CN120487674A - Compressor casing components, compressors and engines - Google Patents
Compressor casing components, compressors and enginesInfo
- Publication number
- CN120487674A CN120487674A CN202510990444.2A CN202510990444A CN120487674A CN 120487674 A CN120487674 A CN 120487674A CN 202510990444 A CN202510990444 A CN 202510990444A CN 120487674 A CN120487674 A CN 120487674A
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- cavity
- compressor
- ring structure
- noise suppressor
- wall
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Abstract
The application provides a shell assembly of a gas compressor, the gas compressor and an engine. The shell assembly of the compressor comprises a compressor shell, a backflow ring and a noise suppressor, wherein the backflow ring and the noise suppressor are sequentially arranged in an air inlet cavity along the direction away from an impeller cavity, the first inner cavity, the second inner cavity and the impeller cavity are communicated, the backflow ring comprises an inner ring structure, an annular cavity and an outer ring structure, one end of the inner ring structure and the cavity wall of the impeller cavity enclose a first gap, an annular groove is formed in the periphery of one end of the noise suppressor, one end of the inner ring structure is inserted into the annular groove and encloses a second gap, the noise suppressor, the outer ring structure and the cavity wall of the air inlet cavity are sequentially abutted, the inner diameter of the outer ring structure is smaller than or equal to the inner diameter of the outer wall of the annular groove, and the first gap, the annular cavity, the annular groove and the second gap are sequentially communicated to form the backflow cavity. According to the application, the noise suppressor and the reflux ring are arranged at the air inlet end of the air compressor, and the effects of reducing noise transmission and surging are realized through reliable axial positioning and radial dimension relation.
Description
Technical Field
The application relates to the technical field of compressors, in particular to a shell assembly of a compressor, the compressor and an engine.
Background
Surging (surging) is the vibration of the compressor under an abnormal condition that occurs when the flow is reduced to a certain extent. Surging presents a serious hazard to the compressor, and can lead to strong mechanical vibration, localized overtemperature, performance degradation, and system instability of the compressor components, and serious damage to the components in a short period of time.
A common and economical way to reduce the risk of surge is to add a return cavity at the compressor inlet end, which is a cavity design. Some researches show that the addition of the guide vane in the backflow cavity can further optimize the surge margin and balance the surge area efficiency, but the addition of the guide vane has certain difficulty in the aspect of industrialized implementation. For example, the integrated design brings manufacturing difficulties, while the split design has higher requirements on the relative positions of parts, so that the integrity of the whole reflux channel needs to be ensured, wherein the integrity comprises the dimensional precision of the fairing and the in-out channel of the reflux cavity, and the precision of the radial matching size and the axial positioning size and the reliability of assembly are ensured. Once the assembly is loosened during application, the risks of surge and noise are aggravated, and serious parts collide with the compressor wheel to cause the failure of the rotor.
Disclosure of Invention
Aiming at the defects of the existing mode, the application provides a shell component of a gas compressor, the gas compressor and an engine, which are used for solving the problems of low surge margin of the gas compressor, surge and noise risks and difficult industrialized implementation existing in the related technology.
In a first aspect, an embodiment of the present application provides a housing assembly for a compressor, comprising:
A compressor housing having an intake chamber and an impeller chamber;
The first inner cavity of the noise suppressor, the second inner cavity of the reflux ring and the impeller cavity are sequentially communicated;
the reflux ring comprises an inner ring structure, a ring cavity and an outer ring structure which are sequentially arranged from inside to outside along the radial direction of the second inner cavity;
One end of the inner ring structure facing the impeller chamber is enclosed with the cavity wall of the impeller chamber to form a first gap;
the inner ring structure is inserted into the annular groove towards one end part of the noise suppressor and is enclosed with the inner wall of the annular groove to form a second gap;
The noise suppressor, the outer ring structure and the cavity wall of the air inlet chamber are sequentially abutted along the axial direction of the air inlet chamber, wherein the inner diameter of the outer ring structure is smaller than or equal to the inner diameter of the outer wall of the annular groove;
the first gap, the annular cavity, the annular groove and the second gap are sequentially communicated to form a backflow cavity.
Optionally, the backflow ring further comprises a plurality of vanes disposed within the ring cavity about an axis of the second inner cavity;
the plurality of vanes are each connected with the inner ring structure and the outer ring structure.
Optionally, the inner ring structure, the plurality of vanes, and the outer ring structure are integrally formed.
Optionally, the noise suppressor is located at an end of the outer ring structure, which is flush with a surface of the air inlet end of the air inlet chamber or is recessed inwardly relative to the air inlet end of the air inlet chamber, in an axial direction of the air inlet chamber.
Optionally, at least a portion of the first lumen tapers in diameter in a direction in which the noise suppressor is pointed toward the reflux ring.
Optionally, the inner wall of the first inner cavity has an S-shaped cross-sectional shape on the axial cross-section of the first inner cavity, or
The first lumen has a tapered cross-sectional shape in its axial cross-section.
Optionally, the inner wall of the air inlet end of the inner ring structure is tapered in a direction in which the noise damper is directed toward the return ring, and/or,
The inner wall minimum diameter of the inner ring structure is smaller than the minimum diameter of the first inner cavity.
Optionally, the return ring is in transition engagement with the compressor housing, and/or,
The noise suppressor is in interference fit with the compressor housing.
Optionally, the material of the reflow ring comprises an aluminum alloy or plastic, and/or,
The noise suppressor is of the same material as the compressor housing.
In a second aspect, an embodiment of the present application provides a compressor comprising a housing assembly of a compressor as described above.
In a third aspect, an embodiment of the present application provides an engine comprising a compressor as described above.
The technical scheme provided by the embodiment of the application has the beneficial technical effects that:
according to the embodiment of the application, the noise suppressor and the reflux ring are arranged at the air inlet end of the air compressor, so that the surge margin and the stability of the air compressor can be improved, the occurrence probability and the risk of surge are reduced, the noise suppressor and the reflux ring are two mutually independent components, the noise suppressor and the reflux ring can be manufactured, installed, detached, maintained or replaced respectively, the manufacturing is easy, the operation is convenient, the flexibility and the adaptability are high, and the two components cannot interfere.
Additional aspects and advantages of the application will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the application.
Drawings
The foregoing and/or additional aspects and advantages of the application will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings, in which:
Fig. 1 is a schematic cross-sectional view of a housing assembly of a compressor according to an embodiment of the present application;
FIG. 2 is a schematic view of a partial enlarged structure at A in FIG. 1;
fig. 3 is an exploded view of a casing assembly of a compressor according to an embodiment of the present application;
FIG. 4 is a schematic cross-sectional view of a housing assembly of the compressor of FIG. 3;
fig. 5 is a schematic cross-sectional view of a compressor housing of a housing assembly of a compressor according to an embodiment of the present application;
Fig. 6 is a schematic structural view of a backflow ring of a casing assembly of a compressor according to an embodiment of the present application;
FIG. 7 is a schematic view of the reflow ring of FIG. 6 from one perspective;
FIG. 8 is a schematic perspective view of a cross-section of a backflow ring of a casing assembly of a compressor (e.g., B-B cross-sectional view in FIG. 7) according to an embodiment of the present application;
FIG. 9 is a schematic cross-sectional view of a backflow ring of a casing assembly of a compressor (e.g., cross-sectional view B-B in FIG. 7) according to an embodiment of the present application;
fig. 10 is a schematic structural view of a noise suppressor of a housing assembly of a compressor according to an embodiment of the present application;
FIG. 11 is a schematic view of a noise suppressor for a compressor housing assembly according to another embodiment of the present application;
Fig. 12 is a schematic cross-sectional view of a noise suppressor of a housing assembly of a compressor according to an embodiment of the present application;
FIG. 13 is a compressor performance map of the baseline scheme;
Fig. 14 is a compressor performance diagram of a shell assembly of a compressor according to an embodiment of the present application;
FIG. 15 is a graph comparing compressor performance of a compressor housing assembly and a baseline version provided by an embodiment of the present application;
fig. 16 is a schematic cross-sectional structure of a housing assembly of a compressor applied to a turbocharger according to an embodiment of the present application.
Reference numerals:
a housing assembly of a 100-compressor;
10-a compressor shell, 11-an air inlet chamber, 12-an impeller chamber, 13-a fifth wall surface and 14-a worm channel;
20-a backflow ring, 21-a second inner cavity, 22-a first wall surface, 23-a ring cavity, 24-guide vanes, 25-a fourth wall surface, 26-an inner ring structure, 27-an outer ring structure, 28-a second wall surface and 29-a third wall surface;
30-noise suppressor, 31-first inner cavity, 32-inner wall of annular groove, 33-annular groove;
41-second gap 42-first gap;
50-a reflow chamber;
1000-a turbocharger;
200-compressor end, 210-compressor impeller;
300-turbine end, 310-volute assembly, 320-turbine;
400-middle shell assembly, 410-end-pressing back plate;
500-diffusion channels;
600-turbine shaft.
Detailed Description
Embodiments of the present application are described below with reference to the drawings in the present application. It should be understood that the embodiments described below with reference to the drawings are exemplary descriptions for explaining the technical solutions of the embodiments of the present application, and the technical solutions of the embodiments of the present application are not limited.
As used herein, "said" and "the" may also include plural forms, unless specifically stated otherwise, as will be understood by those skilled in the art. It should be further understood that the terms "comprises" and/or "comprising," when used in this specification of the present application, specify the presence of stated features, integers and/or components, but do not preclude the presence or addition of other features, information, data, steps, operations, elements, components and/or groups thereof, etc., that are implemented as desired in the art. The term "and/or" as used herein refers to at least one of the items defined by the term, e.g., "a and/or B" may be implemented as "a", or as "B", or as "a and B".
For the purpose of making the objects, technical solutions and advantages of the present application more apparent, the embodiments of the present application will be described in further detail with reference to the accompanying drawings.
In some related art, the noise suppressor and the return ring are an integral insert, but such an integral insert cannot accommodate the blades at the same time due to manufacturability. Recent studies have shown that adding vanes to the noise suppressors helps to increase compressor efficiency. However, the blade based on the noise suppressor design is very thin, it is difficult to ensure sufficient strength during manufacturing, production cannot be achieved, reliability is not high, and cost control is difficult.
The application provides a shell assembly of a compressor, the compressor and an engine, and aims to solve the technical problems of the related art.
The following describes the technical scheme of the present application and how the technical scheme of the present application solves the above technical problems in detail with specific embodiments. It should be noted that the following embodiments may be referred to, or combined with each other, and the description will not be repeated for the same terms, similar features, similar implementation steps, and the like in different embodiments.
An embodiment of the present application provides a housing assembly 100 of a compressor, where a schematic structural diagram of the housing assembly 100 of the compressor is shown in fig. 1,3 and 4, and includes:
the compressor housing (Compressor Housing) 10 has an inlet chamber 11 and an impeller chamber 12, as shown in fig. 5.
The return ring (Ported Shroud) 20 and the Noise suppressor (Noise suppressor) 30 are installed in the intake chamber 11 in order in a direction away from the impeller chamber 12, and the first inner chamber 31 of the Noise suppressor 30, the second inner chamber 21 of the return ring 20, and the impeller chamber 12 are communicated in order.
In the embodiment of the present application, both the backflow ring 20 and the noise suppressor 30 are installed in the air intake chamber 11 of the compressor housing 10, and the backflow ring 20 is close to the impeller chamber 12, and the noise suppressor 30 is located on the side of the backflow ring 20 away from the impeller chamber 12. The compressor housing 10 is adapted to carry a backflow collar 20 and a noise damper 30. The first inner chamber 31 of the noise suppressor 30, the second inner chamber 21 of the backflow ring 20, and the impeller chamber 12 are sequentially communicated as a main passage of the compressor. The gas can enter the impeller chamber 12 after passing through the first inner cavity 31 of the noise suppressor 30 and the second inner cavity 21 of the backflow ring 20 in sequence, components such as a compressor impeller and the like are installed in the impeller chamber 12, and the compressor impeller rotating at high speed in the impeller chamber 12 can do work on the gas entering the impeller chamber 12, so that the gas pressure is improved, and the gas kinetic energy is increased.
The backflow ring 20 can optimize the airflow path and reduce turbulence, so that the stability and surge margin of the compressor can be remarkably improved, and further, larger working stability and safety boundary are obtained, and the system stability is improved. The noise suppressor 30 mainly functions to stably rectify the intake air and reduce the turbulence.
The noise suppressor 30 and the backflow ring 20 are installed at the air intake end of the compressor, so that the occurrence probability and risk of surge can be reduced.
In addition, in the embodiment of the present application, the noise suppressor 30 and the reflow ring 20 are two independent components, and the noise suppressor 30 and the reflow ring 20 can be manufactured, installed, disassembled, maintained or replaced respectively, so that the manufacturing is easy, the operation is convenient, the flexibility and the adaptability are high, and the two components do not interfere.
In the embodiment of the present application, thin arrows in fig. 1 to 12 indicate spaces.
Optionally, as shown in fig. 4 and fig. 6 to fig. 9, in the embodiment of the present application, the reflow ring 20 includes an inner ring structure 26, an annular cavity 23 and an outer ring structure 27 sequentially arranged from inside to outside along the radial direction of the second inner cavity 21.
The end of the inner ring structure 26 facing the impeller chamber 12 (i.e., the air outlet end) encloses a cavity wall of the impeller chamber 12 to form a first gap 42. The outer periphery of the cavity wall of the noise suppressor 30 facing the end (i.e. the air outlet end) of the backflow ring 20 is provided with an annular groove 33, and the part of the inner ring structure 26 facing the end of the noise suppressor 30 (i.e. the main channel air inlet end of the inner ring structure 26) is inserted into the annular groove 33 and is enclosed with the inner wall 32 of the annular groove 33 to form a second gap 41. Along the axial direction of the air inlet chamber 11, the noise suppressor 30, the outer ring structure 27 and the cavity wall of the air inlet chamber 11 are sequentially abutted, and the inner diameter of the outer ring structure 27 is smaller than or equal to the inner diameter of the outer wall of the annular groove 33. The first gap 42, the annular chamber 23, the annular groove 33, and the second gap 41 are sequentially communicated to form a return chamber 50.
In the embodiment of the present application, the inner ring structure 26 encloses a second inner cavity 21, the air inlet end (i.e. the end facing the noise suppressor 30) of the second inner cavity 21 is communicated with the first inner cavity 31, and the air outlet end (i.e. the end facing the impeller chamber 12) is communicated with the impeller chamber 12. The outer ring structure 27 is sleeved on the periphery of the inner ring structure 26, and the outer ring structure 27 and the inner ring structure 26 enclose a ring cavity 23.
The air outlet end (i.e., the fourth wall 25) of the inner ring structure 26 encloses the cavity wall (i.e., the fifth wall 13) of the impeller chamber 12 to form a first gap 42, such that the ring cavity 23 can communicate with the impeller chamber 12 through the first gap 42.
The annular groove 33 of the noise suppressor 30 is disposed around the periphery of the first inner chamber 31 and is located at the air outlet end of the first inner chamber 31. One end portion of the inner ring structure 26 facing the noise suppressor 30 is inserted into the annular groove 33, and a portion of the inner wall of the inner ring structure 26 (i.e., a portion of the first wall surface 22) encloses with the inner wall 32 of the annular groove 33 to form a second gap 41, so that the second inner cavity 21 can communicate with the annular groove 33 through the second gap 41, and the annular groove 33 communicates with the annular cavity 23.
The first gap 42, the annular cavity 23, the annular groove 33 and the second gap 41 are sequentially communicated to form a backflow cavity 50, an air inlet end of the backflow cavity 50 is communicated with the impeller cavity 12, and an air outlet end of the backflow cavity 50 is communicated with the second inner cavity 21.
The gas enters the impeller chamber 12 through the main channel, namely sequentially passes through the first inner cavity 31 and the second inner cavity 21, and the gas in the impeller chamber 12 is further pressurized through a diffusion channel 500 formed by the compressor shell 10 and the pressure end backboard 410 of the middle shell assembly 400 after being pressurized and energized, and then enters the volute 14 of the compressor shell 10 to be guided to the air inlet of the engine for enhancing the performance of the engine, and the other part flows back to the second inner cavity 21 through the backflow cavity 50, namely sequentially passes through the first gap 42, the annular cavity 23, the annular groove 33 and the second gap 41 (as shown in fig. 2, thick arrows indicate the flowing direction of the gas in the backflow cavity 50), so that secondary flow can be realized, airflow is stabilized, and noise is reduced.
In addition, by providing the backflow cavity 50 at the impeller cavity 12, the backflow cavity 50 itself needs to ensure the smoothness, and the front end first gap 42 and the rear end second gap 41 all need to ensure the opening precision, so that the compressor can be prevented from entering the surge working condition, and the anti-surge protection is realized. The curvature of the annular groove 33 of the noise suppressor 30 is an important constituent of the reflow chamber 50, and the reflow ring 20 is provided with an outer ring structure 27, the inner diameter of the outer ring structure 27 is smaller than or equal to the inner diameter of the outer wall of the annular groove 33 of the noise suppressor 30, so that the inner diameter of the outer ring structure 27 is matched with the size of the annular groove 33, and the smooth reflow chamber 50 is ensured to be formed. The backflow cavity 50 is formed into a cavity, can absorb fixed-frequency and broadband aerodynamic noise, reduces noise propagation, and meanwhile, the backflow cavity 50 is matched with a blade backflow ring to help to increase surge margin and reduce the occurrence of surge phenomenon.
The end of the outer ring structure 27 facing the impeller chamber 12 is in abutment with the cavity wall of the intake chamber 11, and the end of the outer peripheral wall of the noise suppressor 30 facing the return ring 20 is in abutment with the end of the outer ring structure 27 facing away from the impeller chamber 12. The return ring 20 can be stopped precisely in the axial direction at the correct position by the noise damper 30 to ensure the axial position of the return ring 20, achieving a reliable axial positioning. Both the backflow ring 20 and the noise suppressor 30 are installed in the air inlet chamber 11 of the compressor housing 10, and the reliability of assembly is ensured by radial matching of dimensions (for example, the outer ring structure 27 of the backflow ring 20 and the wall of the air inlet chamber 11 of the compressor housing 10 are in transition fit, and the noise suppressor 30 and the wall of the air inlet chamber 11 are in interference fit). By precise axial dimension definition, the relative positions of the first gap 42, the second gap 41, and the air intake chamber 11 of the compressor housing 10 with respect to the return ring 20 and the noise damper 30 are ensured.
The embodiment of the application realizes the effects of reducing noise transmission and surging through reliable axial positioning and radial dimension relation.
In the embodiment of the present application, the wall of the cavity of the noise suppressor 30 refers to the outer peripheral wall of the noise suppressor 30 surrounding the first inner cavity 31. The annular recess 33 of the noise damper 30 opens towards the return ring 20.
Alternatively, as shown in fig. 1, in the embodiment of the present application, the noise damper 30, the inner ring structure 26 and the cavity wall of the impeller chamber 12 are coaxially arranged along the axis L, i.e., the first inner cavity 31, the second inner cavity 21 and the impeller chamber 12 are coaxial.
Alternatively, as shown in fig. 1 and 2, in an embodiment of the present application, the first gap 42 is an annular gap extending about the axis L. The second gap 41 is an annular gap extending around the axis L.
Optionally, as shown in fig. 4, 6-9, in an embodiment of the present application, the backflow ring 20 further comprises a plurality of vanes 24 disposed within the ring cavity 23 about the axis of the second inner cavity 21, each of the plurality of vanes 24 being connected to an inner ring structure 26 and an outer ring structure 27.
In the embodiment of the present application, the outer ring structure 27 is connected to the inner ring structure 26 through a plurality of guide vanes 24, the plurality of guide vanes 24 are disposed in the annular cavity 23 and distributed around the axis (i.e., the axis L) of the second inner cavity 21, the plurality of guide vanes 24 divide the annular cavity 23 into a plurality of cavities, a cavity is disposed between any two adjacent guide vanes 24, air inlet ends of each of the plurality of cavities are all communicated with the first gap 42, and air outlet ends are all communicated with the annular groove 33.
In the embodiment of the present application, the provision of the guide vanes 24 in the annular cavity 23 of the backflow ring 20 helps to increase the surge margin of the compressor, which is very useful for applications having a wide operating range.
The return ring 20 is formed as a bladed return ring (Vaned Ported Shroud), and the bladed return ring 20 and the noise suppressor 30 are each separate components, providing the possibility of low cost mass production. The compressor housing assembly 100 provided by the embodiments of the present application achieves low cost, mass producible backflow collars with vanes assembled within the compressor housing 10.
Alternatively, in an embodiment of the present application, the inner ring structure 26, the plurality of vanes 24, and the outer ring structure 27 are integrally formed.
Alternatively, in the embodiment of the present application, the backflow ring 20 with the guide vanes may be manufactured by a die casting process (DIE CASTING processes) or may be manufactured by injection molding, depending on the material.
In the embodiment of the application, the backflow ring 20 with the guide vane is provided with openings on both sides (namely, the air inlet side and the air outlet side), so that both sides of the backflow ring are kept in an open state, and the backflow ring is convenient to install and process in the die casting process.
Of course, in other alternative embodiments of the present application, the inner ring structure 26, the plurality of guide vanes 24, and the outer ring structure 27 may be designed to be separated according to actual needs, and the inner ring structure 26, the plurality of guide vanes 24, and the outer ring structure 27 may be assembled and fastened together as needed.
Alternatively, as shown in fig. 5, in the embodiment of the present application, the air intake chamber 11 is a cylindrical cavity. The outer ring structure 27 is a cylindrical tube. The outer peripheral wall of the noise damper 30 is cylindrical, i.e., has a cylindrical outer contour.
Alternatively, as shown in fig. 1,2, 4 to 6, and 9 to 12, in the embodiment of the present application, the end of the noise suppressor 30 remote from the outer ring structure 27 is flush with the surface of the air intake end of the air intake chamber 11 in the axial direction of the air intake chamber 11. I.e. the sum of the length of the peripheral wall of the noise damper 30 and the length of the outer ring structure 27 in the axial direction is equal to the length of the intake chamber 11. Thus, the surface of the air inlet end of the air compressor can be smooth, the noise suppressor 30 can be protected, damage is reduced, and the air compressor is neat and attractive.
Of course, in other alternative embodiments of the present application, the end of the noise suppressor 30 remote from the outer ring structure 27 may be slightly retracted inwardly relative to the inlet end of the inlet chamber 11 in the axial direction of the inlet chamber 11, as desired. I.e. the sum of the length of the peripheral wall of the noise damper 30 and the length of the outer ring structure 27 in the axial direction is slightly smaller than the length of the inlet chamber 11.
Alternatively, as shown in fig. 1, 4 and 12, in the embodiment of the present application, at least a portion of the first inner cavity 31 is gradually reduced in diameter in a direction in which the noise suppressor 30 is directed toward the reflux ring 20.
In the embodiment of the present application, the gas flows into the first inner chamber 31 from the gas inlet end of the first inner chamber 31 (i.e., the end far away from the second inner chamber 21), and flows into the second inner chamber 21 through the gas outlet end of the first inner chamber 31. Along the direction that the noise suppressor 30 points to the backflow ring 20 (i.e., the direction that the first inner cavity 31 points to the second inner cavity 21), at least part of the first inner cavity 31 is gradually reduced in diameter, i.e., at least part of the inner peripheral wall of the first inner cavity 31 is contracted, so that the design is beneficial to guiding the air flow into the compressor housing 10, reducing the air inlet impact and throttling loss, improving the efficiency of the compressor and reducing the air inlet noise.
It should be noted that, in the embodiment of the present application, "at least part of" includes part and all of, for example, at least part of the first inner cavity 31, including part of the first inner cavity 31 (i.e., part of the first inner cavity 31) and all of the first inner cavity 31.
Alternatively, as shown in fig. 1, 4 and 12, in the embodiment of the present application, the inner wall of the first inner cavity 31 has an S-shape in cross section on the axial section of the first inner cavity 31.
The axial section refers to a section through the shaft, for example, the axial section of the first lumen 31 is a section through the axis of the first lumen 31 (i.e., the axis L shown in fig. 1 and 5).
In the embodiment of the present application, on the axial section, the section shape of the inner wall of the first inner cavity 31 is S-shaped, and the inner peripheral wall of the first inner cavity 31 is integrally formed into a shape similar to a bell mouth for guiding gas into the compressor housing 10, thereby improving the performance of the compressor.
Of course, in other alternative embodiments of the present application, the cross-sectional shape of the first lumen 31 in its axial cross-section may be tapered as desired. Alternatively, the first lumen 31 has a conical cross-sectional shape in its axial cross-section. Alternatively, in the embodiment of the present application, the cross-sectional shape of the inner wall of the first inner cavity 31 is not limited to S-shape or cone-shape, and may be designed into other regular or irregular shapes according to actual needs, so long as at least part of the diameter of the first inner cavity 31 is ensured to be gradually reduced.
Alternatively, in an embodiment of the present application, the noise suppressor 30 is an interference fit with the compressor housing 10. The purpose of the interference fit is to ensure a sufficiently large positive pressure to prevent the insert from disengaging the body at high temperatures, i.e., to prevent the noise suppressor 30 from disengaging from the compressor housing 10 at high temperatures.
Alternatively, in the embodiment of the present application, the noise suppressor 30 is installed in the air intake chamber 11 of the compressor housing 10 by press fit (press fit) or by an industrial refrigerator to prevent damage due to uneven contact surfaces during assembly.
In the embodiment of the present application, the noise suppressor 30 is embedded in the air inlet chamber 11 of the compressor housing 10 by a press-in design and contacts the return ring 20 to ensure the axial position of the return ring 20.
Alternatively, as shown in fig. 10 to 12, in the embodiment of the present application, the noise suppressor 30 has an inner peripheral wall, an outer peripheral wall, a first side face toward the return ring 20, and a second side face toward the air intake end of the compressor. The inner peripheral wall of the noise suppressor 30 encloses a first inner cavity 31, the outer peripheral wall of the noise suppressor 30 is in interference fit with the inner peripheral wall of the air inlet chamber 11 of the compressor housing 10 and contacts the outer ring structure 27 to ensure the axial position of the return ring 20, a portion of the first side surface of the noise suppressor 30 is recessed inwardly (in a direction away from the return ring 20) to form an annular groove 33, and the second side surface is flush with the surface of the air inlet end of the compressor housing 10 or slightly recessed into the air inlet chamber 11 relative to the surface of the air inlet end of the compressor housing 10.
Alternatively, in an embodiment of the present application, the backflow collar 20 is in transition engagement with the compressor housing 10.
Alternatively, in the embodiment of the present application, the outer peripheral wall of the outer ring structure 27 of the backflow ring 20 is in transition fit with the inner peripheral wall of the air intake chamber 11 of the compressor housing 10.
In the embodiment of the present application, the cooperation of the backflow ring 20 and the compressor housing 10 adopts a transitional design to minimize radial deviation. The noise suppressor 30 is connected to the compressor housing 10 by press-in means to provide a securing function to prevent the backflow collar 20 from falling out of the compressor housing 10.
The return ring 20 axially contacts the step of the compressor housing 10 and is axially accumulated (i.e., summed) with the noise damper length to be flush with or slightly recessed from the length of the intake chamber 11 of the compressor housing 10.
Alternatively, as shown in fig. 1,2, 4 and 9, in the embodiment of the present application, the inner wall of the air inlet end of the inner ring structure 26 gradually decreases in diameter in the direction in which the noise suppressor 30 is directed toward the return ring 20. This design can direct the flow of air into the compressor housing 10, helping to improve the compressor efficiency.
Alternatively, as shown in fig. 1 and 2, in the embodiment of the present application, the minimum diameter of the inner wall of the inner ring structure 26 is smaller than the minimum diameter of the first inner cavity 31, which helps to increase the kinetic energy of the gas.
Alternatively, as shown in fig. 6 to 9, in the embodiment of the present application, the inner peripheral wall of the inner ring structure 26 encloses the second inner cavity 21, and the inner peripheral wall includes a first wall 22 and a second wall 28 connected to each other, where the first wall 22 is close to the noise suppressor 30, and the second wall 28 is close to the impeller chamber 12. The cross-sectional shape of the first wall surface 22 is tapered on the axial cross-section of the inner ring structure 26 such that the diameter of the intake end of the second inner chamber 21 is gradually reduced, the cross-sectional shape of the second wall surface 28 is cylindrical, and the diameter of the second wall surface 28 is equal to the minimum diameter of the first wall surface 22.
Alternatively, as shown in fig. 8 and 9, in the embodiment of the present application, the cross-sectional shape of the first wall 22 is conical and the cross-sectional shape of the second wall 28 is cylindrical in axial cross-section.
Of course, in alternative embodiments of the application, the diameter of the second wall 28 may be designed to gradually decrease in the direction of the noise damper 30 toward the return ring 20, as desired.
Of course, in other alternative embodiments of the present application, the shape of the inner peripheral wall of the inner ring structure 26 may be designed to be other shapes as desired, provided that at least a portion of the inner wall of the inner ring structure 26 is tapered in a direction along the noise damper 30 toward the return ring 20.
Alternatively, as shown in fig. 8 and 9, in the embodiment of the present application, the outer peripheral wall of the inner ring structure 26 includes a third wall 29 and a fourth wall 25 connected, the third wall 29 being adjacent to the noise damper 30, and the fourth wall 25 being adjacent to the impeller chamber 12. The guide vane 24 is connected to a third wall surface 29 of the inner ring structure 26.
In the embodiment of the present application, the end of the first wall 22 away from the second wall 28 is connected to the end of the third wall 29 away from the fourth wall 25. The end of the second wall 28 remote from the first wall 22 is connected to the end of the fourth wall 25 remote from the third wall 29.
Alternatively, as shown in fig. 1, 2, 8, 9 and 12, in the embodiment of the present application, the first wall 22 is disposed obliquely with respect to the axis (i.e. the axis L) of the second inner cavity 21, and the distance between the first wall 22 and the axis of the second inner cavity 21 gradually decreases along the direction in which the first inner cavity 31 points toward the second inner cavity 21. The end of the inner ring structure 26 facing the noise damper 30 is inserted into the annular groove 33, and the first wall surface 22 cooperates with the inner wall 32 of the annular groove 33 to define a second gap 41.
Alternatively, as shown in fig. 1, 2, 5, 8 and 9, in the embodiment of the present application, the cavity wall of the impeller chamber 12 has a fifth wall surface 13, and the fifth wall surface 13 is close to the backflow ring 20. The fifth wall surface 13 cooperates with the fourth wall surface 25 to form a first gap 42.
Alternatively, as shown in fig. 5 and 9, in the embodiment of the present application, the fourth wall 25 is disposed obliquely with respect to the axis (i.e., the axis L) of the second inner cavity 21, the fifth wall 13 is disposed obliquely with respect to the axis (i.e., the axis L) of the impeller chamber 12, and the distance between the fourth wall 25 and the axis of the second inner cavity 21 gradually decreases in the direction in which the second inner cavity 21 points toward the impeller chamber 12, and the distance between the fifth wall 13 and the axis of the impeller chamber 12 gradually decreases.
Alternatively, as shown in fig. 6-9, in an embodiment of the present application, the entire shape of the vaned return ring 20 resembles a cylindrical tube.
Alternatively, in the present embodiment, the axial dimensions of the compressor housing 10, the backflow ring 20, and the noise damper 30 are carefully calculated, such as by dimension chain calculation (stack-up calculation), to ensure that the design of the second gap 41 and the first gap 42 are satisfactory.
Alternatively, in an embodiment of the present application, the material of the reflow ring 20 includes an aluminum alloy or plastic.
Alternatively, in the embodiment of the present application, the reflow ring 20 may be made of aluminum (including aluminum simple substance and aluminum alloy), or may be made of plastic material, such as special plastic (SPECIAL PLASTIC).
Alternatively, in an embodiment of the present application, the noise suppressor 30 is of the same material as the compressor housing 10. Thus, even in the operating state, the noise suppressor 30 does not come off. Reliability is ensured by the choice of materials, in particular the noise suppressor 30 is of the same material as the compressor housing 10.
The embodiment of the application provides a shell assembly of a compressor, which comprises a compressor shell 10 and an insert arranged at the air inlet end of the compressor shell 10, wherein the insert comprises a two-part structure, namely a backflow ring 20 with guide vanes and a noise suppressor 30. The vaned return ring 20 and the noise suppressor 30 are in turn mounted from the inlet end of the compressor housing 10 into the interior of the inlet chamber 11. In the embodiment of the present application, the first inner cavity 31 of the noise suppressor 30, the second inner cavity 21 of the backflow ring 20 with guide vanes, and the impeller chamber 12 of the compressor housing 10 are sequentially communicated to form a main channel. The gas can enter the impeller chamber 12 through the main channel sequentially through the first inner cavity 31 and the second inner cavity 21, and the high-speed rotating compressor impeller is utilized to do work in the impeller chamber 12, so that the supercharging is realized.
In the embodiment of the application, the first wall surface 22 of the reflux ring 20 with the guide vane and the inner wall 32 of the annular groove 33 of the noise suppressor 30 are enclosed to form a second gap 41, two ends of the second gap 41 are respectively communicated with the second inner cavity 21 and the annular groove 33, and the annular groove 33 is communicated with the annular cavity 23 of the reflux ring 20 with the guide vane. A plurality of guide vanes 24 are arranged in the annular cavity 23 of the backflow ring 20 with the guide vanes, and the guide vanes 24 are sequentially distributed at intervals around the axis of the second inner cavity 21. The fourth wall surface 25 of the backflow ring 20 with the guide vanes and the fifth wall surface 13 of the cavity wall of the impeller cavity 12 are enclosed to form a first gap 42, and two ends of the first gap 42 are respectively communicated with the annular cavity 23 and the impeller cavity 12.
The first gap 42, the annular chamber 23, the annular groove 33, and the second gap 41 are sequentially communicated to form a return chamber 50. Both ends of the return chamber 50 communicate with the impeller chamber 12 and the second inner chamber 21, respectively.
Alternatively, embodiments of the present application were tested for comparison to a housing assembly 100 of a compressor including a backflow ring 20 with vanes and a noise damper 30 having an S-shaped inner wall cross-sectional shape, and a Baseline version (Baseline).
Fig. 13 is a compressor performance diagram of a reference scheme, fig. 14 is a compressor performance diagram of a compressor housing assembly 100 provided by an embodiment of the present application, and fig. 15 is a compressor performance comparison diagram of the compressor housing assembly 100 and the reference scheme provided by the embodiment of the present application (where R represents the compressor housing assembly 100 provided by the embodiment of the present application and b represents the reference scheme). In fig. 13 to 15, the abscissa indicates the corrected flow rate (Corrected Air Flow in kilograms per second, that is, kg/s), the ordinate indicates the Pressure Ratio (Pressure Ratio), the annular solid line indicates the efficiency, the left broken line indicates the surge line, the right solid line indicates the choke line, and the areas included in both are ranges in which the compressor can normally operate, which are referred to as the circulation ranges. The larger the circulation range of the compressor, the higher the efficiency, and the better the performance.
As can be seen from fig. 13 and 14, the peak efficiency of the housing assembly 100 of the compressor provided by the embodiment of the present application is improved by 1pt (1%) and the efficiency island area is significantly increased compared to the reference solution. At a pressure ratio of 3.5, the 80% efficiency island width increases by about 13%. As can be seen from fig. 15, the compressor housing assembly 100 provided by the embodiment of the present application has a significantly increased surge margin compared to the baseline approach, and the width of the corrected flow versus pressure ratio graph increases by about 10% at a pressure ratio of 3.5.
Therefore, compared with the traditional scheme (such as the reference scheme), the shell assembly 100 of the compressor provided by the embodiment of the application can effectively improve the surge margin under the same pressure ratio.
In addition, compared with the traditional equipment, the shell assembly 100 of the compressor provided by the embodiment of the application is simpler and more convenient to assemble, reliable, standard in strength and controllable in cost.
Optionally, the shell assembly of the compressor provided by the embodiment of the application can be applied to the field of compressors, and further can be applied to turbochargers.
Based on the same inventive concept, an embodiment of the present application provides a compressor including a housing assembly 100 of the compressor as described above.
Alternatively, in the embodiment of the present application, the compressor may be a centrifugal compressor or an axial compressor.
Alternatively, in an embodiment of the present application, the compressor includes, but is not limited to, turbocharger 1000.
Alternatively, as shown in FIG. 16, in an embodiment of the present application, turbocharger 1000 includes a compressor end 200, a turbine end 300, and a middle housing assembly 400. The compressor end 200 includes a compressor housing assembly 100 and a compressor wheel 210. Turbine end 300 includes a volute assembly 310 and a turbine 320. The intermediate housing assembly 400 is disposed between the housing assembly 100 and the volute assembly 310 of the compressor, and the intermediate housing assembly 400 includes bearings. The turbine shaft 600 is installed in the intermediate housing assembly 400. The compressor wheel 210 is fixedly mounted to one end of the turbine shaft 600 and is located within the wheel cavity 12 of the housing assembly 100 of the compressor. The turbine 320 is fixedly mounted to the other end of the turbine shaft 600 and is positioned within a chamber defined by the volute assembly 310. The rotor of the compressor wheel 210, turbine 320 and turbine shaft 600 is free to rotate via bearings.
Gas (e.g., exhaust gas from an engine) enters the chamber in which the turbine 320 is located through the inlet of the volute assembly 310 and drives the turbine 320 to rotate. The turbine 320 rotates the compressor wheel 210 via the turbine shaft 600 such that gas (e.g., ambient air) enters the first interior chamber 31 of the noise damper 30 via the inlet end of the compressor housing assembly 100 and flows to the wheel chamber 12 via the second interior chamber 21 of the backflow ring 20.
A portion of the gas in the impeller chamber 12 flows back through the backflow chamber 50 (i.e., sequentially through the first gap 42, the annular cavity 23, the annular groove 33, and the second gap 41) to the second inner chamber 21, while the main gas is accelerated and pre-pressurized in the impeller chamber 12 by the high-speed rotating compressor impeller 210, thereby increasing the gas pressure and the gas kinetic energy. The accelerated and pre-pressurized gas is further pressurized by the diffuser passage 500 formed by the compressor housing 10 and the pressure end backplate 410 of the intermediate housing assembly 400 and then directed to the air intake of the engine by the volute 14 of the compressor housing 10 for enhanced engine performance.
It should be noted that, since the compressor provided by the embodiment of the present application includes the housing assembly of the compressor provided by the embodiment of the present application, the compressor provided by the embodiment of the present application also has the above beneficial effects of the housing assembly of the compressor provided by the embodiment of the present application, and will not be described herein.
Based on the same inventive concept, an embodiment of the present application provides an engine including a compressor as described above.
Alternatively, in embodiments of the present application, the engines include, but are not limited to, automotive engines and aeroengines. The engine provided by the embodiment of the application can be applied to the fields of vehicles, aircrafts and the like.
It should be noted that, since the engine provided by the embodiment of the present application includes the compressor provided by the embodiment of the present application, the engine provided by the embodiment of the present application also has the above beneficial effects of the compressor provided by the embodiment of the present application, and will not be described here again.
By applying the embodiment of the application, at least the following beneficial effects can be realized:
In the embodiment of the application, the reflux ring and the noise suppressor are both arranged in the air inlet chamber of the compressor shell, the reflux ring is close to the impeller chamber, and the noise suppressor is positioned on one side of the reflux ring away from the impeller chamber. The first inner cavity of the noise suppressor, the second inner cavity of the reflux ring and the impeller cavity are sequentially communicated and serve as a main channel of the air compressor. The gas can enter the impeller chamber after passing through the first inner cavity of the noise suppressor and the second inner cavity of the backflow ring in sequence, parts such as an impeller of the compressor are installed in the impeller chamber, and the impeller rotating at high speed in the impeller chamber can do work on the gas entering the impeller chamber, so that the gas pressure is improved, and the gas kinetic energy is increased.
The reflux ring can optimize the airflow path and reduce turbulence, so that the stability and surge margin of the compressor can be obviously improved, further, larger working stability and safety boundary are obtained, and the system stability is improved. The noise suppressor is mainly used for stably rectifying the air inlet and reducing vortex disturbance.
The noise suppressor and the reflux ring are arranged at the air inlet end of the air compressor, so that the occurrence probability and risk of surge can be reduced.
In addition, in the embodiment of the application, the noise suppressor and the reflux ring are two mutually independent components, and the noise suppressor and the reflux ring can be manufactured, installed, disassembled, maintained or replaced respectively, so that the noise suppressor and the reflux ring are easy to manufacture, convenient to operate and high in flexibility and adaptability, and the two components cannot interfere.
In the description of the present application, directions or positional relationships indicated by words such as "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., are based on exemplary directions or positional relationships shown in the drawings, are for convenience of description or simplification of describing embodiments of the present application, and do not indicate or imply that the devices or components referred to must have a specific orientation or be configured and operated in a specific orientation, and thus are not to be construed as limiting the present application.
The terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present application, unless otherwise indicated, the meaning of "a plurality" is two or more.
In the description of the present specification, a particular feature, structure, material, or characteristic may be combined in any suitable manner in one or more embodiments or examples.
The foregoing is only a part of the embodiments of the present application, and it should be noted that, for those skilled in the art, other similar implementation means based on the technical idea of the present application may be adopted without departing from the technical idea of the solution of the present application, which is also within the protection scope of the embodiments of the present application.
Claims (11)
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| Application Number | Priority Date | Filing Date | Title |
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| CN202510990444.2A CN120487674A (en) | 2025-07-18 | 2025-07-18 | Compressor casing components, compressors and engines |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202510990444.2A CN120487674A (en) | 2025-07-18 | 2025-07-18 | Compressor casing components, compressors and engines |
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| CN120487674A true CN120487674A (en) | 2025-08-15 |
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|---|---|---|---|---|
| US20020071765A1 (en) * | 2000-12-13 | 2002-06-13 | Sahay Sunil Nandan | Turbocharger noise deflector |
| CN203717450U (en) * | 2014-01-26 | 2014-07-16 | 光隆精密工业（福州）有限公司 | Novel air inlet structure of air compressor of turbocharger for automobile |
| CN204828057U (en) * | 2015-05-07 | 2015-12-02 | 罗伯特·博世有限公司 | Compressor and have automobile -used turbo charger of this compressor |
| US20160305453A1 (en) * | 2013-12-06 | 2016-10-20 | Borgwarner Inc. | Reduced noise compressor recirculation |
| CN117167336A (en) * | 2023-09-28 | 2023-12-05 | 潍坊富源增压器有限公司 | Low-noise turbocharger |
| CN117780689A (en) * | 2023-12-29 | 2024-03-29 | 宁波威孚天力增压技术股份有限公司 | Casing assembly for improving surge performance of compressor and turbocharger |
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2025
- 2025-07-18 CN CN202510990444.2A patent/CN120487674A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020071765A1 (en) * | 2000-12-13 | 2002-06-13 | Sahay Sunil Nandan | Turbocharger noise deflector |
| US20160305453A1 (en) * | 2013-12-06 | 2016-10-20 | Borgwarner Inc. | Reduced noise compressor recirculation |
| CN203717450U (en) * | 2014-01-26 | 2014-07-16 | 光隆精密工业（福州）有限公司 | Novel air inlet structure of air compressor of turbocharger for automobile |
| CN204828057U (en) * | 2015-05-07 | 2015-12-02 | 罗伯特·博世有限公司 | Compressor and have automobile -used turbo charger of this compressor |
| CN117167336A (en) * | 2023-09-28 | 2023-12-05 | 潍坊富源增压器有限公司 | Low-noise turbocharger |
| CN117780689A (en) * | 2023-12-29 | 2024-03-29 | 宁波威孚天力增压技术股份有限公司 | Casing assembly for improving surge performance of compressor and turbocharger |
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