CN218644344U - Explosion-proof turbine box with cooling cavity - Google Patents
Explosion-proof turbine box with cooling cavity Download PDFInfo
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- CN218644344U CN218644344U CN202221803426.7U CN202221803426U CN218644344U CN 218644344 U CN218644344 U CN 218644344U CN 202221803426 U CN202221803426 U CN 202221803426U CN 218644344 U CN218644344 U CN 218644344U
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- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
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Abstract
The utility model discloses an explosion-proof turbine case with a cooling cavity, which comprises a turbine case body, wherein a gas flow channel and a cooling diversion cavity are arranged inside the turbine case body, the gas flow channel is a cross section cavity which changes along with the change of the angle, and the cooling diversion cavity comprises a branch flow channel which is arranged outside the gas flow channel along the bending direction of the gas flow channel and a communicating flow channel which is arranged at the inlet position of the gas flow channel and is used for communicating the branch flow channel end to end; the turbine box body is also provided with a cooling liquid inlet, a cooling liquid outlet and two casting process holes, wherein the cooling liquid inlet is communicated with the cooling diversion cavity, the cooling liquid outlet and the two casting process holes are arranged at intervals through the casting process holes, and the cooling liquid inlet is positioned below the cooling liquid outlet. The utility model discloses a set up cooling water conservancy diversion chamber, the lower extreme is intake the water flow direction design of upper end play water and can be made the coolant liquid effectively be full of the cavity, takes away the heat that high temperature waste gas heat-conduction and produced to reach for turbine case and valve drive assembly fully cooled's effect, satisfy explosion-proof environment operation requirement.
Description
Technical Field
The utility model relates to a waste gas turbocharging technical field especially relates to an explosion-proof turbine case of area cooling cavity.
Background
China is a big country for coal use and mining, and nowadays, the coal mining industry is accelerated to approach to science and technology mining, backward mining equipment is gradually eliminated, and an explosion-proof diesel engine is gradually becoming the dominant force of underground operation. With the continuous upgrade of national emission standards, the natural air suction explosion-proof diesel engine can not meet the requirements of regulations, so that the adoption of an explosion-proof turbocharging technology is the most economical and effective measure for improving the performance of the engine and meeting the emission requirements.
According to the general technical condition regulation of the mining explosion-proof diesel engine in China, the surface temperature of any part of the explosion-proof diesel engine is not more than 150 ℃, the heat dissipation effect of the turbine box of the conventional turbocharger is poor, and the surface temperature is easy to be overhigh.
In view of the above, it is necessary to provide an explosion-proof turbine box with a cooling chamber to solve the above-mentioned drawbacks.
SUMMERY OF THE UTILITY MODEL
A primary object of the utility model is to provide a take explosion-proof turbine case of cooling chamber aims at solving the poor problem of radiating effect of current turbine case.
In order to achieve the purpose, the utility model provides an explosion-proof turbine box with a cooling cavity, which comprises a turbine box body and a sealing element, wherein a gas flow channel and a cooling diversion cavity are arranged inside the turbine box body, the gas flow channel is a cross section cavity which changes along with the change of an angle, and the cooling diversion cavity comprises a branch flow channel which is arranged outside the gas flow channel along the bending direction of the gas flow channel in a surrounding way and a communicating flow channel which is arranged at the inlet position of the gas flow channel and is used for communicating the branch flow channel end to end;
the turbine box body is also provided with a cooling liquid inlet, a cooling liquid outlet and two casting process holes, wherein the cooling liquid inlet is communicated with the cooling diversion cavity; the sealing elements and the casting process holes are arranged in a one-to-one correspondence mode.
Preferably, the coolant inlet is close to the inlet of the gas channel, the communication channel is circumferentially arranged outside the gas channel along the circumferential direction of the gas channel, the output end of the coolant inlet is respectively communicated with the head end of the tributary channel and the first end of the communication channel, the second end of the communication channel is communicated with the tail end of the tributary channel, the coolant inlet and the coolant outlet are diagonally arranged relatively, and the coolant outlet is communicated with the middle of the tributary channel.
Preferably, the specific arrangement position of the cooling diversion cavity is from the depth of 5-9 mm of the flange end surface of the gas inlet of the turbine box, and is stopped at the depth of 11-15 mm of the flange end surface of the gas outlet of the turbine box along the rotation direction of the gas flow channel.
Preferably, the cooling liquid inlet and the cooling liquid outlet are both provided with transition joints for connecting with a water circulation system of the engine.
Preferably, the cooling guide cavity has a divergent structure with a channel cross section from the cooling liquid inlet to the cooling liquid outlet increasing with increasing angle.
Preferably, the turbine box body is provided with a shaft sleeve hole for assembling with the valve transmission assembly.
Preferably, the internal cavity of the gas flow passage has a convergent structure with a passage cross-sectional area from the turbine case gas inlet to the turbine case gas outlet decreasing with increasing angle.
Preferably, the turbine case gas inlet is matched to an exhaust gas outlet of the engine.
Compared with the prior art, the utility model provides a take explosion-proof turbine case of cooling chamber has following beneficial effect:
the utility model provides a take explosion-proof turbine case of cooling chamber, through design cooling water conservancy diversion chamber, make the coolant liquid flow through cooling water conservancy diversion chamber, the lower extreme is intake the water flow direction design of upper end play water and can be made the coolant liquid effectively be full of the cavity, take away the heat that high temperature waste gas heat-conduction and produce, can effectively reduce turbine case surface temperature, improve explosion-proof turbine case's security, satisfy explosion-proof environment operation requirement, still can effectively reduce the temperature of axle sleeve and gassing valve component, eliminate the thermal energy phenomenon, avoid the risk of valve drive assembly jamming, improve turbo charger's complete machine reliability.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
Fig. 1 is an overall structural diagram of an explosion-proof turbine box according to an embodiment of the present invention;
fig. 2 is one of schematic internal cross-sectional views of an explosion-proof turbine case according to an embodiment of the present invention;
fig. 3 is a second schematic sectional view of the interior of the explosion-proof turbine box according to an embodiment of the present invention;
the reference numbers indicate:
an explosion-proof turbine case 100; a turbine case body 200; a gas flow passage 210; cooling the baffle cavity 220; a branch flow channel 221; a communication flow passage 222; a coolant inlet 223; a coolant outlet 224; a casting process bore 225; a turbine case gas inlet 230; a turbine case gas outlet 240; a boss bore 250; a bleed valve aperture 260; deflate valve gate plus port 270.
The purpose of the present invention is to provide a novel and improved method and apparatus for operating a computer.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by a person skilled in the art without making creative efforts belong to the protection scope of the present invention.
It should be noted that all the directional indicators (such as up, down, left, right, front, back, 8230; \8230;) in the embodiments of the present invention are only used to explain the relative position relationship between the components, the motion situation, etc. in a specific posture (as shown in the attached drawings), and if the specific posture is changed, the directional indicator is changed accordingly.
Furthermore, the descriptions in the present application related to "first", "second", etc. are for descriptive purposes only and are not to be construed as indicating or implying relative importance or to imply that the number of technical features indicated are implicitly being indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions in the embodiments may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the combination of the technical solutions should not be considered to exist, and is not within the protection scope of the present invention.
Referring to fig. 1 to 3, the present invention provides an explosion-proof turbine box 100 with a cooling chamber, including a turbine box body 200 and a sealing member (not shown), wherein a gas flow channel 210 and a cooling diversion cavity 220 are disposed inside the turbine box body 200, the gas flow channel 210 is a cross-sectional cavity that changes with angle change, the cooling diversion cavity 220 includes a branch flow channel 221 disposed outside the gas flow channel 210 along a bending direction of the gas flow channel 210, and a communication flow channel 222 disposed at an inlet position of the gas flow channel 210 for communicating the branch flow channel 221 end to end;
the turbine box body 200 is further provided with a cooling liquid inlet 223, a cooling liquid outlet 224 and two casting process holes 225, wherein the cooling liquid inlet 223 and the cooling liquid outlet 224 are communicated with the cooling diversion cavity 220, the cooling liquid inlet 223 and the cooling liquid outlet 224 are arranged at intervals through the casting process holes 225, and the cooling liquid inlet 223 is located below the cooling liquid outlet 224; the sealing elements are arranged in one-to-one correspondence with the casting process holes 225.
Specifically, the gas channel 210 is a cross-sectional cavity that changes with the change of angle, the cooling diversion cavity 220 is disposed outside the gas channel 210, the cooling diversion cavity 220 includes a branch channel 221 and a communication channel 222, the communication channel 222 is mainly used for communicating the branch channel 221 end to end, two branches can be formed when the cooling liquid enters, the two branches respectively go up from the head end and the tail end of the branch channel 221, and the cooling liquid flows out through a cooling liquid outlet 224 so as to ensure that the cooling liquid is effectively filled in the cooling diversion cavity 220, and the turbine box body 200 and a valve transmission assembly (not shown) connected with the turbine box body 200 are sufficiently cooled.
In detail, referring to fig. 1, a bleed valve hole 260 and a bleed valve adding hole 270 are formed in a turbine box body 200, a cooling guide cavity 220 is provided with a cooling liquid inlet 223 and a cooling liquid outlet 224, the cooling liquid inlet 223 is arranged at the lower end, the cooling liquid outlet 224 is arranged at the upper end, two casting process holes 225 are further formed in the cooling guide cavity 220, the two casting process holes 225 are arranged in a staggered and spaced mode with the cooling liquid inlet 223 and the cooling liquid outlet 224, the casting process holes 225 are used for discharging sand in the cavity after a shell of the turbine box body 200 is formed, and meanwhile, a sealing piece is arranged inside the casting process holes 225 and used for sealing the casting process holes.
It should be noted that the casting process hole 225 has the same aperture as the coolant inlet 223 and the coolant outlet 224, the size of the sealing element is matched with the aperture, the flow rate of water entering from the coolant inlet 223 is the same as the flow rate of water entering from the casting process hole 225 at the lower end under the same water inlet pressure, and in practical use, the casting process hole 225 at the lower end can be used as the inlet of the coolant, the casting process hole 225 at the upper end can be used as the outlet of the coolant, and the inlet and the outlet of the coolant can be used as the casting process holes; the inlet of the cooling liquid is only required to be located at the lower end, the outlet of the cooling liquid is located at the upper end, the effect that the cooling liquid enters water from the lower end and exits water from the upper end can be achieved, and the inlet and the outlet of the specific cooling liquid can be selected according to actual conditions.
It should be understood that, by designing the cooling diversion cavity 220, the water circulation system (not shown) of the engine is connected through a pipeline, so that the cooling liquid flows through the cooling diversion cavity 220, the water flow direction design of the water flowing from the lower end of the water inlet to the upper end of the water outlet can enable the cooling liquid to be effectively filled in the cavity, the heat generated by the heat conduction of high-temperature waste gas can be taken away, the temperature of the outer surface of the explosion-proof turbine box 100 can be effectively reduced, the design requirement of < 150 ℃ provided by the specification is met, the safety of the explosion-proof turbine box 100 is improved, the use requirement of an explosion-proof environment is met, the temperature of a shaft sleeve and an air bleeding valve component can be effectively reduced, the thermal expansion phenomenon is eliminated, the clamping risk of the valve transmission component is avoided, and the overall reliability of the turbocharger is improved.
As a preferred embodiment of the present invention, the coolant inlet 223 is close to the inlet position of the gas flow channel 210, the communication flow channel 222 is along the circumference of the gas flow channel 210 is surrounded and located outside the gas flow channel 210, the output end of the coolant inlet 223 is respectively communicated with the head end of the branch flow channel 221 and the first end of the communication flow channel 222, the second end of the communication flow channel 222 is communicated with the tail end of the branch flow channel 221, the coolant inlet 223 is relatively arranged along the slant with the coolant outlet 224, the coolant outlet 224 is communicated with the middle of the branch flow channel 221.
In detail, the cooling liquid inlet 223 is disposed at a position close to the inlet of the gas flow channel 210, the communication flow channel 222 is disposed at the inlet of the gas flow channel 210 and surrounds the gas flow channel 210, the output end of the cooling liquid inlet 223 refers to one end of the cooling liquid entering and flowing out from the inlet, the head end of the branch flow channel 221 refers to one end of the branch flow channel 221 located at the cooling liquid inlet 223, the tail end of the branch flow channel 221 refers to one end of the branch flow channel 221 farthest from the head end in the water flow direction, i.e., the end opposite to the head end, and the output end of the cooling liquid inlet 223 is communicated with both the head end of the branch flow channel 221 and the first end of the communication flow channel 222; that is, a first end of the communication channel 222 communicates with the coolant inlet 223, and a second end of the communication channel 222 communicates with the rear end of the branch channel 221.
Therefore, when the coolant enters from the coolant inlet 223, the coolant flows to the leading end of the branch flow channel 221 and also flows to the communication flow channel 222, and the coolant flows to the trailing end of the branch flow channel 221 through the communication flow channel 222, that is, the coolant is collected and flowed out from the leading end and the trailing end of the branch flow channel 221 toward the outlet direction.
It should be noted that the outlet of the cooling liquid is arranged at the upper end of the turbine box body 200 and is located in the middle of the branch flow channel 221, and the cooling guide cavity 220 is filled with the cooling liquid effectively due to the structure that the cooling guide cavity 220 is arranged in the lower portion and the upper portion, so that the effect of fully cooling the explosion-proof turbine box 100 and the valve transmission assembly is achieved.
As a preferred embodiment of the present invention, the specific layout position of the cooling diversion cavity 220 is the flange end face depth 5-9 mm from the turbine box gas inlet 230, and follows the rotation direction of the gas flow channel 210 is stopped at the flange end face depth 11-15 mm from the turbine box gas outlet 240.
In detail, the turbine box gas inlet 230 is a gas inlet arranged on the turbine box body 200, the turbine box gas outlet 240 is a gas outlet arranged on the turbine box body 200, and the specific position of the cooling diversion cavity 220 can be set according to actual conditions, in this embodiment, the cooling diversion cavity 220 is arranged between the gas flow passage 210 and the outer wall of the turbine box body 200, starting from the depth of the flange end face of the turbine box gas inlet 230 of 5-9 mm, and ending at the depth of the flange end face of the turbine box gas outlet 240 of 11-15 mm along the rotation direction of the gas flow passage 210, so as to facilitate the entering of cooling liquid, and effectively and fully cool the turbine box body 200.
Further, a transition joint (not shown) for connecting with an engine water circulation system is arranged on each of the cooling liquid inlet 223 and the cooling liquid outlet 224.
It should be noted that coolant inlet 223 and coolant outlet 224 are connected with engine water circulation pipeline through transition joint, set up transition joint and play a linking effect, can improve the leakproofness, prevent to reveal, and it is very convenient simultaneously in the assembling process, the coolant inlet 223 of being convenient for and coolant outlet 224 and engine water circulation system's being connected make coolant liquid circulation flow through cooling water conservancy diversion chamber 220.
As a preferred embodiment of the present invention, the cooling guide cavity 220 has a divergent structure with a channel cross section from the cooling fluid inlet 223 to the cooling fluid outlet 224 increasing with an increase of the angle.
It should be understood that the specific type of the cooling guiding cavity 220 can be set according to actual needs, in this embodiment, the cooling guiding cavity 220 is set from the cooling liquid inlet 223 to the cooling liquid outlet 224, the channel cross section of the cooling guiding cavity is in a divergent structure increasing with the increase of the angle, and the cooling liquid inlet 223 is set at the lower end and the cooling liquid outlet 224 is set at the upper end, and this structure can enhance the cooling effect on the turbine box body 200, and improve the safety and reliability of use.
As a preferred embodiment of the present invention, the turbine box body 200 is provided with a shaft sleeve hole 250 for assembling with the valve transmission assembly.
It should be noted that the shaft sleeve hole 250 is formed in the turbine box body 200, the shaft sleeve hole 250 is used for assembling the valve transmission assembly into the shaft sleeve hole, the shaft sleeve is assembled into the shaft sleeve hole firstly in the assembling sequence, then the valve transmission assembly is assembled into the shaft sleeve, and the shaft sleeve and the valve transmission assembly are coaxially assembled.
It should be understood that, the position of the shaft sleeve hole 250 is arranged near the cooling diversion cavity 220, when the cooling liquid enters the cooling diversion cavity 220, the outer wall of the shaft sleeve hole 250 starts to be cooled, and then the cooling liquid is transmitted to the shaft sleeve and then transmitted to the valve transmission assembly, and then the outer wall of the shaft sleeve hole 250 is subjected to osmotic cooling from outside to inside, so that the temperature of the shaft sleeve and the temperature of the air bleeding valve assembly are effectively reduced, the thermal expansion phenomenon is eliminated, the jamming risk of the valve transmission assembly is avoided, and the overall reliability of the turbocharger is improved.
Further, the inner cavity of the gas flow channel 210 has a convergent structure in which the cross-sectional area of the channel from the turbine case gas inlet 230 to the turbine case gas outlet 240 decreases with increasing angle.
In detail, the sectional area of the inner cavity of the gas flow channel 210 changes with the change of the angle, the area of the sectional area is continuously reduced with the increase of the rotation angle, the change curve of the sectional area is arc-shaped, a convergent gas flow channel 210 is formed, the exhaust gas enters the gas flow channel 210 from the gas inlet 230 of the turbine box, the gas is continuously discharged because the gas is continuously discharged, the sectional area of the gas flow channel 210 into which the gas enters is continuously reduced, the exhaust gas is compressed, the compressed gas has high heat energy and kinetic energy and also has high pressure, and the compressed gas is treated by a device at the center of the turbine box body 200, so the exhaust gas discharged by the engine is fully utilized, and the utilization rate of the fuel is improved.
As a preferred embodiment of the present invention, the turbine case gas inlet 230 is matched with an exhaust gas outlet (not shown) of the engine. It should be understood that when the supercharger is operated, high-temperature and high-pressure gas discharged from the exhaust manifold of the engine flows into the gas flow passage 210 through the turbine case gas inlet 230, and the turbine case gas inlet 230 is disposed to be matched with the exhaust gas outlet of the engine, so that assembly is facilitated, leakage of exhaust gas is prevented, and utilization of exhaust gas is maximized.
The above is only the preferred embodiment of the present invention, and not the scope of the present invention, all the equivalent structures or equivalent flow changes made by the contents of the specification and the drawings or the direct or indirect application in other related technical fields are included in the patent protection scope of the present invention.
Claims (7)
1. An explosion-proof turbine box with a cooling cavity is characterized by comprising a turbine box body and a sealing piece, wherein a gas flow channel and a cooling flow guide cavity are arranged inside the turbine box body, the gas flow channel is a cross section cavity which changes along with the change of an angle, and the cooling flow guide cavity comprises a branch flow channel which is arranged outside the gas flow channel in a surrounding manner along the bending direction of the gas flow channel and a communication flow channel which is arranged at the inlet position of the gas flow channel and is used for communicating the branch flow channel end to end;
the turbine box body is also provided with a cooling liquid inlet, a cooling liquid outlet and two casting process holes, wherein the cooling liquid inlet is communicated with the cooling diversion cavity, the cooling liquid outlet and the cooling liquid inlet are arranged at intervals through the casting process holes, the cooling liquid inlet is positioned below the cooling liquid outlet, and the cavity can be effectively filled with cooling liquid due to the design of the water flow direction of water flowing from the lower end of the water inlet to the upper end of the water outlet;
the sealing elements and the casting process holes are arranged in a one-to-one correspondence manner;
the cooling liquid inlet is close to the inlet position of the gas flow channel, the communicating flow channel is arranged outside the gas flow channel in a surrounding mode along the circumferential direction of the gas flow channel, the output end of the cooling liquid inlet is communicated with the head end of the branch flow channel and the first end of the communicating flow channel respectively, the second end of the communicating flow channel is communicated with the tail end of the branch flow channel, the cooling liquid inlet and the cooling liquid outlet are arranged oppositely along the inclined direction, and the cooling liquid outlet is communicated with the middle of the branch flow channel.
2. The explosion-proof turbine box with the cooling chamber as claimed in claim 1, wherein the specific layout position of the cooling diversion cavity is from 5 to 9mm deep from the flange end face of the gas inlet of the turbine box and is stopped at 11 to 15mm deep from the flange end face of the gas outlet of the turbine box along the rotation direction of the gas flow channel.
3. An explosion-proof turbine case with a cooling chamber as claimed in any one of claims 1 to 2 wherein the coolant inlet and the coolant outlet are each provided with a transition joint for connection to an engine water circulation system.
4. The explosion proof turbine case with cooling chamber as recited in any one of claims 1-2, wherein the cooling baffle cavity has a divergent structure with a channel cross section from the cooling fluid inlet to the cooling fluid outlet that increases with increasing angle.
5. An explosion-proof turbine case with a cooling chamber as claimed in any one of claims 1 to 2, wherein the turbine case body is provided with a boss hole for fitting with a valve transmission assembly.
6. The explosion-proof turbine case with the cooling chamber as claimed in any one of claims 1 to 2, wherein the internal cavity of the gas flow passage has a convergent structure in which the cross-sectional area of the passage from the gas inlet of the turbine case to the gas outlet of the turbine case decreases with increasing angle.
7. An explosion proof turbine case with a cooling chamber as claimed in any one of claims 1 to 2 wherein the turbine case gas inlet matches the exhaust gas outlet of the engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221803426.7U CN218644344U (en) | 2022-07-13 | 2022-07-13 | Explosion-proof turbine box with cooling cavity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221803426.7U CN218644344U (en) | 2022-07-13 | 2022-07-13 | Explosion-proof turbine box with cooling cavity |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218644344U true CN218644344U (en) | 2023-03-17 |
Family
ID=85487907
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221803426.7U Active CN218644344U (en) | 2022-07-13 | 2022-07-13 | Explosion-proof turbine box with cooling cavity |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218644344U (en) |
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2022
- 2022-07-13 CN CN202221803426.7U patent/CN218644344U/en active Active
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