CN115962153B - Compressor and engine with narrow transition section noon flow passage width - Google Patents
Compressor and engine with narrow transition section noon flow passage width Download PDFInfo
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- CN115962153B CN115962153B CN202310259025.2A CN202310259025A CN115962153B CN 115962153 B CN115962153 B CN 115962153B CN 202310259025 A CN202310259025 A CN 202310259025A CN 115962153 B CN115962153 B CN 115962153B
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Abstract
The application provides a compressor and an engine with a narrowed transition section noon runner width, which comprises an impeller, a transition section and a vaned diffuser, wherein an air outlet of the impeller is connected with an air inlet of the transition section, and an air outlet of the transition section is connected with an air inlet of the vaned diffuser; the meridian runner of the transition section comprises a first molded line positioned on the hub side and a second molded line positioned on the casing side; at least part of the meridian flow passage of the transition section is a contraction section, and the first molded line and the second molded line approach to the central line of the meridian flow passage of the transition section along the airflow direction at the contraction section; the direction of the air flow is the direction from the air inlet of the transition section to the air outlet of the transition section. The first molded line and the second molded line shrink to the central line, can reduce the width of meridian runner, promote the tangential velocity of the compressed gas of changeover portion cartridge receiver side, rectify the tangential velocity of the compressed gas of passing through the impeller, reach the effect that reduces the tangential velocity of vaned diffuser air inlet department and be in blade direction of height, improve compressor efficiency.
Description
Technical Field
The invention relates to the technical field of compressors, in particular to a compressor and an engine with a narrowed transition section noon runner width.
Background
In the compressor, after air is compressed by the impeller, the tangential velocity distribution of the compressed air at the impeller outlet is non-uniform. A tangential velocity profile of air at the outlet of a typical impeller is shown in figure 2.
In the existing compressor, the transition section between the impeller and the vaned diffuser adopts a constant-width design, that is, the width of the meridian flow passage of the transition section in the existing compressor is equal everywhere from the air inlet to the air outlet of the transition section.
The transition section cannot rectify the compressed air flowing through the impeller, so that the tangential velocity distribution of the gas at the inlet of the vaned diffuser still presents an uneven state as shown in fig. 2, and the uneven tangential velocity distribution can lead to lower overall efficiency of the compressor.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a compressor and an engine with narrowed transition section noon flow passage width, so as to improve the tangential velocity distribution condition of gas at the inlet of a vaned diffuser of the compressor and improve the efficiency of the compressor.
The application provides a compressor with a narrowed transition section noon runner width, which comprises an impeller, a transition section and a bladed diffuser, wherein an air outlet of the impeller is connected with an air inlet of the transition section, and an air outlet of the transition section is connected with an air inlet of the bladed diffuser;
the meridian runner of the transition section comprises a first molded line positioned on the hub side and a second molded line positioned on the casing side;
at least one part of the meridian flow passage of the transition section is a contraction section, and the first molded line and the second molded line are both close to the central line of the meridian flow passage of the transition section along the airflow direction at the contraction section;
one part of the meridian flow passage of the transition section is a contraction section, the other part of the meridian flow passage of the transition section is a parallel section, and the first molded line is provided with a groove at the head end of the parallel section;
at the constriction section, the portion of the first molded line other than the groove and the second molded line are both parallel to a centerline of a meridional flow path of the transition section;
the air flow direction is the direction from the air inlet of the transition section to the air outlet of the transition section.
Optionally, the head end of the contraction section is located at the air inlet of the transition section, the tail end of the contraction section is connected with the head end of the parallel section, and the tail end of the parallel section is located at the air outlet of the transition section.
Optionally, the tail end of the contraction section is located at the air outlet of the transition section, the head end of the contraction section is connected with the tail end of the parallel section, and the head end of the parallel section is located at the air inlet of the transition section.
Optionally, the parallel segments include a first parallel segment and a second parallel segment;
the head end of the first parallel section is positioned at the air inlet of the transition section, the tail end of the first parallel section is connected with the head end of the contraction section, the tail end of the contraction section is connected with the head end of the second parallel section, and the tail end of the second parallel section is positioned at the air outlet of the transition section.
Optionally, the portions of the first molded line and the second molded line located at the contraction section are both curved.
Optionally, the portions of the first molded line and the second molded line located at the contraction section are both straight lines.
The application also provides an engine at least comprising a combustion chamber, a turbine and the compressor of any one of the application;
the compressor and the turbine are coaxial;
the air outlet of the air compressor is connected with the air inlet of the combustion chamber;
the air inlet of the turbine is connected with the air outlet of the combustion chamber.
The application provides a compressor and an engine with a narrowed transition section noon runner width, which comprises an impeller, a transition section and a vaned diffuser, wherein an air outlet of the impeller is connected with an air inlet of the transition section, and an air outlet of the transition section is connected with an air inlet of the vaned diffuser; the meridian runner of the transition section comprises a first molded line positioned on the hub side and a second molded line positioned on the casing side; at least one part of the meridian flow passage of the transition section is a contraction section, and the first molded line and the second molded line approach to the central line of the meridian flow passage of the transition section along the airflow direction at the contraction section; the direction of the air flow is the direction from the air inlet of the transition section to the air outlet of the transition section. The first molded line and the second molded line shrink to the central line, can reduce the width of meridian runner, promote the tangential velocity of compressed gas of changeover portion cartridge receiver side to carry out the rectification to the tangential velocity of compressed gas through the impeller, reach the effect that reduces tangential velocity in blade direction of height in the vaned diffuser air inlet department, improve compressor efficiency.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are required to be used in the embodiments or the description of the prior art will be briefly described below, and it is obvious that the drawings in the following description are only embodiments of the present invention, and that other drawings can be obtained according to the provided drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic view of a meridian flow path of an existing compressor according to an embodiment of the present application;
FIG. 2 is a schematic view of tangential velocity distribution of air at the outlet of an existing compressor wheel according to an embodiment of the present application;
fig. 3 is a schematic view of a meridian flow path of a compressor with a narrowed width of a meridian flow path of a transition section according to an embodiment of the present application;
fig. 4 is a schematic view of a meridian flow path of a transition segment according to an embodiment of the present application;
FIG. 5 is a schematic view of a meridian flow path of another transition segment according to an embodiment of the present disclosure;
FIG. 6 is a schematic view of a meridian flow path of yet another transition segment according to an embodiment of the present application;
FIG. 7 is a schematic view of a meridian flow passage of yet another transition segment provided in an embodiment of the present application;
fig. 8 is a schematic view of a meridian flow passage of a transition section according to an embodiment of the present application;
fig. 9 is a schematic diagram of tangential velocity distribution of air at an air inlet of a vaned diffuser in a compressor with a narrowed radial flow passage width at a transition section according to an embodiment of the present application.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
To facilitate an understanding of the technical solutions of the present application, terms that may be partially involved will first be described.
The turbocharger is actually an air compressor, and consists of a turbine and a compressor which are coaxial, when the exhaust gas discharged by the engine flows through the turbine, the turbine is driven to rotate by the inertial impulsive force of the exhaust gas, and the turbine drives the impeller of the compressor which is coaxial to rotate so as to compress the air to increase the air inflow.
An impeller: the air flow control device is a core component of a rotor assembly in a compressor end of the supercharger, and the supercharger for the vehicle has wide rotating speed range and large air flow change, and an impeller is formed by radially and curvilinearly arranging impeller blades (called blades for short) on a hub, wherein the blades are generally ternary curved thin-wall impeller blades.
The vane diffuser is positioned at the rear end of the impeller, and the speed energy of the compressed gas flowing through the impeller is converted into pressure energy by utilizing the difference of the flow cross sections. The vaned diffuser is a device for converting kinetic energy of compressed air into static pressure, and the tangential velocity of the compressed air is reduced and the static pressure of the compressed air is increased by restricting the flow direction of the air flow by the shape of the vanes.
Meridian passage: is a physical term. Is the projection of the impeller-type airflow channel on the meridian plane. Meridian plane is understood to be any plane passing through the axis of the impeller.
Referring to fig. 1, a schematic view of a meridian passage of an existing compressor is shown, wherein the meridian passage of an impeller (i.e. a projection of an airflow passage of the impeller on a meridian plane) is 100, 101 is an air inlet of the compressor, and 102 is an air outlet of the compressor.
The meridional flow path with a vaned diffuser (i.e., the projection of the vaned diffuser's airflow path on the meridional plane) is 300, where 301 is the vaned diffuser's air inlet and 302 is the vaned diffuser's air outlet.
The impeller of the compressor is connected with the vaned diffuser through the transition section, and the meridian flow passage of the transition section (namely the projection of the airflow passage of the transition section on the meridian plane) is 200. The air inlet of the transition section is connected with the air outlet of the impeller, and the air outlet is arranged at one end of the transition section, which is connected with the air inlet of the vaned diffuser.
When the compressor works, air enters the impeller from the air inlet of the impeller, gas compressed by the impeller enters the transition section from the air outlet of the impeller, flows through the transition section and then enters the vaned diffuser, is further compressed in the vaned diffuser, and then enters the part at the rear end of the compressor from the air outlet of the vaned diffuser.
As can be seen in fig. 1, the radial flow channels of the transition section of the existing compressor are designed with equal widths, that is, the widths of the radial flow channels of the transition section are equal everywhere along the airflow direction, and correspondingly, the areas of the cross sections of the transition section are equal everywhere along the airflow direction. The cross section of the transition section refers to the cross section of the transition section perpendicular to the flow direction of the airflow.
Wherein the flow direction of the gas flow in the transition section is defined as the direction perpendicular to the compressor axis 10, as indicated by arrow 20 in fig. 1.
As described in the background section, the speed of the compressed gas flowing through the transition section cannot be adjusted by the transition section of the structure, so that in the existing compressor, the tangential speed distribution of the compressed gas flowing through the transition section along the height direction of the blades is basically unchanged.
The tangential velocity distribution of the compressed gas at the impeller outlet along the height of the vanes can be seen in figure 2.
In fig. 2, the horizontal axis represents speed in meters per second and the vertical axis represents normalized blade height, where 1 represents blade tip height, corresponding to the case side in this embodiment, and 0 represents blade root height, corresponding to the hub side in this embodiment.
As can be seen from the distribution of fig. 2, the tangential velocity of the compressed gas at the outlet of the impeller is distributed to a high degree along the height of the blade.
Due to the transition section structure of the existing compressor, the condition of uneven tangential velocity shown in fig. 2 is continued to the air inlet of the vaned diffuser, that is, in the existing compressor, the tangential velocity of the air at the air inlet of the vaned diffuser is unevenly distributed along the height distribution of the vane, and the uneven tangential velocity can cause the reduction of the compression efficiency of the vaned diffuser, thereby reducing the overall efficiency of the compressor.
One solution to this problem is to increase the degree of twisting of the blades in the vaned diffuser, but this solution increases the manufacturing costs of the blades in the vaned diffuser on the one hand and reduces the reliability of the blades, and on the other hand only partially alleviates the tangential velocity non-uniformity.
In view of the above problems, an embodiment of the present application provides a compressor with a narrowed width of a meridian passage of a transition section, and please refer to fig. 3, which is a schematic view of a meridian passage of a compressor with a narrowed width of a meridian passage of a transition section provided in an embodiment of the present application.
The transition section of the compressor has the following characteristics:
at least a part of the airflow channel of the transition section is a contraction section, in which the wall surface of the casing side and the wall surface of the hub side approach the inside of the airflow channel along the airflow direction, in other words, in the contraction section, the wall surface of the casing side and the wall surface of the hub side contract toward the inside of the airflow channel along the airflow direction.
From the projection of the air flow channel on the meridian plane, i.e. the meridian flow channel, at least a part of the meridian flow channel of the transition section is a contraction section in which the first molded line on the hub side and the second molded line on the casing side approach the centerline 205 of the meridian flow channel of the transition section in the air flow direction, in other words, in which both the first molded line and the second molded line contract toward the centerline 205.
The gas flow channel of the transition section thus assumes a state in which the area of the cross section in the gas flow direction is gradually reduced in the constriction section, that is to say in the constriction section the gas flow channel is gradually narrowed in the gas flow direction.
In the airflow channel with the structure, on one hand, the wall surface of the casing (Shroud) side is contracted towards the center, so that the tangential velocity of the gas at the casing side can be improved when the compressed gas flows through the transition section; on the other hand, the wall surface of the Hub (Hub) side is contracted towards the center, so that the tangential velocity of the gas at the Hub side can be improved when the compressed gas flows through the transition section, and the two factors are combined, so that the tangential velocity distribution of the gas at the gas outlet of the transition section tends to be uniformly distributed, and the compression efficiency of the vaned diffuser is improved.
As can be seen from fig. 3, the compressor comprises an impeller, a transition section and a vaned diffuser, wherein the air outlet of the impeller is connected to the air inlet of the transition section, and the air outlet of the transition section is connected to the air inlet of the vaned diffuser.
In fig. 3, the air inlet of the transition section is 201, and the air outlet of the transition section is 202. The portion of the meridian passage of the transition segment within the rectangular frame 210 is the aforementioned constriction.
The meridian passage of the transition section includes a first molded line on the hub (hub) side and a second molded line on the casing (shroud) side.
In fig. 3, the first molded line is 203, and the second molded line is 204. The first molded line can be regarded as the projection of the side wall surface of the hub on the meridian plane in the airflow channel of the transition section, and the second molded line can be regarded as the projection of the side wall surface of the casing on the meridian plane in the airflow channel of the transition section.
In some optional embodiments, in the transition section of the compressor provided by the present application, the contraction section of the meridian passage may be a part of the meridian passage of the transition section, that is, the meridian passage of the transition section may be divided into two parts, one part is the aforementioned contraction section, and the other part is a parallel section, where the first molded line and the second molded line are both parallel to the center line of the meridian passage of the transition section, that is, the airflow passage in the parallel section is still designed with equal width.
In the case that the transition section noon flow passage includes a constriction section and a parallel section, the position of the constriction section in the transition section noon flow passage may be set according to actual conditions.
An alternative constriction is located at the end of the transition section noon passageway adjacent the impeller. Specifically, the head end of the contraction section is positioned at the air inlet of the transition section, the tail end of the contraction section is connected with the head end of the parallel section, and the tail end of the parallel section is positioned at the air outlet of the transition section.
In this case, the meridian passage of the transition section may have a shape as shown in fig. 3, and it can be seen that, after the compressed gas passing through the impeller enters the transition section, the compressed gas passes through the contraction section, then passes through the parallel section, and exits the transition section from the gas outlet of the transition section after passing through the parallel section.
An alternative constriction is located at the end of the transition section noon flow passage near the vaned diffuser. Specifically, the tail end of the contraction section is positioned at the air outlet of the transition section, the head end of the contraction section is connected with the tail end of the parallel section, and the head end of the parallel section is positioned at the air inlet of the transition section.
In this case, the meridian passage of the transition section may have a shape as shown in fig. 4, and it can be seen that, after the compressed gas passing through the impeller enters the transition section, the compressed gas passes through the parallel section and then passes through the contraction section, and then exits the transition section from the gas outlet of the transition section after passing through the contraction section.
An alternative constriction is located in the middle of the transition section noon flow passage. Specifically, the parallel section is divided into two parts, namely a first parallel section and a second parallel section, the head end of the first parallel section is positioned at the air inlet of the transition section, the tail end of the first parallel section is connected with the head end of the contraction section, the tail end of the contraction section is connected with the head end of the second parallel section, and the tail end of the second parallel section is positioned at the air outlet of the transition section.
In this case, the meridian passage of the transition section may have a shape as shown in fig. 5, and fig. 5 is a schematic diagram of another meridian passage of the transition section according to an embodiment of the present application. In this configuration, the compressed gas flows from the impeller, first through the first parallel section, then from the first parallel section into the convergent section, after flowing through the convergent section, into the second parallel section, and finally through the second parallel section to the gas outlet of the transition section.
Alternatively, when the meridian passage of the transition section is divided into the contraction section and the parallel section, a groove structure may be provided on the first molded line located on the hub side, and please refer to fig. 6, which is a schematic view of the meridian passage of the transition section when the groove structure is provided.
It will be seen that the groove may be provided at the head end of the parallel section, i.e. at the junction of the convergent section and the parallel section, when the convergent section is located near one end of the impeller. The groove structure is arranged, so that the tangential speed of the hub-side compressed gas can be adjusted, the non-uniformity of the compressed gas in the height direction of the blade is reduced, the design, the manufacture and the efficiency improvement of the diffuser blade are facilitated, and the efficiency improvement of the pressure end of the supercharger is facilitated.
In addition to the above arrangement, the groove structure of the first molded line may be disposed at the head end of the contraction section when the contraction section is located near the end of the vaned diffuser. When the contraction section is located between the first parallel section and the second parallel section, the groove structure may be disposed at the head end of the first parallel section, or may be disposed at the head end of the second parallel section.
The benefit of setting the above trench structure is:
the groove structure arranged on the hub side can reduce the tangential velocity of gas close to the hub side, so that the tangential velocity of the gas on the hub side is lower than that of the gas on the casing side, and the uniformity of the tangential velocity of air at the air inlet of the vaned diffuser along the height direction of the blade is improved.
Meanwhile, the tangential velocity of the gas close to the hub side is reduced by the groove structure, and the average tangential velocity of the gas at the gas inlet of the vaned diffuser is naturally reduced, so that the phenomenon that the tangential velocity of the gas entering the vaned diffuser is too high to generate larger flow loss can be avoided.
In summary, by providing the groove structure in the first molded line, uniformity of tangential velocity of air at the inlet of the vaned diffuser along the height direction of the vane can be improved without increasing flow loss in the vaned diffuser.
In some alternative embodiments, the meridian passage of the transition section is a convergent section from the air inlet of the transition section to the air outlet of the transition section.
In this case, the meridian passage of the transition piece may have a shape as shown in fig. 7, and fig. 7 is a schematic view of a meridian passage of another transition piece according to an embodiment of the present application.
As can be seen from fig. 7, in this case, the first profile continues to shrink from the air inlet of the transition section in the air flow direction toward the center line of the noon flow passage of the transition section until the air outlet of the transition section, and the second profile continues to shrink from the air inlet of the transition section in the air flow direction toward the center line of the noon flow passage of the transition section until the air outlet of the transition section. Correspondingly, the area of the cross section of the airflow channel of the transition section gradually becomes smaller from the air inlet to the air outlet, and compressed gas continuously compresses in the airflow channel of the transition section after entering the transition section from the impeller until leaving the transition section.
It should be noted that, in the compressor provided in the embodiment of the present application, in the contraction section, the wall surfaces on the casing side and the hub side may contract in a curved manner or may contract in a straight manner, and correspondingly, in the contraction section, the first molded line and the second molded line may be represented as curves as shown in fig. 3 to 7 or may be straight.
Illustratively, when the portions of the first and second molded lines within the converging section are straight, the meridian passage of the transition section may have a shape as shown in fig. 8, and fig. 8 is a schematic diagram of a meridian passage of a further transition section according to an embodiment of the present application.
Further optionally, the casing-side and hub-side wall surfaces can also be respectively shrunk in different ways in the shrink section. Correspondingly, the first and second profiles may exhibit different profiles.
For example, the inner wall surface of the shrink section may be configured such that the wall surface of the casing side is shrunk in a curved manner, the wall surface of the hub side is shrunk in a straight line manner, and correspondingly, a portion of the first molded line formed by projection of the hub side wall surface in the shrink section is straight, and a portion of the second molded line formed by projection of the casing side wall surface in the shrink section is curved.
Alternatively, the opposite may be that the wall surface on the hub side is contracted in a curved manner, the wall surface on the casing side is contracted in a linear manner, and the portion of the first molded line formed by the projection of the side wall surface of the hub in the contracted section is curved, and the portion of the second molded line formed by the projection of the side wall surface of the casing in the contracted section is linear.
It should be noted that, when the portion of the first molded line and/or the second molded line located in the contraction section is a curve, the curve may be any form of curve, including, but not limited to, a spline curve, an arc, a polynomial curve, and the like, which is not limited in this embodiment.
When the transition section of the compressor has the characteristic of gradually narrowing in the air flow direction in the contraction section, the transition section can improve the tangential velocity of compressed air flowing through the transition section on the casing side and the hub side, so that the air flowing through the transition section and reaching the inlet of the vaned diffuser has more uniform tangential velocity distribution in the height direction of the blades. Referring to fig. 9, in a compressor with a narrowed radial flow passage width at a transition section provided in an embodiment of the present application, there is a schematic diagram of tangential velocity distribution of air at an air inlet of a vaned diffuser.
As can be seen from comparing fig. 2 and fig. 9, when the transition section structure provided by the embodiment of the present application is adopted, after compressed gas flows through the transition section, the tangential speeds of the casing side and the hub side are significantly improved, and correspondingly, the tangential speeds of the air at the inlet of the vaned diffuser are uniformly distributed along the height direction of the vane. Therefore, the transition section structure as shown in fig. 3 to 8 provided by the embodiment of the application can improve the distribution condition of the tangential velocity of air at the air inlet of the vaned diffuser along the height direction of the vane, improve the compression efficiency of the vaned diffuser, and further improve the overall compression efficiency of the compressor.
The embodiment of the application also provides an engine, which at least comprises a combustion chamber, a turbine and the compressor provided by any embodiment of the application;
the compressor and the turbine are coaxial;
the air outlet of the air compressor is connected with the air inlet of the combustion chamber;
the turbine inlet is connected to the combustion chamber exhaust.
Based on the connection, the compressor can compress the sucked air and then send the compressed air into the combustion chamber for combustion.
The exhaust gas generated after combustion in the combustion chamber can enter the turbine, so that the turbine is driven to rotate, the compressor can be driven to rotate after the turbine rotates, specifically, the impeller of the compressor can be driven to rotate, and air compression is achieved.
The combustion chamber may be one or more cylinders, but may be of any other structure, and is not limited thereto.
Finally, it is further noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
It should be noted that the terms "first," "second," and the like herein are merely used for distinguishing between different devices, modules, or units and not for limiting the order or interdependence of the functions performed by such devices, modules, or units.
Those skilled in the art can make or use the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (7)
1. The compressor with the narrowed transition section noon runner width is characterized by comprising an impeller, a transition section and a bladed diffuser, wherein an air outlet of the impeller is connected with an air inlet of the transition section, and an air outlet of the transition section is connected with an air inlet of the bladed diffuser;
the meridian runner of the transition section comprises a first molded line positioned on the hub side and a second molded line positioned on the casing side;
at least one part of the meridian flow passage of the transition section is a contraction section, and the first molded line and the second molded line are both close to the central line of the meridian flow passage of the transition section along the airflow direction at the contraction section;
one part of the meridian flow passage of the transition section is a contraction section, the other part of the meridian flow passage of the transition section is a parallel section, and the first molded line is provided with a groove at the head end of the parallel section; when the contraction section is positioned near one end of the vaned diffuser, the groove of the first molded line is arranged at the head end of the contraction section;
at the parallel section, the portion of the first molded line other than the groove and the second molded line are parallel to the center line of the meridian passage of the transition section;
the air flow direction is the direction from the air inlet of the transition section to the air outlet of the transition section.
2. The compressor of claim 1, wherein a head end of the convergent section is located at an air inlet of the transition section, a tail end of the convergent section is connected to a head end of the parallel section, and a tail end of the parallel section is located at an air outlet of the transition section.
3. The compressor of claim 1, wherein a trailing end of the convergent section is located at an outlet of the transition section, a leading end of the convergent section is connected to a trailing end of the parallel section, and a leading end of the parallel section is located at an inlet of the transition section.
4. The compressor of claim 1, wherein the parallel sections include a first parallel section and a second parallel section;
the head end of the first parallel section is positioned at the air inlet of the transition section, the tail end of the first parallel section is connected with the head end of the contraction section, the tail end of the contraction section is connected with the head end of the second parallel section, and the tail end of the second parallel section is positioned at the air outlet of the transition section.
5. The compressor of any one of claims 1 to 4, wherein portions of the first and second profiles at the contraction section are each curved.
6. The compressor of any one of claims 1 to 4, wherein portions of the first and second molded lines at the contracted section are each straight.
7. An engine comprising at least a combustion chamber, a turbine and a compressor as claimed in any one of claims 1 to 6;
the compressor and the turbine are coaxial;
the air outlet of the air compressor is connected with the air inlet of the combustion chamber;
the air inlet of the turbine is connected with the air outlet of the combustion chamber.
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| CN202310259025.2A CN115962153B (en) | 2023-03-17 | 2023-03-17 | Compressor and engine with narrow transition section noon flow passage width |
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| CN202310259025.2A CN115962153B (en) | 2023-03-17 | 2023-03-17 | Compressor and engine with narrow transition section noon flow passage width |
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| CN117436210B (en) * | 2023-12-18 | 2024-03-19 | 潍柴动力股份有限公司 | Combined design method and device for widening flow grooves and impellers |
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| SU688705A1 (en) * | 1978-04-20 | 1979-09-30 | Ленинградский Ордена Ленина Политехнический Институт Им. М.И.Калинина | Centrifugal compressor stage |
| EP2960526B1 (en) * | 2013-02-22 | 2017-11-08 | Mitsubishi Heavy Industries, Ltd. | Centrifugal compressor with intake resistive element |
| US9644639B2 (en) * | 2014-01-27 | 2017-05-09 | Pratt & Whitney Canada Corp. | Shroud treatment for a centrifugal compressor |
| GB2531029B (en) * | 2014-10-07 | 2020-11-18 | Cummins Ltd | Compressor and turbocharger |
| CN107061356B (en) * | 2017-01-05 | 2020-01-07 | 上海交通大学 | Groove flow choking structure |
| CN208858644U (en) * | 2018-06-11 | 2019-05-14 | 华南理工大学 | A kind of centrifugal compressor with narrowed type diffuser and local guide vane |
| CN111120400A (en) * | 2019-12-24 | 2020-05-08 | 哈尔滨工程大学 | Centrifugal compressor for micro gas turbine |
| JP2021124069A (en) * | 2020-02-06 | 2021-08-30 | 三菱重工業株式会社 | Compressor housing, compressor with compressor housing, and turbocharger with compressor |
| CN216589292U (en) * | 2021-12-16 | 2022-05-24 | 西北工业大学 | Centrifugal compressor stage serial diffuser |
| CN115045722A (en) * | 2022-05-27 | 2022-09-13 | 中国航发湖南动力机械研究所 | Transonic speed guider applied to centripetal turbine and centripetal turbine |
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