CN115962153A - Compressor and engine with narrowed runner width at noon of transition section - Google Patents
Compressor and engine with narrowed runner width at noon of transition section Download PDFInfo
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- CN115962153A CN115962153A CN202310259025.2A CN202310259025A CN115962153A CN 115962153 A CN115962153 A CN 115962153A CN 202310259025 A CN202310259025 A CN 202310259025A CN 115962153 A CN115962153 A CN 115962153A
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The application provides a compressor and an engine with a narrowed runner width at noon of a transition section, which comprise an impeller, the transition section and a diffuser with blades, 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 diffuser with blades; the meridian flow channel of the transition section comprises a first molded line on the hub side and a second molded line on the casing side; at least part of the meridian flow channel 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 channel of the transition section along the air flow direction at the contraction section; the direction of the air flow is 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 towards the center line, the width of a meridian flow channel can be reduced, the tangential speed of compressed gas on the casing side of the transition section is improved, the tangential speed of the compressed gas passing through the impeller is rectified, the non-uniformity of the tangential speed at the air inlet of the vane diffuser in the height direction of the vanes is reduced, and the efficiency of the air compressor is improved.
Description
Technical Field
The invention relates to the technical field of gas compressors, in particular to a gas compressor with a narrowed midday flow passage width at a transition section and an engine.
Background
In the compressor, after air is compressed by an impeller, the tangential velocity distribution of the compressed air at the outlet of the impeller is uneven. A typical tangential velocity profile of air at the impeller exit is shown in figure 2.
In the existing gas compressor, the transition section between the impeller and the bladed diffuser is designed to be equal in width, that is, in the existing gas compressor, the width of a meridian flow passage of the transition section is equal from the gas inlet to the gas 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 air inlet of the vane diffuser still presents an uneven state as shown in fig. 2, and the uneven tangential velocity distribution state can cause the overall efficiency of the compressor to be lower.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a compressor and an engine with a narrowed midday flow passage width at a transition section, so as to improve the tangential velocity distribution condition of gas at the air inlet of a vane diffuser of the compressor and improve the efficiency of the compressor.
The application provides a compressor with a narrowed runner width at noon of a transition section, which comprises an impeller, the transition section and a diffuser with blades, 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 diffuser with blades;
the meridian flow channel of the transition section comprises a first molded line on the hub side and a second molded line on the casing side;
at least one part of the meridian flow passages 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 passages of the transition section along the air flow direction at the contraction section;
one part of the meridian flow channel of the transition section is a contraction section, the other part of the meridian flow channel 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 contraction section, the parts of the first molded lines except the grooves and the second molded lines are parallel to the central line of the meridian flow channel of the transition section;
the air flow direction is a 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 ends of the parallel sections, 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 section includes 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.
Optionally, the portions of the first profile and the second profile located in the contraction section are both curves.
Optionally, the portions of the first profile and the second profile located in the contraction section are both straight lines.
The application also provides an engine, which at least comprises a combustion chamber, a turbine and the compressor of any one of the applications;
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 midday flow passage width at a transition section, which comprise an impeller, the transition section and a diffuser with blades, 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 diffuser with blades; the meridian flow channel of the transition section comprises a first molded line on the hub side and a second molded line on the casing side; at least one part of the meridian flow channel 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 channel of the transition section along the air flow direction at the contraction section; the direction of the air flow is 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 towards the center line, the width of a meridian flow channel can be reduced, and the tangential speed of compressed gas on the casing side of the transition section is improved, so that the tangential speed of the compressed gas passing through the impeller is rectified, the unevenness of the tangential speed at the air inlet of the vane diffuser in the height direction of the vane is reduced, and the efficiency of the gas compressor is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a schematic view of a radial flow channel of a conventional compressor provided in an embodiment of the present application;
FIG. 2 is a schematic diagram illustrating a tangential velocity distribution of air at an outlet of a compressor wheel according to an exemplary embodiment of the present disclosure;
fig. 3 is a schematic view of a radial flow channel of a compressor with a narrowed radial flow channel width in a transition section provided in an embodiment of the present application;
FIG. 4 is a schematic view of a meridian flow path of a transition section provided in an embodiment of the present application;
FIG. 5 is a schematic representation of a radial flow path of another transition section provided in an embodiment of the present application;
FIG. 6 is a schematic representation of a meridian flow path of yet another transition section provided in an embodiment of the present application;
FIG. 7 is a schematic representation of a radial flow path of yet another transition section provided by an embodiment of the present application;
FIG. 8 is a schematic representation of a meridian flow path of a transition section provided in accordance with an embodiment of the present application;
fig. 9 is a schematic diagram of a tangential velocity distribution of air at an air inlet of a bladed diffuser in a compressor with a narrowed radial flow path width in a transition section according to an embodiment of the present application.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
To facilitate understanding of the technical solutions of the present application, some terms that may be referred to will be described first.
The turbocharger, actually an air compressor, is composed of a turbine and a compressor which are coaxial, when exhaust gas discharged from an engine flows through the turbine, the inertia impulse of the exhaust gas pushes the turbine to rotate, and the turbine drives an impeller of the compressor to rotate, so that air is compressed to increase the air inflow.
Impeller: the impeller is formed by impeller blades (called blades for short) arranged on a hub in a radial curve manner, and the blades are three-element curved surface thin-wall impeller blades generally.
The diffuser with vanes is positioned at the rear end of the impeller, and the velocity 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 shape of the vane limits the flow direction of air flow so as to reduce tangential velocity of the compressed air and increase the static pressure of the compressed air.
A meridian flow passage: is a physical term. Is a projection of the impeller-type air flow passage on a meridian plane. A meridian plane is understood to mean any plane passing through the axis of the impeller.
Please refer to fig. 1, which is a schematic view of a radial flow channel of a conventional compressor, wherein the radial flow channel of an impeller (i.e. a projection of a flow channel of the impeller on a radial plane) is 100, where 101 is an air inlet of the compressor, and 102 is an air outlet of the compressor.
The meridian flow passage (i.e. the projection of the airflow passage of the vane diffuser on the meridian plane) of the vane diffuser is 300, wherein 301 is the air inlet of the vane diffuser, and 302 is the air outlet of the vane diffuser.
The impeller and the bladed diffuser of the compressor are connected through a transition section, and the meridian flow passage (namely the projection of the airflow channel of the transition section on the meridian plane) of the transition section is 200. 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 connected with the air inlet of the diffuser with blades.
When the air compressor works, air enters the impeller from the air inlet of the impeller, the air compressed by the impeller enters the transition section from the air outlet of the impeller, flows through the transition section and then enters the bladed diffuser, is further compressed in the bladed diffuser, and then enters a part at the rear end of the air compressor from the air outlet of the bladed diffuser.
As can be seen from fig. 1, the radial flow channels of the transition section of the conventional compressor are designed to have equal widths, that is, the widths of the radial flow channels of the transition section are equal everywhere along the flow direction of the gas flow, and correspondingly, the areas of the cross sections of the transition section are equal everywhere along the flow direction of the gas flow. The cross section of the transition section refers to the section of the transition section perpendicular to the flow direction of the gas flow.
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 the arrow 20 in fig. 1.
As described in the background section, the velocity of the compressed gas flowing through the transition section cannot be adjusted by the transition section of this structure, so in the conventional compressor, the distribution of the tangential velocity of the compressed gas flowing before and after the transition section along the height direction of the blade is substantially constant.
The distribution of the tangential velocity of the compressed gas at the impeller gas outlet along the height of the blades can be seen in figure 2.
In fig. 2, the horizontal axis is speed in meters per second and the vertical axis is normalized blade height, where 1 represents the height of the blade tip, corresponding to the case side in the present embodiment, and 0 represents the height of the blade root, corresponding to the hub side in the present embodiment.
As can be seen from the distribution of fig. 2, the tangential velocity of the compressed gas at the impeller gas outlet is distributed along the height direction of the blades to a high degree.
Due to the transition section structure of the existing compressor, the condition of non-uniform tangential velocity shown in fig. 2 continues to the air inlet of the vaned diffuser, that is, in the existing compressor, the tangential velocity of the gas at the air inlet of the vaned diffuser is also in non-uniform distribution as shown in fig. 2 along the height distribution of the blades, and the non-uniform tangential velocity causes the reduction of the compression efficiency of the vaned diffuser, thereby causing the reduction of the overall efficiency of the compressor.
One solution to this problem is to increase the twist of the vanes in the vaned diffuser, but this solution increases the manufacturing cost of the vanes in the vaned diffuser and reduces the reliability of the vanes, and on the other hand only partially alleviates the non-uniform tangential velocity.
In view of the above problems, an embodiment of the present application provides a compressor with a narrowed radial flow passage in a transition section, please refer to fig. 3, which is a schematic view of a radial flow passage of a compressor with a narrowed radial flow passage in a transition section according to an embodiment of the present application.
The transition section of the compressor has the following characteristics:
at least a part of the flow passage of the transition section is a constricted section in which both the casing-side wall surface and the hub-side wall surface approach the inside of the flow passage in the flow direction, in other words, in the constricted section, both the casing-side wall surface and the hub-side wall surface converge toward the inside of the flow passage in the flow 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 profile on the hub side and the second profile on the casing side approach the center line 205 of the meridian flow channel of the transition section along the air flow direction, in other words, in the contraction section, both the first profile and the second profile contract toward the center line 205.
The air flow channel of the transition section thus assumes a state in which the cross-sectional area is gradually reduced in the direction of air flow in the constriction section, i.e. the air flow channel is gradually narrowed in the direction of air flow in the constriction section.
In the airflow channel with the structure, on one hand, the wall surface of the side of the casing (Shroud) shrinks towards the center, and the tangential speed of the gas at the side of the casing can be improved when the compressed gas flows through the transition section; on the other hand, the wall surface of the Hub (Hub) side shrinks towards the center, so that the tangential velocity of the gas on the Hub side can be improved when the compressed gas flows through the transition section, and the tangential velocity distribution of the gas at the gas outlet of the transition section tends to be uniformly distributed by combining the two factors, thereby improving the compression efficiency of the vaned diffuser.
As can be seen from fig. 3, the compressor comprises an impeller, a transition section and a vaned diffuser, wherein an outlet of the impeller is connected with an inlet of the transition section, and an outlet of the transition section is connected with an inlet of the vaned diffuser.
In fig. 3, the inlet of the transition section is 201 and the outlet of the transition section is 202. The portion of the transition section where the meridian flow paths are within the rectangular frame 210 is the aforementioned convergent section.
The meridian flow path of the transition section includes a first profile on the hub (hub) side and a second profile on the casing (shroud) side.
In fig. 3, the first profile is 203 and the second profile is 204. The first profile can be regarded as a projection of the hub side wall surface in the air flow channel of the transition section on the meridian plane, and the second profile can be regarded as a projection of the casing side wall surface in the air flow channel of the transition section on the meridian plane.
In some optional embodiments, in the transition section of the compressor provided by the present application, the contraction section of the radial flow channel of the compressor may be a part of the transition section sub-radial flow channel, that is, the radial flow channel 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, in the parallel section, both the first profile and the second profile are parallel to the central line of the radial flow channel of the transition section, that is, in the parallel section, the air flow channel still adopts an equal-width design.
In the case that the transition section midday flow channel includes a contraction section and a parallel section, the position of the contraction section in the transition section midday flow channel can be set according to actual conditions.
An alternative location for the constriction is to locate the constriction at the end of the transition sub-meridian passage adjacent the impeller. Particularly, 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 meridional flow passage of the transition section may have a shape as shown in fig. 3, and it can be seen that the compressed gas passing through the impeller enters the transition section, passes through the contraction section first, then passes through the parallel section, and then exits the transition section from the gas outlet of the transition section after passing through the parallel section.
An alternative location for the constrictor is where the constrictor is located at the end of the transition segment flowpath adjacent the vaned diffuser. Particularly, 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 flow passage of the transition section may have a shape as shown in fig. 4, and it can be seen that the compressed gas passing through the impeller enters the transition section, passes through the parallel section first, 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 position for the constriction is that the constriction is located in the middle of the transition flow path. Specifically, the parallel section is divided into two parts, which are respectively marked as a first parallel section and a second parallel section, the head end of the first parallel section is located 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 located at the air outlet of the transition section.
In this case, the meridian flow passages of the transition section may have a shape as shown in fig. 5, and fig. 5 is a schematic view of another meridian flow passage of the transition section provided in an embodiment of the present application. In the structure, after flowing out of the impeller, the compressed gas firstly passes through the first parallel section, then enters the contraction section from the first parallel section, flows through the contraction section, then enters the second parallel section, and finally flows through the second parallel section to reach the gas outlet of the transition section.
Optionally, when the meridian flow path of the transition section is divided into a contraction section and a parallel section, a groove structure may be disposed on the first mold line located on the hub side, please refer to fig. 6, which is a schematic view of the meridian flow path of the transition section when the groove structure is disposed.
It will be seen that when the convergent section is located near one end of the impeller, the channel may be located at the head end of the parallel section, i.e. at the junction of the convergent and parallel sections. Set up the slot structure, can adjust the tangential velocity of wheel hub side compressed gas to reduce the compressed gas in the unevenness of blade direction of height, be favorable to diffuser blade design, manufacturing and efficiency promotion, thereby be favorable to the efficiency promotion of booster pressure end.
In addition to the above arrangement, when the contraction section is located near one end of the vaned diffuser, the groove structure of the first profile may also be located at the head end of the contraction section. When the constriction section is located between the first parallel section and the second parallel section, the groove structure may be arranged at a head end of the first parallel section, or may be arranged at a head end of the second parallel section.
The benefit of setting up above trench structure lies in:
the groove structure arranged on the side of the hub can reduce the tangential velocity of the gas close to the side of the hub, so that the tangential velocity of the gas on the side of the hub is lower than that of the gas on the side of the casing, and the uniformity of the tangential velocity of the air at the air inlet of the vaned diffuser along the height direction of the blades is improved.
Meanwhile, the groove structure reduces the tangential velocity of the gas close to the hub side, and naturally also reduces the average tangential velocity at the air inlet of the vane diffuser, so that the condition that the tangential velocity of the gas entering the vane diffuser is too high to generate large flow loss can be avoided.
In conclusion, through the groove structure arranged on the first molded line, the uniformity of the tangential speed of air at the air inlet of the vane diffuser along the height direction of the vane can be improved on the premise of not increasing the flow loss in the vane diffuser.
In some alternative embodiments, the meridional flow paths of the transition section are convergent sections from the inlet of the transition section to the outlet of the transition section.
In this case, the radial flow channels of the transition section may have a shape as shown in fig. 7, and fig. 7 is a schematic view of a radial flow channel of another transition section provided in an embodiment of the present application.
As can be seen from fig. 7, in this case, the first profile continuously converges from the inlet of the transition section in the air flow direction towards the center line of the midday flow channel of the transition section until the outlet of the transition section, and the second profile continuously converges from the inlet of the transition section in the air flow direction towards the center line of the midday flow channel of the transition section until the outlet of the transition section. Correspondingly, the area of the cross section of the transition section airflow channel is gradually reduced from the air inlet to the air outlet, and after the compressed gas enters the transition section from the impeller, the compressed gas is continuously compressed in the continuous transition section airflow channel until the compressed gas leaves 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 in a linear manner, and correspondingly, in the contraction section, the first profile and the second profile may present a curved line as shown in fig. 3 to fig. 7 or may be a linear line.
For example, when the portions of the first and second profiles in the convergent section are straight lines, the meridional flow channel of the transition section may have a shape as shown in fig. 8, and fig. 8 is a schematic view of another meridional flow channel of the transition section provided in the embodiments of the present application.
As a further alternative, the wall surfaces on the casing side and on the hub side can also be retracted in the retraction section in different ways. Correspondingly, the first profile and the second profile may present different profiles.
For example, the inner wall surface of the contraction section may be configured such that the wall surface on the casing side contracts in a curved manner, the wall surface on the hub side contracts in a linear manner, and correspondingly, the portion of the first molded line formed by projection of the side wall surface of the hub in the contraction section is a straight line, and the portion of the second molded line formed by projection of the side wall surface of the casing in the contraction section is a curved line.
Or, the other way around, namely, the wall surface on the hub side is shrunk in a curved manner, the wall surface on the casing side is shrunk in a linear manner, correspondingly, the part of the first molded line formed by the projection of the side wall surface of the hub in the shrinking section is a curve, and the part of the second molded line formed by the projection of the side wall surface of the casing in the shrinking section is a straight line.
It should be noted that, when the portion of the first profile and/or the second profile located in the shrinking section is a curve, the curve may be any form of curve, including but not limited to a spline curve, an arc curve, a polynomial curve, and the like, which is not limited in this embodiment.
When the transition section of the compressor has the above-mentioned characteristic of narrowing gradually in the direction of gas flow in the contraction section, the transition section can increase the tangential velocity of the compressed gas flowing through the transition section on the casing side and the hub side, so that the gas flowing through the transition section and reaching the inlet of the vaned diffuser has a more uniform tangential velocity distribution in the height direction of the blades. Referring to fig. 9, in a compressor with a narrowed meridian flow passage in a transition section according to an embodiment of the present application, a tangential velocity distribution diagram of air at an air inlet of a vaned diffuser is provided.
Comparing fig. 2 and fig. 9, it can be seen that when the transition section structure provided in the embodiment of the present application is adopted, after the compressed gas flows through the transition section, the tangential velocities of the casing side and the hub side are significantly increased, and correspondingly, the tangential velocities of the air at the air 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 the air at the air inlet of the vane diffuser along the height direction of the vane, improve the compression efficiency of the vane 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 inlet of the turbine is connected to the outlet of the combustion chamber.
Based on the connection relationship, the compressor can compress the sucked air and then send the compressed air into the combustion chamber for combustion.
Waste gas generated after combustion in the combustion chamber can enter the turbine so as to drive the turbine to rotate, the turbine can drive the air compressor to rotate after rotating, and particularly, the impeller of the air compressor can be driven to rotate, so that air compression is realized.
The combustion chamber may be specifically one or more cylinders, and may have other structures, without limitation.
Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be 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. Also, 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 phrases "comprising one of 8230; \8230;" 8230; "does not exclude the presence of additional 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 in the present invention are only used for distinguishing different devices, modules or units, and are not used for limiting the order or interdependence relationship of the functions performed by the devices, modules or units.
A person 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 runner width at noon of the transition section is characterized by comprising an impeller, the transition section and a diffuser with blades, 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 diffuser with blades;
the meridian flow channel of the transition section comprises a first molded line on the hub side and a second molded line on the casing side;
at least one part of the meridian flow passages 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 passages of the transition section along the air flow direction at the contraction section;
one part of the meridian flow channel of the transition section is a contraction section, the other part of the meridian flow channel 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 contraction section, the parts of the first molded lines except the grooves and the second molded lines are parallel to the central line of the meridian flow passage of the transition section;
the air flow direction is a 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, and an aft end of the convergent section is connected to a head end of the parallel section, and an aft end of the parallel section is located at an air outlet of the transition section.
3. The compressor of claim 1, wherein an aft end of the convergent section is located at an air outlet of the transition section, a head end of the convergent section is connected to an aft end of the parallel section, and a head end of the parallel section is located at an air 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 the portions of the first and second profiles in the converging section are both curved.
6. The compressor of any one of claims 1 to 4, wherein the portions of the first profile and the second profile located in the convergent section are both straight lines.
7. An engine comprising at least a combustion chamber, a turbine and a compressor according to 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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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN117436210A (en) * | 2023-12-18 | 2024-01-23 | 潍柴动力股份有限公司 | Combined design method and device for widening flow grooves and impellers |
| 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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| CN115962153B (en) | 2023-06-23 |
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