamber adjustment block 210, a jet plate 220, a lower chamber adjustment plate 230, a lower cover 300, fasteners 400, fixing screws 500, and a temperature measuring element 600.

[0045] like Figure 1 As shown in Figure 7, the left side of the upper cover 100 is a flange 101, which is used for process connection with the front-end supercritical pressure hydrocarbon fuel supply device. The left and right sides of the inlet pipe 102 are welded to the flange 101 and the upper cover body 103, respectively. A cylindrical channel is opened inside the upper cover body 103. The channel is coaxial with the inlet pipe 102 and the diameter is the same as the inner diameter of the inlet pipe 102. A rectangular groove 107 is opened at the bottom of the upper cover body 103. The upper rectangular boss 211 of the upper chamber adjustment block 210 is embedded in the rectangular groove 107 to achieve the positioning and sealing effect of the upper chamber adjustment block 210. An upper chamber sealing groove surface 106 is opened at the bottom of the upper cover body 103. The upper chamber sealing tenon surface 223 of the top of the jet plate 220 is embedded in the upper chamber sealing groove surface 106 to achieve the sealing of the contact position. The top surface of the lower chamber adjustment plate 230 is tightly fitted with the bottom surface of the jet plate 220.

[0046] The upper cover body 103 has circular countersunk holes 115 on both the front and rear sides, and the upper chamber adjustment block 210 has second screw holes 212 on both the front and rear sides. The fixing flat head screw 510 passes through the circular countersunk hole 115 and is screwed into the second screw hole 212 to fix the upper chamber adjustment block 210 to the upper cover body 103, thus enabling the replacement of the upper chamber adjustment block 210.

[0047] The top cover body 103 has four first screw holes 108 at its bottom corners, the jet plate 220 has four positioning holes 221 at its corners, and the lower chamber adjustment plate 230 has four round countersunk holes 231 at its corners. The fastening flathead screw 520 passes through the round countersunk holes 231 and the positioning holes 221 and is screwed into the first screw hole 108 to fix the lower chamber adjustment plate 230 and the jet plate 220 to the top cover body 103. Therefore, the jet plate 220 and the lower chamber adjustment plate 230 can be replaced. Special attention should be paid to the installation direction of the three parts. It should be ensured that the first positioning groove 109 on the left side of the top cover body 103, the second positioning groove 225 on the left side of the jet plate 220, and the third positioning groove 232 on the left side of the lower chamber adjustment plate 230 are on the same side after installation.

[0048] The lower cover 300 has a cylindrical body 301 with a rectangular experimental cavity 306 in the middle. The left wall of the experimental cavity 306 is provided with two positioning guide rails 305. The lower cover body 301 has a cylindrical channel inside. The channel is coaxial with the outlet pipe 302 and its diameter is the same as the inner diameter of the outlet pipe 302. The left and right sides of the outlet pipe 302 are welded to the lower cover body 301 and the flange 303, respectively. The flange 303 is used for process connection with the downstream supercritical pressure hydrocarbon fuel cooling and recovery device.

[0049] The assembly formed by the upper cover body 103, the upper chamber adjustment block 210, the jet plate 220, and the lower chamber adjustment plate 230 is embedded in the rectangular experimental cavity 306. The positioning guide rail 305 is embedded in the positioning groove formed by the first positioning groove 109, the second positioning groove 225, and the third positioning groove 232. The inner walls of the experimental cavity 306 are in contact with the side walls of the upper cover body 103, the jet plate 220, and the lower chamber adjustment plate 230, and the bottom surface of the lower chamber adjustment plate 230 is in contact with the bottom surface of the experimental cavity 306.

[0050] The upper cover body 103 has multiple bolt holes 104 evenly distributed around its circumference, and the lower cover body 301 has multiple bolt holes 304 evenly distributed around its circumference. The upper cover 100 and the lower cover 300 are connected by multiple sets of fasteners 400. Therefore, the upper cover 100 and the lower cover 300 can be separated for inspection and replacement of internal experimental parts. Each set of fasteners 400 includes a fastening stud 410 and two nuts 420.

[0051] The convex sealing surface 113 in the middle of the upper cover body 103 and the concave sealing surface 307 at the top of the lower cover body 301 cooperate to form a sealing structure. A sealing gasket 200 is placed between the convex sealing surface 113 and the concave sealing surface 307 to achieve a sealing effect.

[0052] The space formed by the first rectangular flow channel groove 116 on the left side of the upper cover body 103, the left inner wall of the experimental chamber 306, and the left wall of the upper chamber adjustment block 210 constitutes the inlet pressure stabilizing chamber. The top of the inlet pressure stabilizing chamber has an inlet temperature measuring hole 110. The inlet temperature measuring threaded connector 111 is coaxial with the inlet temperature measuring hole 110 and welded to the top of the upper cover body 103. The inlet temperature measuring threaded connector 111 is connected to the bottom of the thermocouple ferrule connector 620 by threads to achieve a seal at the connection. After the metal protective sleeve of the armored thermocouple 610 is passed through the movable ferrule at the top of the thermocouple ferrule connector 620, the movable ferrule is tightened to achieve a seal at the connection. The metal protective sleeve of the armored thermocouple 610 is further passed through the inlet temperature measuring hole 110 and finally inserted into the middle of the inlet pressure stabilizing chamber to achieve the measurement of the inlet temperature of the supercritical pressure hydrocarbon fuel in the experimental device.

[0053] The space formed between the bottom surface of the upper chamber adjustment block 210 and the fourth rectangular flow channel groove 227 in the middle of the jet plate 220 constitutes the upper chamber.

[0054] The space formed by the bottom surface of the jet plate 220, the bottom surface of the experimental chamber 306, and the lower chamber adjustment plate 230 constitutes the lower chamber.

[0055] The space formed by the second rectangular flow channel 114 on the right side of the upper cover body 103, the third rectangular flow channel 222 on the right side of the jet plate 220, and the right wall of the experimental chamber 306 constitutes the outlet pressure stabilizing chamber. An outlet temperature measuring hole 105 is opened at the top of the outlet pressure stabilizing chamber. The outlet temperature measuring threaded connector 112 is coaxial with the outlet temperature measuring hole 105 and welded to the top of the upper cover body 103. The outlet temperature measuring threaded connector 112 is connected to the bottom of the thermocouple ferrule connector 620 by threads to achieve a seal at the connection. After the metal protective sleeve of the armored thermocouple 610 is passed through the movable ferrule at the top of the thermocouple ferrule connector 620, the movable ferrule is tightened to achieve a seal at the connection. The metal protective sleeve of the armored thermocouple 610 is further passed through the outlet temperature measuring hole 105 and finally inserted into the middle of the outlet pressure stabilizing chamber to achieve the measurement of the outlet temperature of the supercritical pressure hydrocarbon fuel in the experimental device.

[0056] The bottom of the lower cover body 301 is provided with a rectangular heating boss 308. The rectangular heating boss 308 is used to contact the experimental heating equipment to simulate the thermal environment of the scramjet engine wall. Multiple thermocouple wires 630 are fixed on the surface of the heating boss by spot welding to realize the measurement of the temperature of the heated wall of the experimental equipment.

[0057] It should be emphasized that the experimental heating equipment is not within the scope of this invention. In actual use, you can choose a suitable heating equipment yourself, but you should pay attention to leaving space for the thermocouple wire 630 to pass through.

[0058] It should be emphasized that both the armored thermocouple 610 and the thermocouple wire 630 need to be connected to a data acquisition device to realize the acquisition and recording of temperature data. The relevant data acquisition and recording device is not shown in the accompanying drawings of this invention.

[0059] During the experiment, supercritical pressure hydrocarbon fuel enters the cylindrical channel inside the upper cover body 103 through the inlet pipe 102, then changes flow direction to enter the inlet pressure stabilizing chamber, and then further changes flow direction to enter the upper chamber. The supercritical pressure hydrocarbon fuel is injected into the lower chamber through the jet holes 224 on the jet plate 220 to cool the heated wall surface 308, then changes flow direction to enter the outlet pressure stabilizing chamber, and finally the heated supercritical pressure hydrocarbon fuel flows out of the experimental equipment through the cylindrical channel inside the lower cover body 301 and the outlet pipe 302.

[0060] The height parameter of the upper chamber can be adjusted by replacing the upper chamber adjustment block 210 with different thicknesses.

[0061] In this embodiment, the adjustable range of the upper chamber height is 0.5-9mm.

[0062] The jet diameter parameter can be adjusted by replacing the jet plate 220 with different jet orifice diameters 224.

[0063] In this embodiment, the adjustable range of the jet diameter is 0.2-1mm.

[0064] The jet spacing parameter can be adjusted by replacing the jet plate 220 with different jet hole spacings.

[0065] In this embodiment, the adjustable range of the jet spacing is 3-20 times the jet orifice diameter.

[0066] The jet plate 220 can be replaced by a jet plate 220 in which the jet holes 224 are arranged in a straight or staggered manner.

[0067] The jet orifice height parameter can be adjusted by replacing the jet plate 220 with a jet plate 226 of different thicknesses.

[0068] In this embodiment, the adjustable range of the jet hole height is 0.5-3mm.

[0069] The jet impact height parameter can be adjusted by replacing the jet plate 220 and the lower chamber adjustment plate 230 with different thicknesses.

[0070] In this embodiment, the adjustable range of the jet impact height is 1-5mm.

[0071] It is particularly important to note that the sum of the thickness of the lower cuboid structure of the upper cover body 103, the thickness of the jet plate 220, and the thickness of the lower chamber adjustment plate 230 should be consistent with the sum of the thickness of the experimental chamber 306 and the thickness of the sealing gasket 200 after compression, in order to prevent sealing failure.

[0072] The flange 101, inlet pipe 102, outlet pipe 302, flange 303, inlet temperature measuring threaded connector 111, outlet temperature measuring threaded connector 112, and thermocouple ferrule connector 620 are all made of 316L stainless steel. 316L stainless steel offers good strength at high temperatures and is of moderate cost. The upper cover body 103 and lower cover body 301 are both made of 310S stainless steel. 310S stainless steel maintains high strength even at extreme high temperatures. The upper chamber adjusting block 210, jet plate 220, lower chamber adjusting plate 230, and fixed flat head are also included. Screw 510 and fastening flathead screw 520 are both made of 304 stainless steel. 304 stainless steel has good strength at high temperatures and is relatively inexpensive. Fastening stud 410 and nut 420 are made of 35CrMo. 35CrMo has the advantages of high temperature resistance and high tensile strength. Sealing gasket 200 is a stainless steel graphite spiral wound gasket with an inner ring. Stainless steel graphite spiral wound gasket has the advantages of high temperature resistance and high pressure resistance. Armored thermocouple 610 and thermocouple wire 630 are both type K thermocouples. The temperature measurement range of type K thermocouples meets the requirements of this experiment.

[0073] In this embodiment, the diameters of the upper cover body 103 and the lower cover body 301 are both 220mm. The thickness of the cylindrical section of the upper cover body 103 is 29.5mm, and the thickness of the cylindrical section of the lower cover body 301 is 32mm. The lower cuboid structure of the upper cover body 103 has a side length of 51mm and a thickness of 23mm. The experimental cavity 306 has a side length of 51mm and a thickness of 28mm. The thickness between the bottom surface of the experimental cavity 306 and the bottom surface of the cylindrical section of the lower cover body 301 is 5mm. The diameter of the convex sealing surface 113 is 109mm. The outer diameter of the concave sealing surface 307 is 122mm, the inner diameter is 110mm, and the thickness is 4mm. The diameter of bolt holes 104 and 304 is 26mm, the center circle diameter of bolt holes 104 and 304 is 170mm, and there are 8 bolt holes 104 and 304. The fastening studs 410 and nuts 420 are both M24. The side lengths of the heated bosses 308 are 32mm and 33mm, and the thickness is 2mm.

[0074] This embodiment can meet the requirements of jet impact cooling experiments for supercritical pressure hydrocarbon fuels under conditions of a maximum inlet temperature of 400°C and a maximum outlet pressure of 6MPa. Furthermore, jet impact cooling experiments for supercritical pressure hydrocarbon fuels under different jet impact structures can be achieved by replacing the upper chamber adjustment block 210, jet plate 220, and lower chamber adjustment plate 230 with different structural parameters.

[0075] The above-described embodiments are merely illustrative of the implementation methods of the present invention, but should not be construed as limiting the scope of the present invention. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of the present invention, and these modifications and improvements all fall within the protection scope of the present invention.

Claims

1. An experimental device for supercritical pressure hydrocarbon fuel jet impingement cooling with adjustable structure, characterized in that, It includes an upper cover (100), a sealing gasket (200), an upper chamber adjusting block (210), a jet plate (220), a lower chamber adjusting plate (230), a lower cover (300), fasteners (400), fixing screws (500), and a temperature sensing element (600); The upper cover (100) is welded together from a flange (101), an inlet pipe (102), and an upper cover body (103). The upper cover body (103) includes an upper cylindrical structure, a middle convex sealing surface (113), and a lower cuboid structure. The upper cylindrical structure has an inlet temperature measuring hole (110) and an outlet temperature measuring hole (105) inside. Its top surface is coaxially welded with the inlet temperature measuring hole (110) and the outlet temperature measuring hole (105) to the threaded connectors for inlet and outlet temperature measuring holes (111 and 112). Multiple evenly distributed bolt holes (104) are opened in the circumference. The lower cuboid structure has a first rectangular flow channel groove (116) on the left side. The first rectangular flow channel groove (116) extends vertically upward, penetrates the convex sealing surface (113) and the near end of the upper cylindrical structure, and communicates with the inlet temperature measuring hole (110). The first rectangular flow channel groove (116) has a rectangular first positioning groove (109) on each of its left and right sides. The lower cuboid structure has a second rectangular flow channel groove (114) on its right side, which communicates with the outlet temperature measuring hole (105). The lower cuboid structure has two circular countersunk holes (115) on each of its front and rear sides. The bottom has a C-shaped upper chamber sealing groove surface (106) with an opening on the left side. The four corners have first screw holes (108), and the center has a rectangular groove (107). The upper chamber adjustment block (210) has a cuboid structure with a rectangular boss (211) on the top and two second screw holes (212) on the front and rear sides. The jet plate (220) is a cuboid structure with a C-shaped upper chamber sealing tenon (223) with an opening on the left side at the top. There are two rectangular second positioning grooves (225) on the left side and a third rectangular flow channel groove (222) on the right side. The jet plate (220) is provided with a fourth rectangular flow channel groove (227) extending along the length direction. The fourth rectangular flow channel groove (227) opens from the left side and extends to the near end on the right side. Its bottom is a jet orifice plate (226). There are several jet holes (224) on the jet orifice plate (226). There are circular positioning holes (221) at the four corners of the jet plate (220). The lower chamber adjustment plate (230) is a C-shaped structure with an opening on the right side, two rectangular third positioning grooves (232) on the left side, and circular countersunk holes (231) at the four corners. The lower cover is welded from the lower cover body (301), the outlet pipe (302) and the flange (303). The lower cover body (301) is a cylindrical structure with a rectangular experimental cavity (306) in the center. Two rectangular positioning guide rails (305) are provided on the left side of the experimental cavity (306). The top of the cylindrical structure is provided with a concave sealing surface (307), and the bottom center is provided with a rectangular heating boss (308). Multiple evenly distributed bolt holes (304) are opened around the perimeter. The fastener (400) includes a plurality of fastening studs (410) and nuts (420); The fixing screw (500) includes a plurality of fixing flat head screws (510) and fastening flat head screws (520); The temperature sensing element (600) includes an armored thermocouple (610), a thermocouple ferrule connector (620), and multiple thermocouple wires (630).

2. The experimental apparatus for supercritical pressure hydrocarbon fuel jet impingement cooling with adjustable structure according to claim 1, characterized in that, The rectangular boss (211) on the top of the upper chamber adjustment block (210) is embedded in the rectangular groove (107) at the bottom of the upper cover body (103). The second screw holes (212) on the front and rear sides of the upper chamber adjustment block (210) are coaxial with the circular countersunk holes (115) on the front and rear sides of the lower cuboid structure of the upper cover body (103) and are fixed by fixing flat head screws (510).

3. The experimental apparatus for supercritical pressure hydrocarbon fuel jet impingement cooling with adjustable structure according to claim 1, characterized in that, The upper chamber sealing tenon (223) at the top of the jet plate (220) is embedded in the upper chamber sealing groove (106) at the bottom of the upper cover body (103). The top surface of the lower chamber adjusting plate (230) is close to the bottom surface of the jet plate (220). The circular positioning holes (221) at the four corners of the jet plate (220) and the circular countersunk holes (231) at the four corners of the lower chamber adjusting plate (230) are coaxial with the first screw holes (108) at the four corners of the bottom of the upper cover body (103) and are installed at the bottom of the upper cover body (103) by fastening flat-head screws (520).

4. The experimental apparatus for supercritical pressure hydrocarbon fuel jet impingement cooling with adjustable structure according to claim 1, characterized in that, The assembly consisting of the upper cover (100), the upper chamber adjustment block (210), the jet plate (220), and the lower chamber adjustment plate (230) is embedded in the experimental chamber (306) of the lower cover (300). The positioning guide rail (305) on the left side of the experimental chamber (306) is embedded in the positioning groove formed by the first positioning groove (109), the second positioning groove (225), and the third positioning groove (232). The convex sealing surface (113) in the middle of the upper cover body (103) cooperates with the concave sealing surface (307) at the top of the lower cover body (301). The sealing gasket (200) is placed between the convex sealing surface (113) and the concave sealing surface (307) to play a sealing role.

5. The experimental apparatus for supercritical pressure hydrocarbon fuel jet impingement cooling with adjustable structure according to claim 1, characterized in that, The upper cover (100) and the lower cover (300) are fixedly connected by multiple fastening studs (410) and nuts (420); the flange (101), inlet pipe (102), outlet pipe (302), flange (303), inlet temperature measuring threaded connector (111), outlet temperature measuring threaded connector (112), and thermocouple ferrule connector (620) are all made of 316L stainless steel; the upper cover body (103) and the lower cover body (301) are both made of 310S stainless steel; the upper chamber adjusting block (210), jet plate (220), lower chamber adjusting plate (230), and fixing screw (500) are all made of 304 stainless steel; the fastener (400) is made of 35CrMo; the sealing gasket (200) is a stainless steel graphite spiral wound gasket with an inner ring; and the armored thermocouple (610) and thermocouple wire (630) are both K-type thermocouples.

6. The experimental apparatus for supercritical pressure hydrocarbon fuel jet impingement cooling with adjustable structure according to claim 1, characterized in that, The armored thermocouple (610) is installed at the bottom of the thermocouple ferrule connector (620) to the inlet temperature measuring threaded connector (111) and the outlet temperature measuring threaded connector (112) on the top of the upper cover body (103) via the bottom thread of the thermocouple ferrule connector (620) for measuring the inlet and outlet temperatures of the supercritical pressure hydrocarbon fuel in the device. The thermocouple wire (630) is welded to the heated boss (308) for measuring its wall temperature.

7. The experimental apparatus for supercritical pressure hydrocarbon fuel jet impingement cooling with adjustable structure according to claim 1, characterized in that, The space between the first rectangular flow channel (116), the left side wall of the upper chamber adjustment block (210), and the experimental chamber (306) constitutes the inlet pressure stabilizing chamber. The space between the bottom surface of the upper chamber adjustment block (210) and the fourth rectangular flow channel (227) constitutes the upper chamber. The space between the bottom surface of the jet plate (220), the lower chamber adjustment plate (230), and the experimental chamber (306) constitutes the lower chamber. The space between the second rectangular flow channel (114), the third rectangular flow channel (222), and the experimental chamber (306) constitutes the outlet pressure stabilizing chamber.

8. The experimental apparatus for supercritical pressure hydrocarbon fuel jet impingement cooling with adjustable structure according to claim 1, characterized in that, The upper chamber adjustment block (210) can be replaced with an upper chamber adjustment block (210) of different thicknesses to adjust the height of the upper chamber within the range of 0.5-9mm; the jet plate (220) can be replaced with a jet plate (220) of different jet hole (224) diameters to adjust the jet diameter within the range of 0.2-1mm; the jet plate (220) energy consumption can be replaced with a jet plate (220) of different jet hole (224) spacings to adjust the jet spacing within the range of 3 to 20 times the jet hole diameter.

9. The experimental apparatus for supercritical pressure hydrocarbon fuel jet impingement cooling with adjustable structure according to claim 1, characterized in that, The jet plate (220) can be replaced by a jet plate (220) with jet holes (224) arranged in a straight or staggered manner; the jet plate (220) can be replaced by a jet plate (220) with different thicknesses of jet hole plates (225) to adjust the height of the jet holes within the range of 0.5-3mm.

10. The experimental apparatus for supercritical pressure hydrocarbon fuel jet impingement cooling with adjustable structure according to claim 1, characterized in that, The jet plate (220) and the lower chamber adjustment plate (230) can be replaced with jet plates (220) and lower chamber adjustment plates (230) of different thicknesses to adjust the jet impact height within the range of 1-5mm.

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