CN115962154A - Compressor with transition section meridian flow channel narrowed at casing side, engine and automobile - Google Patents
Compressor with transition section meridian flow channel narrowed at casing side, engine and automobile Download PDFInfo
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- CN115962154A CN115962154A CN202310259863.XA CN202310259863A CN115962154A CN 115962154 A CN115962154 A CN 115962154A CN 202310259863 A CN202310259863 A CN 202310259863A CN 115962154 A CN115962154 A CN 115962154A
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- 230000007704 transition Effects 0.000 title claims abstract description 140
- 238000002485 combustion reaction Methods 0.000 claims description 23
- 230000008602 contraction Effects 0.000 claims description 16
- 239000004973 liquid crystal related substance Substances 0.000 claims 1
- 238000000465 moulding Methods 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 31
- 238000000034 method Methods 0.000 description 6
- 230000009471 action Effects 0.000 description 3
- 230000006835 compression Effects 0.000 description 3
- 238000007906 compression Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000009467 reduction Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The application provides a compressor, an engine and an automobile with a transition section meridian flow passage narrowed at a casing side, 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; 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; the first molded line of the transition section is vertical to the axis of the compressor; the width of the meridian flow channel of the transition section at the air inlet of the transition section is larger than that of the meridian flow channel of the transition section at the air outlet of the transition section. The second molding line positioned on the casing side in the transitional section radial flow channel shrinks towards the hub side, so that the tangential speed of the compressed gas on the transitional section casing side can be increased, 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 vanes is reduced, and the efficiency of the gas compressor is improved.
Description
Technical Field
The invention relates to the technical field of gas compressors, in particular to a gas compressor with a transition section runner narrowed at a casing side, an engine and an automobile.
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
In view of the defects of the prior art, the invention provides a compressor, an engine and an automobile with a transition section meridian flow passage narrowed at a casing side, so as to improve the tangential velocity distribution condition of gas at an air inlet of a bladed diffuser of the compressor and improve the efficiency of the compressor.
The application provides a compressor with a transition section meridian flow passage narrowed at a casing side, which comprises an impeller, a 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;
a first molded line of the transition section is perpendicular to the axis of the compressor;
the width of the meridian flow channel of the transition section at the air inlet of the transition section is greater than that of the meridian flow channel of the transition section at the air outlet of the transition section;
the second molded lines comprise shrinkage molded lines and parallel molded lines;
the parallel molded line is parallel to the first molded line;
the width of the meridian flow channel of the transition section at the head end of the shrinkage molded line is greater than the width of the meridian flow channel of the transition section at the tail end of the shrinkage molded line;
in the contraction molded line, one end close to the impeller is a head end, and one end close to the vane diffuser is a tail end;
the structure of the second molded line is as follows:
the tail end of the contraction molded line is positioned at the air outlet of the transition section, the head end of the contraction molded line is connected with the tail end of the parallel molded line, and the head end of the parallel molded line is positioned at the air inlet of the transition section;
alternatively, the first and second electrodes may be,
the parallel molded lines comprise a first parallel molded line and a second parallel molded line, the contraction molded line is positioned between the first parallel molded line and the second parallel molded line, the head end of the first parallel molded line is positioned at the air inlet of the transition section, and the tail end of the second parallel molded line is positioned at the air outlet of the transition section.
Optionally, the shrinkage profile is a curve.
Optionally, the shrink profile is a straight line.
The application also provides an engine, which at least comprises a combustion chamber, a turbine and the compressor provided by 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 also provides an automobile, wherein an engine of the automobile at least comprises a combustion chamber, a turbine and the compressor provided by 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, an engine and an automobile with a transition section meridian flow passage narrowed at a casing side, 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; 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; the first molded line of the transition section is vertical to the axis of the compressor; the width of the meridian flow channel of the transition section at the air inlet of the transition section is larger than that of the meridian flow channel of the transition section at the air outlet of the transition section. The second molding line positioned on the casing side in the transitional section meridian flow channel shrinks towards the hub side, so that the tangential speed of the compressed gas on the transitional section casing side can be increased, 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 vanes 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 an impeller of a conventional compressor according to an embodiment of the present disclosure;
fig. 3 is a schematic view of a radial flow channel of a compressor in which a radial flow channel of a transition section is narrowed at a casing side according to 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 meridian flow path of yet another transition section provided in an embodiment of the present application;
fig. 8 is a schematic diagram of a tangential velocity distribution of air at an inlet of a vaned diffuser in a compressor in which a transition section meridian flow path is narrowed at a casing side 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 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 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 vane diffuser, is further compressed in the vane diffuser, and then enters a component at the rear end of the air compressor from the air outlet of the vane 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 denotes the height of the blade tip, corresponding to the case side in the present embodiment, and 0 denotes 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 non-uniformly distributed along the height distribution of the vanes as shown in fig. 2, and the non-uniformly distributed 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, embodiments of the present application provide a compressor with a transition section radial flow channel narrowed at a casing side, where the transition section of the compressor has the following features:
in the meridian flow channel of the transition section, the second molding line on the side of the casing is totally or partially contracted towards the side of the hub, so that the width of the meridian flow channel of the transition section at the air outlet of the transition section is smaller than the width of the meridian flow channel of the transition section at the air inlet of the transition section. Therefore, the airflow channel of the transition section presents a state that the area of the cross section is gradually reduced from the casing side along the airflow direction, and the airflow channel with the structure can improve the tangential speed of the gas on the casing side when the compressed gas flows through the transition section, so that the tangential speed distribution of the gas at the gas outlet of the transition section tends to be uniformly distributed.
Referring to fig. 3, a schematic view of a radial flow channel of a compressor with a transition section radial flow channel narrowed at a casing side is provided according to an embodiment of the present application.
It can be seen that the compressor comprises an impeller, a transition section and a vaned diffuser, wherein the outlet of the impeller is connected to the inlet of the transition section and the outlet of the transition section is connected to the 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 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.
The first molded line of the transition section is perpendicular to the axis of the compressor.
The width of the meridian flow channel of the transition section at the air inlet of the transition section is larger than that of the meridian flow channel of the transition section at the air outlet of the transition section.
It will be appreciated that the present application provides a compressor transition section in which the casing side wall surface can be retracted toward the hub side in a variety of ways.
An alternative way of collapsing is to have the casing side wall surface collapse from the transition section air inlet to a distance parallel to the hub side wall surface.
In this case, the meridian flow passage of the transition section may have a shape as shown in fig. 3, and it can be seen that a part of the second profile is a contracted profile and another part is a parallel profile;
the parallel molded line is parallel to the first molded line;
the width of the meridian flow channel of the transition section at the head end of the shrinkage molded line is larger than the width of the meridian flow channel of the transition section at the tail end of the shrinkage molded line;
in the contraction molded line, one end close to the impeller is a head end, and the other end close to the diffuser with the blades is a tail end.
And the head end of the contraction molded line is positioned at the air inlet of the transition section, the tail end of the contraction molded line is connected with the head end of the parallel molded line, and the tail end of the parallel molded line is positioned at the air outlet of the transition section.
An alternative way of contracting is that, from the air inlet of the transition section, the wall surface of the casing side is parallel to the wall surface of the hub side, and after a certain distance, the contracting towards the hub side is started until the air outlet of the transition section.
In this case, the radial flow channels of the transition section may have a shape as shown in fig. 4, and fig. 4 is a schematic view of the radial flow channels of the transition section according to an embodiment of the present invention. It can be seen that, in the second profile of the transition section, the tail end of the shrinkage profile is located at the air outlet of the transition section, the head end of the shrinkage profile is connected with the tail end of the parallel profile, and the head end of the parallel profile is located at the air inlet of the transition section.
An alternative contraction mode is that from the air inlet of the transition section, the wall surface of the casing side is kept parallel to the wall surface of the hub side, after a certain distance, the casing side and the hub side begin to contract, after a certain distance, the casing side and the hub side again keep parallel until the air outlet of the transition section.
In this case, the radial flow channels of the transition section may have a shape as shown in fig. 5, and fig. 5 is a schematic view of another radial flow channel of the transition section provided in the embodiment of the present application.
It can be seen that the parallel profile now includes a first parallel profile and a second parallel profile; the head end of the first parallel molded line is positioned at the air inlet of the transition section, the tail end of the first parallel molded line is connected with the head end of the contraction molded line, the tail end of the contraction molded line is connected with the head end of the second parallel molded line, and the tail end of the second parallel molded line is positioned at the air outlet of the transition section.
An alternative way of collapsing is to start the wall of the casing side from the transition section air inlet to the hub side until the transition section air outlet.
In this case, the radial flow channels of the transition section may have a shape as shown in fig. 6, and fig. 6 is a schematic view of a radial flow channel of another transition section provided in an embodiment of the present application.
The width of the meridian flow channel of the transition section at the head end of the shrinkage profile line is larger than that of the meridian flow channel of the transition section at the tail end of the shrinkage profile line;
in the contraction molded line, one end close to the impeller is a head end, and the other end close to the diffuser with the blades is a tail end.
It should be noted that, in the compressor provided in the embodiment of the present application, the wall surface on the casing side of the transition section may be shrunk in a curved manner or in a linear manner, and correspondingly, in the second profile on the casing side, the shrunk profile may be a curve as shown in fig. 3 to fig. 6 or a straight line.
Further, when the second profile is a curve, it may be a curve in any form, for example, the second profile may be a polynomial curve generated based on a preset polynomial, may be a spline curve generated based on a plurality of designated control points, or may be an arc with a preset radius, and this embodiment does not limit the specific form of the curve.
For example, when the contraction profile is a straight line, the meridian flow channel of the transition section may have a shape as shown in fig. 6, and fig. 6 is a schematic view of a meridian flow channel of another transition section provided in an embodiment of the present application.
When the transition section of the compressor has the characteristic that the cross-sectional area is gradually reduced from the casing side, the transition section can increase the tangential velocity of the compressed gas flowing through the transition section on the casing side. Referring to fig. 8, in a compressor in which a transition section meridian flow path is narrowed at a casing side, a tangential velocity distribution diagram of air at an air inlet of a vaned diffuser is provided according to an embodiment of the present application.
Comparing fig. 2 and fig. 8, it can be seen that, when the transition section structure provided by the embodiment of the present application is adopted, after the compressed gas flows through the transition section, the tangential velocity of the casing side is significantly increased, and correspondingly, the tangential velocity of the air at the air inlet of the vaned diffuser is uniformly distributed along the vane height direction. Therefore, the transition section structure provided by the embodiment of the application and shown in fig. 3 to 7 can improve the distribution condition of the tangential speed 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 compressor to rotate after rotating, and particularly, the turbine can drive the impeller of the compressor to rotate so as to compress air.
The combustion chamber may be specifically one or more cylinders, and may have other structures, without limitation.
The embodiment of the application also provides an automobile, wherein an engine of the automobile at least comprises a combustion chamber, a turbine and the compressor provided by 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 inlet of the turbine is connected to the outlet of the combustion chamber.
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.
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 (5)
1. A compressor with a transition section meridian flow passage narrowed at a casing side is characterized by comprising an impeller, a transition section and a diffuser with blades, wherein an air outlet of the impeller is connected with an air inlet of the transition section;
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;
a first molded line of the transition section is perpendicular to the axis of the compressor;
the width of the meridian flow channel of the transition section at the air inlet of the transition section is greater than that of the meridian flow channel of the transition section at the air outlet of the transition section;
the second molded lines comprise shrinkage molded lines and parallel molded lines;
the parallel molded line is parallel to the first molded line;
the width of the meridian flow channel of the transition section at the head end of the shrinkage molded line is greater than the width of the meridian flow channel of the transition section at the tail end of the shrinkage molded line;
in the contraction molded line, one end close to the impeller is a head end, and one end close to the diffuser with the blades is a tail end;
the structure of the second molded line is as follows:
the tail end of the contraction molded line is positioned at the air outlet of the transition section, the head end of the contraction molded line is connected with the tail end of the parallel molded line, and the head end of the parallel molded line is positioned at the air inlet of the transition section;
alternatively, the first and second liquid crystal display panels may be,
the parallel molded lines comprise a first parallel molded line and a second parallel molded line, the contraction molded line is positioned between the first parallel molded line and the second parallel molded line, the head end of the first parallel molded line is positioned at the air inlet of the transition section, and the tail end of the second parallel molded line is positioned at the air outlet of the transition section.
2. An air compressor according to claim 1, characterized in that the shrink profile is a curve.
3. An air compressor according to claim 1, characterized in that the shrink profile is a straight line.
4. An engine comprising at least a combustion chamber, a turbine and a compressor according to any one of claims 1 to 3;
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.
5. A motor vehicle, characterized in that the engine of the motor vehicle comprises at least a combustion chamber, a turbine and a compressor according to any one of claims 1 to 3;
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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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310259863.XA CN115962154A (en) | 2023-03-17 | 2023-03-17 | Compressor with transition section meridian flow channel narrowed at casing side, engine and automobile |
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| CN202310259863.XA CN115962154A (en) | 2023-03-17 | 2023-03-17 | Compressor with transition section meridian flow channel narrowed at casing side, engine and automobile |
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Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH322420A (en) * | 1953-07-01 | 1957-06-15 | Maschf Augsburg Nuernberg Ag | Centrifugal machine of radial design |
| SU572586A1 (en) * | 1976-02-17 | 1977-09-15 | Николаевский Ордена Трудового Красного Знамени Кораблестроительный Институт Им.Адмилара С.О.Макарова | Vaned diffuser of centrifugal compressor |
| SU688705A1 (en) * | 1978-04-20 | 1979-09-30 | Ленинградский Ордена Ленина Политехнический Институт Им. М.И.Калинина | Centrifugal compressor stage |
| JP2001248597A (en) * | 2000-03-02 | 2001-09-14 | Hitachi Ltd | Turbo compressor and turbo blower |
| JP2004197612A (en) * | 2002-12-17 | 2004-07-15 | Ishikawajima Harima Heavy Ind Co Ltd | Centrifugal compressor |
| EP1574667A1 (en) * | 2004-03-02 | 2005-09-14 | Siemens Aktiengesellschaft | Diffuser for compressor |
| CN1791738A (en) * | 2003-05-15 | 2006-06-21 | 沃尔沃拉斯特瓦格纳公司 | Turbocompressor system for an internal combustion engine |
| CN201090462Y (en) * | 2007-08-15 | 2008-07-23 | 沈阳鼓风机(集团)有限公司 | Enclosed high energy head model level |
| JP2010144698A (en) * | 2008-12-22 | 2010-07-01 | Ihi Corp | Centrifugal compressor |
| JP2019167871A (en) * | 2018-03-23 | 2019-10-03 | 株式会社Ihi | Vaned diffuser and centrifugal compressor |
| CN115038878A (en) * | 2020-01-07 | 2022-09-09 | 涡轮增压系统瑞士有限公司 | Outflow region of a compressor, compressor having an outflow region of said type and turbocharger having a compressor |
-
2023
- 2023-03-17 CN CN202310259863.XA patent/CN115962154A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH322420A (en) * | 1953-07-01 | 1957-06-15 | Maschf Augsburg Nuernberg Ag | Centrifugal machine of radial design |
| SU572586A1 (en) * | 1976-02-17 | 1977-09-15 | Николаевский Ордена Трудового Красного Знамени Кораблестроительный Институт Им.Адмилара С.О.Макарова | Vaned diffuser of centrifugal compressor |
| SU688705A1 (en) * | 1978-04-20 | 1979-09-30 | Ленинградский Ордена Ленина Политехнический Институт Им. М.И.Калинина | Centrifugal compressor stage |
| JP2001248597A (en) * | 2000-03-02 | 2001-09-14 | Hitachi Ltd | Turbo compressor and turbo blower |
| JP2004197612A (en) * | 2002-12-17 | 2004-07-15 | Ishikawajima Harima Heavy Ind Co Ltd | Centrifugal compressor |
| CN1791738A (en) * | 2003-05-15 | 2006-06-21 | 沃尔沃拉斯特瓦格纳公司 | Turbocompressor system for an internal combustion engine |
| EP1574667A1 (en) * | 2004-03-02 | 2005-09-14 | Siemens Aktiengesellschaft | Diffuser for compressor |
| CN201090462Y (en) * | 2007-08-15 | 2008-07-23 | 沈阳鼓风机(集团)有限公司 | Enclosed high energy head model level |
| JP2010144698A (en) * | 2008-12-22 | 2010-07-01 | Ihi Corp | Centrifugal compressor |
| JP2019167871A (en) * | 2018-03-23 | 2019-10-03 | 株式会社Ihi | Vaned diffuser and centrifugal compressor |
| CN115038878A (en) * | 2020-01-07 | 2022-09-09 | 涡轮增压系统瑞士有限公司 | Outflow region of a compressor, compressor having an outflow region of said type and turbocharger having a compressor |
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