WO2020151365A1

WO2020151365A1 - Flow guide pipe structure, non-orbiting scroll member, compressor assembly, and compressor system

Info

Publication number: WO2020151365A1
Application number: PCT/CN2019/121485
Authority: WO
Inventors: 彭楠; 周启明; 陈新虹
Original assignee: 艾默生环境优化技术(苏州)有限公司
Priority date: 2019-01-24
Filing date: 2019-11-28
Publication date: 2020-07-30

Abstract

A flow guide pipe structure for an enhanced vapor injection compressor assembly. The compressor assembly comprises a compressor (1), an enhanced vapor injection fluid source, and an enhanced vapor injection pipe (2) suitable for supplying an enhanced vapor injection fluid from the enhanced vapor injection fluid source to a medium pressure cavity of the compressor (1). The flow guide pipe structure comprises a flow guide pipe (23, 33). The flow guide pipe (23, 33) is provided in the enhanced vapor injection pipe (2) to constitute at least a part of a flow path of the enhanced vapor injection fluid. The flow guide pipe (23, 33) comprises: an inlet and an outlet, the inlet being located on an enhanced vapor injection fluid source side to receive the enhanced vapor injection fluid, and the outlet being located on a medium pressure cavity side to discharge the received enhanced vapor injection fluid; a pipe wall; and blades (233, 2033, 331), the blades (233, 2033, 331) being formed to obliquely extend from the inner wall surface of the pipe wall to the outlet to prevent a pressure pulse in the medium pressure cavity from being transported out.

Description

Draft tube structure, fixed scroll components, compressor components and compressor systems

This application claims the priority of the following Chinese patent applications: the application number submitted to the Chinese Patent Office on January 24, 2019 is 201910066927.8, the name of the invention and creation is "guide tube structure, fixed scroll component, compressor assembly and compressor system ”Chinese patent application; submitted to the Chinese Patent Office on January 24, 2019, the application number is 201920125053.4, and the invention and creation title is “Guide tube structure, fixed scroll components, compressor components and compressor systems”. . The entire contents of these patent applications are incorporated into this application by reference.

Technical field

The present disclosure relates to a draft tube structure, and more specifically, to a draft tube structure for a compressor assembly with jet enthalpy. The present disclosure also relates to a fixed scroll component, and more particularly, to a fixed scroll component with a draft tube structure. The present disclosure also relates to a compressor assembly and a compressor system with a draft tube structure.

Background technique

Existing compressor systems for refrigeration/heating (including air conditioners, refrigeration equipment, etc.) generally include a compressor, a condenser, a main throttling device, and an evaporator that are sequentially connected to form a circulation loop. In the low temperature heating condition, in order to increase the heating capacity, the prior art has adopted the method of increasing the enthalpy by jetting. The jet enthalpy increase pipeline usually includes an economizer with a throttling device, which is connected to the intermediate pressure supplementary port of the compressor to supplement the jet enthalpy increasing fluid to the intermediate pressure cavity of the compressor, thereby increasing the compressor displacement, and then Increase the heating capacity at low temperatures. Similarly, it is also possible to supplement the jet enthalpy fluid (supplement air) to increase the refrigeration capacity of the compressor system.

However, during the operation of the air jet compressor, the air jet enthalpy pipeline is directly connected to the intermediate pressure part of the compressor, such as the scroll cavity of a scroll compressor or the compression cavity of a gear compressor. The internal pressure fluctuates with the movement of the compression component. This pressure fluctuation will cause vibration and noise of the jet enthalpy increasing pipeline, and will cause an impact on the valve on the jet increasing enthalpy pipeline.

Therefore, there is a need to improve the air jet enthalpy increase pipeline to reduce the vibration and noise of the pipeline and reduce the impact on the valve.

Summary of the invention

The purpose of the present disclosure is to solve or at least alleviate at least one of the above-mentioned problems, that is, to provide a device that can reduce or even eliminate the reverse flow of the fluid in the enthalpy-enhancing path of the jet, thereby reducing the vibration and noise of the pipeline and avoiding interference The valve body in the path causes damage.

According to one aspect of the present disclosure, there is provided a draft tube structure for a compressor assembly with jet enthalpy. The compressor assembly includes a compressor, a jet enthalpy-enhancing fluid source, and a jet enthalpy-enhancing fluid source adapted to transfer the jet enthalpy from the jet The enthalpy-increasing fluid source is supplied to the jet enthalpy-increasing pipeline of the intermediate pressure cavity of the compressor. The draft tube structure includes a draft tube. The draft tube is arranged in the jet enthalpy-increasing pipeline to form at least a part of the flow path of the jet enthalpy-increasing fluid Among them, the draft tube includes: an inlet and an outlet, the inlet is located at the side of the jet enthalpy-enhancing fluid to receive the jet-enhancing fluid, and the outlet is located at the side of the medium-pressure cavity to discharge the received jet-enhancing fluid; the tube wall; and vanes. In order to extend obliquely from the inner wall surface of the tube wall toward the outlet, to suppress the pressure pulse in the medium pressure chamber from being transmitted outwards.

Optionally, the blade is formed to extend obliquely in an arc shape or a straight line from the inner wall surface of the pipe wall toward the outlet.

Optionally, when the blade is formed in a circular arc shape, the radius R1 of the blade is in the range of 4mm to 7mm, and when the blade is formed in a straight shape, between the blade and the central axis of the guide tube The formed acute angle α is in the range of 20° to 70°.

Optionally, the blade is formed as a spiral-shaped single integral blade or a spiral-shaped multiple segmented blades.

Optionally, the inner wall surface of the tube wall includes a first inner wall surface and a second inner wall surface disposed oppositely, and the blades are formed as a first blade extending from the first inner wall surface and a second blade extending from the second inner wall surface.

Optionally, there are multiple first blades and second blades, the first blades are arranged in sequence with an equal axial distance L1, and/or the second blades are arranged in sequence with an equal axial distance L1. Preferably, the number of the first blades is three, and the number of the second blades is three.

Optionally, the ratio L1/D between the axial distance L1 and the inner diameter D of the draft tube is in the range of 0.5 to 2.

Optionally, the first blade and the second blade extend toward the central axis of the guide tube such that the free end of the first blade is spaced apart from the free end of the adjacent second blade by a predetermined radial distance L2.

Optionally, the predetermined radial distance L2 is in the range of 0.5 mm to 3 mm.

Optionally, the first blade and the second blade are arranged in sequence with an axial distance L5 between the adjacent first blade and the second blade.

Optionally, the ratio L5/D between the axial distance L5 and the inner diameter D of the draft tube is in the range of 0.5 to 2.

Optionally, the first blade and the second blade extend toward the central axis of the guide tube such that the free end of the first blade and the free end of the second blade extend beyond the central axis of the guide tube, thereby The first blade and the second blade partially overlap each other when viewed in the direction of the central axis of the tube.

Optionally, the radial distance L4 between the free end of the first blade and the opposite inner wall surface of the tube wall is in the range of 2 mm to 5 mm, and/or, the free end of the second blade is between the opposite inner wall surface of the tube wall The radial distance between L4 is in the range of 2mm to 5mm.

Optionally, the free end of the blade is formed with a chamfered surface facing the outlet.

Optionally, the acute angle β formed between the chamfered surface and the central axis of the draft tube is in the range of 10° to 40°. Preferably, the acute angle β formed between the chamfered surface and the central axis of the draft tube is in the range of 18° to 22°.

Optionally, the thickness h of the blade is in the range of 1 mm to 3 mm.

Optionally, the outer wall surface of the draft tube is cylindrical, and the inner wall surface of the draft tube is circular or formed by two opposite arc surfaces and two opposite flat surfaces.

Optionally, the draft tube structure further includes a liner, and the draft tube is installed in the liner.

Optionally, the compressor includes a fixed part that defines a middle pressure cavity, one end of the liner is coupled to the fixed part so that the outlet is connected to the middle pressure cavity, and the outer pipe of the jet enthalpy increasing pipeline is connected to the other end of the liner and is connected to the draft tube The abutment allows the inlet to be connected to the source of the jet enthalpy-enhancing fluid.

Optionally, the compressor includes a fixed part defining the intermediate pressure chamber, and a flow passage defining the draft tube is formed in the fixed part.

Optionally, the flow channel is a rectangular parallelepiped groove, and the bottom surface of the flow channel is provided with an inlet connected to the outer pipe of the air jet enthalpy increasing pipe and an outlet connected to the medium pressure cavity.

Optionally, the draft tube structure further includes a cover plate covering the flow channel to define the draft tube together with the flow channel.

According to another aspect of the present disclosure, there is also provided a fixed scroll component of a scroll compressor. The fixed scroll component is implemented as the above-mentioned fixed component so as to provide the above-mentioned guide tube structure.

According to yet another aspect of the present disclosure, there is also provided a compressor assembly with jet enthalpy, the compressor assembly comprising a compressor, a jet enthalpy-enhancing fluid source and suitable for supplying jet enthalpy-enhancing fluid from the jet enthalpy-enhancing fluid source The air jet enthalpy increasing pipeline to the intermediate pressure cavity of the compressor, wherein the air jet enthalpy increasing pipeline is provided with the above-mentioned draft tube structure.

According to yet another aspect of the present disclosure, there is also provided a compressor system with jet enthalpy, wherein the compressor system includes the compressor assembly described above.

According to the guide pipe structure, compressor assembly, and compressor assembly provided by the present disclosure, during its use, the positive flow of the jet enthalpy-enhancing fluid can be little or almost no effect, and can be significantly reduced or even Eliminate the reverse flow of the jet enthalpy-enhancing fluid in the jet enthalpy path, thereby reducing the vibration and noise of the pipeline and avoiding damage to the valve body in the path without reducing the forward flow efficiency of the jet-enhancing fluid .

Description of the drawings

Through the following description with reference to the accompanying drawings, the features and advantages of one or more embodiments of the present disclosure will become easier to understand. The drawings described herein are for illustrative purposes only and are not intended to limit the scope of the present disclosure in any way. The drawings are not drawn to scale, but some features can be enlarged or reduced to show details of specific components. In the attached picture:

Figure 1 is a partial longitudinal cross-sectional view of a compressor assembly with jet enthalpy in the prior art;

2 is a partial longitudinal sectional view of a compressor assembly with jet enthalpy according to the first exemplary embodiment of the present disclosure;

Fig. 3 is a schematic diagram of the forward injection of fluid in the draft tube structure according to the first exemplary embodiment of the present disclosure;

4 is a schematic diagram of reverse impact of fluid in the draft tube structure according to the first exemplary embodiment of the present disclosure;

Fig. 5 is a perspective schematic view of a copper elbow of an air-jet enthalpy-enhancing pipe according to the first exemplary embodiment of the present disclosure;

Fig. 6 is a perspective schematic view of the liner of the air-jet enthalpy-enhancing pipeline according to the first exemplary embodiment of the present disclosure;

7a to 7d are respectively a three-dimensional schematic diagram of the assembled draft tube according to the first exemplary embodiment of the present disclosure, the perspective schematic view of the first half and the second half of the draft tube, and the assembled guide tube Schematic diagram of the cross section of the tube;

FIG. 8 is a longitudinal sectional view of the draft tube structure according to the first exemplary embodiment of the present disclosure;

Fig. 9 is a perspective schematic view of a fixed scroll component according to a second exemplary embodiment of the present disclosure;

10 is a perspective schematic view of the fixed scroll component after the cover plate is removed according to the second exemplary embodiment of the present disclosure;

11a to 11b are perspective schematic views of bolts and cover plates of a fixed scroll component according to a second exemplary embodiment of the present disclosure;

Fig. 12 is a partial schematic view of a flow passage of a fixed scroll component according to a second exemplary embodiment of the present disclosure;

Fig. 13 is a longitudinal sectional view of a fixed scroll component according to a second exemplary embodiment of the present disclosure;

FIG. 14 is a top view of the flow passage of the fixed scroll component according to the second exemplary embodiment of the present disclosure; and

FIG. 15 is a schematic diagram of a guide vane according to a third exemplary embodiment of the present disclosure.

detailed description

Those skilled in the art will know that the jet enthalpy increase technology can be applied to various compressors, such as scroll compressors or gear compressors. For the convenience of description, in the present disclosure, a scroll compressor is used as an example to describe the associated jet enthalpy increase pipeline. Hereinafter, preferred embodiments of the present disclosure will be described with reference to the accompanying drawings. The description is only exemplary and does not constitute a limitation to the present disclosure and its applications.

The compressor system mainly includes compressor, condenser, main expansion valve and evaporator. The lower pressure working fluid vapor flowing out of the evaporator enters the suction port of the compressor and is compressed, so that its temperature and pressure are increased, and then the working fluid leaves the discharge port of the compressor and enters the condenser. In the condenser, the working fluid releases heat and condenses into a liquid with normal temperature and higher pressure. After being throttled by the main expansion valve, it becomes a liquid with lower temperature and pressure and sent to the evaporator where it absorbs heat and evaporates It becomes the vapor with higher temperature and lower pressure, and then it is sent to the air inlet of the compressor to complete a working cycle. When the condenser is located indoors and the evaporator is located outdoors, the working cycle can be considered a heating cycle. The compressor system can also have a four-way reversing valve, so that the indoor heat exchanger is used as an evaporator, and the outdoor heat exchanger is used as a condenser to achieve indoor cooling, which is not described in detail here.

In cold areas, when the outdoor temperature is very low, the heat exchange capacity of the outdoor evaporator decreases, the return air volume of the compressor intake port decreases, and the compressor power decreases, which cannot exert the best effect. However, the intermediate pressure replenishment port on the compressor is used to supplement the working fluid (that is, the jet enthalpy-enhancing fluid in this article), thereby increasing the compressor displacement, and increasing the quality of the heating cycle of the indoor heat exchanger to increase the heating capacity. This way of increasing the heat of the compression mechanism is called jet enthalpy. The greater the difference between the evaporation temperature (outdoor temperature) and the condensation temperature (indoor temperature), the better the effect will be, so the effect is more obvious in the low temperature environment.

In order to achieve the jet enthalpy increase, in addition to the above-described working fluid circulation path (main circuit), the compressor system is also provided with a jet enthalpy increase path. In the compressor system provided with the jet enthalpy increasing path, an economizer (equivalent to the jet enthalpy increasing fluid source in this document) is also provided, which includes, for example, an economizer expansion valve and a heat exchanger. The heat exchanger has a first channel and a second channel that are fluidly isolated from each other. A part of the working fluid from the condenser directly passes through the first channel of the heat exchanger, and then enters the main expansion valve. Another part of the working fluid from the condenser passes through the economizer expansion valve, the second passage of the heat exchanger in turn, and returns to the air supplement port of the compressor communicating with the intermediate pressure part. After throttling by the economizer expansion valve, the temperature and pressure of the second working fluid part are reduced. Therefore, when the second working fluid part subsequently enters the second passage of the heat exchanger, the second working fluid part whose temperature is relatively low Heat exchange occurs with the first working fluid part, thereby reducing the temperature of the first working fluid part and appropriately increasing the temperature of the second working fluid part. The path downstream of the second passage of the heat exchanger in the jet enthalpy compressor system is called the jet enthalpy path.

By setting the air jet path to increase the enthalpy, on the one hand, the working fluid in the main circuit (the first working fluid part) is cooled before throttling to increase the enthalpy difference; on the other hand, the low temperature that passes through the economizer expansion valve is throttled. The low-pressure working fluid (the second working fluid part) is preheated to reach a suitable intermediate pressure and provided to the compressor for secondary compression. Thus, the compression process of the compressor becomes a quasi-two-stage compression process.

Fig. 1 is a partial longitudinal sectional view of a compressor assembly with jet enthalpy in the prior art. As shown in Figure 1, the compressor assembly includes a compressor (shown as a scroll compressor in Figure 1), a source of jet enthalpy-enhancing fluid (not shown), and a source adapted to transfer the jet enthalpy-enhancing fluid from the jet-enhancing fluid The enthalpy-increasing pipeline of the air jet supplied to the intermediate pressure chamber of the compressor 1. The scroll compressor 1 mainly includes a housing 13, a compression mechanism composed of a fixed scroll component 11 and a movable scroll component 12, and a driving mechanism. The compression mechanism is driven by the drive mechanism. Specifically, when the drive shaft of the drive mechanism rotates, the movable scroll member 12 can be driven via the crank pin of the drive shaft, so that the movable scroll member 12 performs translational rotation relative to the fixed scroll member 11. The movable scroll part 12 and the fixed scroll part 11 form several closed compression chambers. As the movable scroll part 12 orbits relative to the fixed scroll part 11, the compression chamber moves from the inlet of the compression mechanism to the exhaust port. And the volume is gradually reduced, and the pressure of the sucked working fluid is gradually increased. The jet enthalpy increasing pipeline 2 penetrates the casing 13 of the compressor 1 and is fixedly connected with the casing 13 and the fixed scroll component 11, and the fluid in the jet increasing enthalpy pipeline 2 enters the compressor 1 through the air supplement port on the fixed scroll component 11 The medium pressure cavity. Here, the flow direction of the fluid in the jet enthalpy increasing pipe 2 flowing into the intermediate pressure chamber of the compressor 1 is defined as the positive direction. Since the position of the supplementary air inlet into the intermediate pressure cavity of the compressor 1 is fixed, and the pressure of the intermediate pressure cavity changes with the orbiting scroll, the pressure at the outlet of the injection enthalpy increasing pipe 2 fluctuates. At the inlet of the jet enthalpy increasing pipe 2, the pressure of the fluid leaving the economizer is basically stable. Therefore, the pressure difference between the inlet and the outlet generates pressure pulsations in the jet enthalpy increasing path. Here, the direction in which the fluid in the jet enthalpy increasing pipe 2 flows in the reverse direction due to the pressure pulsation is defined as the reverse direction. This kind of pressure pulsation is likely to cause violent shaking of various devices (such as valves) on the pipeline or the pipeline itself, which not only generates noise, but also easily leads to breakage of the pipeline connection.

In the prior art, it is often used to add a muffler to the jet enthalpy increase pipeline to reduce noise and vibration, but this method will cause the compressor system to be complex and costly. Or an expansion chamber is provided in the compressor to reduce the pressure pulse, but the effect is often not good due to the space limitation inside the compressor. Or a one-way valve is provided in the compressor to prevent the medium-pressure working fluid from flowing in the reverse direction. However, this setting will cause a large pressure loss of the forward injection, and there are problems with the reliability of the valve plate.

To this end, the present disclosure proposes a draft tube structure for the enthalpy-increasing path of the jet. Referring to FIG. 2, in the compressor assembly with jet enthalpy according to the first exemplary embodiment of the present disclosure, the structure and working principle of the compressor 1 are basically the same as those of the scroll compressor in FIG. Repeat it again. The jet enthalpy increasing pipeline 20 connected to the compressor 1 mainly includes an elbow 21, a liner 22 and a draft tube 23. The liner 22 passes through the housing 13 of the compressor 1 and is fixed on the housing 13. The first end of the liner 22 extends inside the compressor 1 to be connected to the fixed scroll member 11 and the end is connected to the fixed scroll member 11 The upper air supplement port communicating with the intermediate pressure chamber is in fluid communication, and the second end opposite to the first end extends outside the compressor 1 and is connected to the elbow 21. Referring to Figure 6, the liner 22 is substantially cylindrical, and its first end has a reduced diameter part. The connection between this part and the rest of the liner 22 forms a stepped surface, which is used for guiding on the one hand. The abutment and positioning of the flow tube 23, on the other hand, are used to keep the inner diameter of this part substantially the same as or slightly smaller than the inner diameter of the flow guiding tube 23 and the elbow 21. An annular boss is formed on the second end of the liner 22, which is used to position the liner 22 against the outside of the casing 13 of the compressor and is used for the gap between the liner 22 and the casing 13 welding. The liner 22 is preferably a metal liner, and is preferably welded and fixed to the housing 13.

The guide pipe 23 is installed inside the liner 22. The guide tube 23 preferably has a clearance fit with the liner tube 22, but it can also be in other ways, such as interference fit. The inner wall of the guide tube 23 is provided with several pairs of blades arranged at certain intervals along the axial direction of the guide tube 23, wherein two blades 233 of each pair of blades are respectively arranged in a plane passing through the axis of the guide tube 23 On both sides, the two blades 233 in each pair of blades can be arranged symmetrically with respect to the above-mentioned plane, or staggered. Each blade 233 extends obliquely from the inner wall surface of the tube wall toward the outlet of the guide tube. The outer wall surface of the draft tube 23 is cylindrical and fits with the inner wall surface of the draft tube 23, and the inner wall surface of the draft tube 23 is not limited to a circular shape. The guide tube 23 can be divided into two symmetrical halves for processing, or can be integrally formed. Figures 7a to 7d show the draft tube 23 divided into two halves for processing. 7a is a perspective schematic view of the two halves of the draft tube 23 combined together, and FIGS. 7b and 7c are perspective schematic views of the first half 231 and the second half 232 of the draft tube, respectively, and FIG. 7d It is a cross-sectional view of the guide tube 23 along the radial direction. In the examples shown in FIGS. 7 a to 7 d, the inner wall surface of the guide tube 23 is formed by connecting two opposing arcuate surface sections 234 and two opposing plane sections 235. Two blades 233 in each pair of blades are formed on two circular arc surface segments 234 respectively. The first half 231 and the second half 232 of the guide tube are mirror-symmetrical, wherein the first half 231 has a tube wall part and a blade part, and the inner wall of the tube wall part is formed by two opposite arc surface sections 234. One part and one flat section 235 are formed, and the blade part is formed by one-half 2311 of the two blades 233 in each pair of blades. When the first half 231 and the second half 232 of the draft tube are combined and installed on the liner 22, a complete blade 233 and a smooth inner wall surface of the draft tube 23 are formed. The guide tube 23 is preferably a metal piece, more preferably a cast aluminum piece, or a plastic piece.

One end of the elbow 21 is installed in the liner 22 and abuts against the draft tube 23, while the other end is connected to an external jet enthalpy-enhancing fluid source (such as an economizer). Referring to Fig. 5, the elbow 21 is preferably a copper elbow, and is welded to the liner 22 and the pipeline of the jet enthalpy-enhancing fluid source.

Figures 3 and 4 show the flow paths of the fluids in the enthalpy-enhancing pipes, especially the draft tubes, respectively. When the fluid is injected in the forward direction from the external jet-enhancing fluid source into the intermediate pressure chamber of the compressor, the blades 233 in the draft tube 23 extend obliquely from the inner wall surface of the tube wall toward the outlet of the draft tube 23 , The fluid flows into the medium-pressure chamber with little or almost negligible pressure loss. When the fluid flows in the reverse direction from the medium pressure chamber to the external jet enthalpy fluid source due to pressure pulsation, the blades 233 greatly hinder the flow of the fluid, causing the flow in the reverse direction to be blocked or even to isolate the pressure. The effect of pulsation on the enthalpy-enhancing pipeline of the jet.

In order to better divert the flow of the fluid in the forward direction and hinder the effect of the fluid in the reverse direction, the detailed dimensions of the guide tube 23 will be described below with reference to FIG. 8. 8 is a longitudinal cross-sectional view of the guide tube 23, wherein the blade 233 has an arc-shaped cross section along the axis of the guide tube 23 and passing through the center of the blade, and the radius R1 thereof is preferably in the range of 4 mm to 7 mm. The thickness h of the blade 233 is preferably in the range of 1 mm to 2.5 mm. Each blade 233 of each pair of blades extends obliquely from the inner wall surface of the tube wall toward the outlet of the guide tube 23 and extends to a position where the free ends of the blades are separated by a radial distance L2, preferably the radial distance L2 is 0.5 mm to 3mm. The ratio L1/D of the axial distance L1 between adjacent vanes 233 on the same side of the plane passing through the axis of the guide tube 23 to the inner diameter D of the guide tube 23 is preferably in the range of 0.5 to 2. . It should be noted here that when the inner wall surface of the draft tube 23 is formed by arc surface segments and flat segments as shown in FIGS. 7a to 7d, the inner diameter D of the draft tube 23 refers to the circle containing the arc surface segments. diameter of. In addition, the more the logarithm of the blade 233, the better the obstructive effect on the reverse flow of the fluid, but it will also increase the pressure loss of the forward flow of the fluid. Therefore, the logarithm of the blade 233 should be within a reasonable range, for example, preferably For 3 pairs.

The inventor measured the pressure in the jet enthalpy increase path in the prior art as shown in FIG. 1 and the pressure in the jet enthalpy increase path according to the first embodiment of the present disclosure as shown in FIGS. 2 to 8 Second, compare the above-mentioned curves of pressure 1 and pressure 2 with time. It is observed that pressure 1 shows significant pulse fluctuations, while pressure 2 is more stable, and the amplitude of pressure pulses is significantly reduced. The amplitude of the pressure pulse is significantly reduced in each frequency domain (for example, at 100 Hz, 200 Hz, 400 Hz, and 600 Hz). From this, it can be seen that the flow guide tube according to the first embodiment of the present disclosure can prevent the fluid from flowing in the opposite direction in the enthalpy-increasing path of the jet, and significantly improve the noise and vibration of the compressor caused by pressure pulsation.

The pressure pulsation can be reduced or even eliminated by arranging a flow channel structure with guide vanes in the air jet enthalpy increasing path, but the flow channel structure with guide vanes is not limited to being arranged in the air jet enthalpy increasing path in the manner of a guide tube. Can be integrated on the fixed scroll component. Figures 9 to 14 show a second embodiment according to the present disclosure, and mainly relate to a fixed scroll component with a flow channel structure containing guide vanes.

9 and 10 are perspective schematic views of the fixed scroll component 11 with the cover plate 2032 installed and the cover plate 2032 removed, respectively. Except for the arrangement of the flow path structure of the guide vane, the main structure of the fixed scroll component 11 is basically the same as the fixed scroll component 11 in the prior art and the first embodiment of the present disclosure. The following description mainly focuses on the arrangement of the flow channel structure of the guide vane on the fixed scroll component 11. The fixed scroll member 11 has a base plate 111 and a scroll 112 extending on the lower surface of the base plate 111. The substrate 111 is provided with a groove formed by recessing from the upper surface of the substrate 111 toward the inside of the substrate. In addition, referring to Figures 11a and 11b, a cover plate 2032 is also provided. The cover plate 2032 covers the flow channel 203 and is fixed to the base plate 111 by screws 2033 passing through the holes on the cover plate 2032, thereby defining the groove together Runner 203. The shape and size of the cover 2032 match the groove. The groove of the flow channel 203 has a rectangular parallelepiped shape, and several pairs of blades 2031 are arranged at the same interval along the longitudinal axis of the flow channel 203 in the groove. The blade 2031 is formed on the long side wall of the groove and forms the bottom surface of the groove. Referring to FIG. 14, the remaining settings of the blades 2031, such as the arrangement rules and extension directions of the blades, and specific dimensions, such as the axis between adjacent blades 2031 on the same side of the plane passing through the longitudinal axis of the flow channel 203 The ratio (L1/L3) of the directional distance L1 to the inner diameter of the flow channel (in this example, the short side wall length L3), etc., are basically the same as the relevant settings and dimensions of the blade 233 in the first embodiment of the present disclosure. In particular, the radius R1 of the arc-shaped cross section of the blade 2031 in the axial direction of the flow channel 203 is preferably in the range of 4 mm to 6 mm.

Referring to FIGS. 12 and 13, an injection port 2034 is opened on the circumferential side surface of the base plate 111 of the fixed scroll component 11, and the jet enthalpy increasing pipe is connected to the injection port 2034. The bottom surface of the flow channel 203 is provided with an inlet 2036 and an outlet 2035. The inlet 2036 is arranged near the short side wall of the jet port 2034, and the inlet 2036 is in fluid communication with the jet port 2034, and the outlet 2035 is arranged close to the position opposite to the inlet 2036. At the short side wall, and the outlet 2035 is in fluid communication with the medium pressure chamber of the compression mechanism. The blade 2031 is arranged between the inlet 2036 and the outlet 2035.

The flow channel 203 is not limited to the rectangular parallelepiped shape as shown in FIGS. 9 to 14, and a flow channel such as the guide tube 23 may be directly formed inside the base plate 111 of the fixed scroll component 11, that is, a flow path with blades is formed inside the base plate 111 233 is a cylindrical or arc-shaped flow channel formed by a flat section. In this case, the inlet of the flow channel is formed on the circumferential side surface of the base plate 111 and is connected with the jet enthalpy increasing pipe, and the outlet of the flow channel is in fluid communication with the medium pressure chamber of the compression mechanism.

According to the flow channel arrangement of the second embodiment of the present disclosure, not only can the pressure pulse amplitude in the enthalpy increase path of the jet be effectively reduced to reduce noise and vibration, but also because the flow channel is directly integrated on the fixed scroll component, the components are reduced. The quantity reduces the requirements of assembly and processing accuracy.

Regarding the arrangement and shape of the blades in the flow channel, there are other forms besides those described above. Figure 15 shows an optimized blade form. Wherein, a plurality of blades 331 are arranged on the inner wall surface of the guide tube 33 at certain intervals along the axial direction of the guide tube 33, and the blades 331 alternately move from the inner wall surfaces on both sides of the plane passing through the axis of the guide tube 33. It extends obliquely toward the outlet of the guide tube 33, and each blade 331 is staggered from the adjacent blade with respect to the above-mentioned plane.

The blade 331 has a linear cross section along the axis of the guide tube 33 and passing through the center of the blade. The blade 331 is formed with a first curved surface that smoothly transitions with the inner wall surface at the first end connected to the inner wall surface of the guide tube 33 Portion, and a second curved portion extending in the forward direction is formed on the second end opposite to the first end, and the second curved portion is also formed with a chamfered surface facing the outlet of the flow guide tube 33. The acute angle β between the cut surface and the central axis of the guide tube 33 is preferably in the range of 10° to 40°. Preferably, the acute angle β between the chamfered surface and the central axis of the draft tube 33 is preferably in the range of 18° to 22°. The angle α between the blade 331 and the central axis of the guide tube 33 is preferably in the range of 20° to 70°. The thickness h of the blade 331 is preferably in the range of 1 mm to 3 mm. The vane 331 extends toward the axis of the guide tube 33 to a position where its free end exceeds the centerline of the guide tube 33 and extends to the position of the radial distance L4 between the top end of the chamfered surface and the opposite inner wall, so that the The blades located on both sides of the plane passing through the axis of the guide tube 33 partially overlap each other when viewed in the direction of the central axis of the flow tube 33. Preferably, the radial distance L4 is in the range of 2 mm to 5 mm. The ratio L5/D of the axial distance L5 between every two adjacent blades to the inner diameter D of the guide tube 23 is preferably in the range of 0.5 to 2. It should be noted here that when the inner wall surface of the draft tube 33 is formed by arc surface segments and flat segments as shown in FIGS. 7a to 7d, the inner diameter D of the draft tube 33 refers to the circle containing the arc surface segments. diameter of.

The form of the blade shown in FIG. 15 is not limited to being provided in the draft tube, and can also be applied to the second embodiment of the present disclosure as shown in FIGS. 9 to 14. In this case, the inner diameter D of the draft tube 33 corresponds to the short side wall length L3 of the rectangular parallelepiped flow passage 203, and the radial direction corresponds to the direction along the short side wall. In addition, the blade form described in the third embodiment is not limited to be completely applied to the guide tube or flow channel to replace the arc-shaped blade, but a single feature or a combination of partial features can be alternatively or additionally In the first embodiment and the second embodiment, for example, the arc-shaped blade may also be formed in a form with a chamfered surface or a form in which the free end of the blade exceeds the central axis of the guide tube.

After testing, the inventor found that the blade form described in the third embodiment equally or even better reduces the amplitude of the pressure pulse in the jet enthalpy path, thereby greatly reducing noise and vibration and avoiding the enthalpy path in the jet. The valve is damaged.

The present disclosure allows various possible modifications. For example, the blades can be arranged as integral or segmented spiral blades extending in the forward direction of the draft tube, which are used to divert the jet enthalpy-enhancing fluid flowing in the forward direction and hinder the reverse direction. flow. For another example, the structure of the draft tube with blades can not only be semi-embedded or fully integrated on the compressor, but also can be completely arranged outside the compressor, as long as it is arranged on the jet enthalpy increase path.

Although various embodiments of the present disclosure have been described in detail herein, it should be understood that the present disclosure is not limited to the specific embodiments described and shown in detail here, and can be used by those skilled in the art without departing from the spirit and scope of the present disclosure. Technicians implement other variations and variants. All these variations and variations fall within the scope of the present disclosure. Moreover, all the components described herein can be replaced by other technically equivalent components.

Claims

A draft tube structure for a compressor assembly with jet enthalpy, said compressor assembly comprising a compressor, jet enthalpy-enhancing fluid source and suitable for supplying jet enthalpy-enhancing fluid from said jet enthalpy fluid source to The air jet enthalpy increasing pipeline of the intermediate pressure cavity of the compressor, the draft tube structure includes a draft tube (23, 33), and the draft tube (23, 33) is arranged in the jet enthalpy increasing pipeline. At least a part of the flow path of the air-jet enthalpy-enhancing fluid is constituted, wherein the draft tube (23, 33) includes:

An inlet and an outlet, the inlet is located on the side of the jet enthalpy increasing fluid source to receive the jet of enthalpy increasing fluid, and the outlet is located on the medium pressure cavity side to discharge the received jet of enthalpy increasing fluid;

Pipe wall; and

Vanes (233, 2033, 331), the vanes are formed to extend obliquely from the inner wall surface of the tube wall toward the outlet, so as to suppress the pressure pulse in the intermediate pressure chamber from being transmitted outward.
The guide tube structure according to claim 1, wherein the blade is formed to extend obliquely in an arc shape or a straight line from the inner wall surface of the tube wall toward the outlet.
The guide tube structure according to claim 2, wherein when the blades are formed in a circular arc shape, the radius R1 of the blades (233, 2033) is in the range of 4mm to 7mm, and the When the blades are formed in a linear shape, the acute angle α formed between the blades (331) and the central axis of the guide pipes (23, 33) is in the range of 20° to 70°.
The guide tube structure according to claim 1, wherein the blades (233, 2033, 331) are formed as a spiral-shaped single integrated blade or a spiral-shaped multiple segmented blades.
The draft tube structure according to claim 1, wherein the inner wall surface of the tube wall includes a first inner wall surface and a second inner wall surface that are opposed to each other, and the blade is formed to extend from the first inner wall surface A first blade and a second blade extending from the second inner wall surface.
The guide tube structure according to claim 5, wherein the first blades and the second blades are both multiple, and the first blades are arranged in sequence with an equal axial distance L1, and/or, The second blades are arranged in sequence with an equal axial distance L1.
The draft tube structure according to claim 6, wherein the ratio L1/D between the axial distance L1 and the inner diameter D of the draft tube (23) is in the range of 0.5 to 2.
The guide tube structure according to claim 5, wherein the first blade and the second blade extend toward the central axis of the guide tube (23) such that: the free end of the first blade and The free ends of the adjacent second blades are separated by a predetermined radial distance L2.
The draft tube structure according to claim 8, wherein the predetermined radial distance L2 is in the range of 0.5 mm to 3 mm.
The flow guide tube structure according to claim 5, wherein the number of the first blades is three, and the number of the second blades is three.
The guide tube structure according to claim 5, wherein the first blade and the second blade are arranged in sequence with an axial distance L5 between the adjacent first blade and the second blade.
The draft tube structure according to claim 11, wherein the ratio L5/D between the axial distance L5 and the inner diameter D of the draft tube (23) is in the range of 0.5 to 2.
The guide tube structure according to claim 5, wherein the first blade and the second blade extend toward the central axis of the guide tube (23) such that: the free end of the first blade and The free end of the second blade extends beyond the central axis of the guide tube (23), so that when viewed from the direction of the central axis of the guide tube (23, 33), the first blade and the The second blades partially overlap each other.
The guide tube structure according to claim 13, wherein the radial distance L4 between the free end of the first blade and the opposite inner wall surface of the tube wall is in the range of 2mm to 5mm, and/or, The radial distance L4 between the free end of the second blade and the opposite inner wall surface of the tube wall is in the range of 2 mm to 5 mm.
The guide tube structure according to any one of claims 1 to 14, wherein the free end of the blade is formed with a chamfered surface facing the outlet.
The draft tube structure according to claim 15, wherein the acute angle β formed between the chamfered surface and the central axis of the draft tube (23, 33) is in the range of 10° to 40° .
The guide tube structure according to any one of claims 1 to 14, wherein the thickness h of the blade (331) is in the range of 1 mm to 3 mm.
The draft tube structure according to any one of claims 1 to 14, wherein the outer wall surface of the draft tube (23, 33) is cylindrical, and the inner wall of the draft tube (23, 33) The wall surface is circular or formed by two opposite circular arc surfaces and two opposite flat surfaces.
The draft tube structure according to any one of claims 1 to 14, wherein the draft tube structure further comprises a liner (22), and the draft tube (23, 33) is installed on the liner (22) In.
The draft tube structure according to claim 19, wherein the compressor includes a fixed part defining the intermediate pressure chamber, and one end of the liner (22) is coupled to the fixed part so that the outlet is connected to In the medium-pressure cavity, the outer pipe of the air jet enthalpy increasing pipe is connected to the other end of the liner (22) and abuts the draft tube (23, 33) so that the inlet is connected to the air jet Enthalpy-increasing fluid source.
The draft tube structure according to any one of claims 1 to 14, wherein the compressor includes a fixed part defining the intermediate pressure chamber, and the fixed part is formed in the fixed part defining the draft tube ( 23, 33) of the runner (203).
The draft tube structure according to claim 21, wherein the flow channel (203) is a rectangular parallelepiped groove, and a bottom surface of the flow channel (203) is provided with a pipe connected to the air jet enthalpy The inlet (2036) of the outer pipe of the external pipe and the outlet (2035) connected to the medium pressure chamber.
The draft tube structure according to claim 21, wherein the draft tube structure further comprises a cover plate (2032), the cover plate (2032) covering the flow channel (203) and interacting with the flow The channels (203) together define the draft tubes (23, 33).
A fixed scroll component of a scroll compressor, wherein the fixed scroll component is implemented as the fixed component according to any one of claims 21 to 23 so as to be provided with any one of claims 21 to 23 The structure of the draft tube.
A compressor assembly with jet enthalpy, the compressor assembly comprising a compressor, a jet enthalpy-enhancing fluid source, and an intermediate pressure suitable for supplying jet enthalpy-enhancing fluid from the jet enthalpy-enhancing fluid source to the compressor The air-jet enthalpy-increasing pipeline of the cavity, wherein the air-jet enthalpy increase pipeline is provided with the draft tube structure according to any one of claims 1 to 23.
A compressor system with jet enthalpy, wherein the compressor system includes the compressor assembly according to claim 25.