CN104755768A - Diffuser assembly comprising diffuser vanes pivoting about the leading edge - Google Patents
Diffuser assembly comprising diffuser vanes pivoting about the leading edge Download PDFInfo
- Publication number
- CN104755768A CN104755768A CN201380051296.3A CN201380051296A CN104755768A CN 104755768 A CN104755768 A CN 104755768A CN 201380051296 A CN201380051296 A CN 201380051296A CN 104755768 A CN104755768 A CN 104755768A
- Authority
- CN
- China
- Prior art keywords
- diffuser
- leading edge
- stator
- axis
- spin axis
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/52—Outlet
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Embodiments of a diffuser assembly incorporate a diffuser vane with a trailing edge that changes position to improve flow performance of a compressor device. In one embodiment, the trailing edge rotates about the leading edge. This configuration maintains the position of the leading edge on the diffuser vanes relative to the orientation of the working fluid.
Description
Background technique
Theme disclosed herein relates to compressor set (such as, centrifugal compressor), and the diffuser related to particularly for compressor set and diffuser stator.
The speed that compressor set (such as, centrifugal compressor) uses diffuser assembly to pass expanding volume region by the working fluid that slows down converts the kinetic energy of working fluid to static pressure.The example of diffuser assembly usually use around impeller axial arranged in some diffuser stators.The design (such as, shape and size) of the diffuser stator combined relative to the preferred orientation of working-fluid flow with leading edge and the trailing edge of diffuser stator determines how diffuser stator is attached in diffuser assembly usually.
In order to by further improve and flexibility add in design, some examples of diffuser assembly combine variable diffuser stator.The diffuser stator of these types moves the orientation changing leading edge and trailing edge.This feature contributes to the operation regulating compressor set.The Known designs of variable diffuser stator is enclosed and is rotated about the axis, and axis is arranged in lower half portion, that is, compare the trailing edge of diffuser stator closer to leading edge.
The position of spin axis allow for trailing edge and scans larger angle, and therefore allow for well-tuned and the optimization of compressor performance.But although the use of these variable diffuser stators can improving SNR, the enforcement of the conventional design of variable diffuser stator makes trailing edge and leading edge move (such as, rotating) relative to the working fluid arrived.This feature can have negative effect to compressor performance.The change in location of the leading edge caused by the change of the angular orientation of diffuser stator can cause the surperficial premature disengagement of working fluid stream and diffuser stator, regulates the validity of the performance of compressor set because this reducing variable diffuser stator.
Summary of the invention
Present disclosure presents the embodiment of diffuser assembly, it makes diffuser stator be combined with trailing edge, and trailing edge changes the mobile performance that compressor set is improved in position.But diffuser stator keeps leading edge relative to the position of the orientation of working fluid.When implemented, such as, in compressor set, these embodiments prevent the too early flow separation in the surface of the working fluid of arrival and diffuser stator.At least this feature can provide the good control of compressor performance in larger flow range and optimization.
Accompanying drawing explanation
Now concise and to the point with reference to accompanying drawing, in the accompanying drawings:
Fig. 1 depicts the perspective view of example diffuser stator;
Fig. 2 depicts the detail drawing of the leading edge of the example diffuser stator of Fig. 1;
Fig. 3 depicts the top view of the example diffuser stator of Fig. 1;
Fig. 4 depicts the schematic diagram of the example diffuser assembly in conjunction with multiple diffuser stator, such as, and the diffuser stator of Fig. 1 and 2;
Fig. 5 depicts the side cross-sectional view of the diffuser assembly of Fig. 3; And
Fig. 6 depicts can in conjunction with the perspective view of the exemplary compression machine of diffuser assembly, such as, and the diffuser assembly of Figure 4 and 5.
Under appropriate circumstances, similar reference number represents the identical or corresponding component and unit that run through some views, accompanying drawing not drawn on scale, unless otherwise noted.
Embodiment
Broadly, below discuss the improvement concentrating on diffuser and diffuser assembly design, to realize the superperformance in compressor set, such as, centrifugal compressor.On the one hand, these improve solve due to the diffuser stator in diffuser assembly Angle Position redirect the problem caused.As mentioned below, the embodiment of the diffuser assembly of proposition allows trailing edge undesirably to locate, but keeps the leading edge on diffuser stator relative to the orientation of the flow direction of the working fluid of the diffuser stator flow through in diffuser assembly.
Fig. 1 shows the perspective view of diffuser stator 100.Diffuser stator 100 has the stator body 102 of band leading edge 104 and trailing edge 106.Chord length L limits the crow flight distance between leading edge 104 and trailing edge 106.Stator body 102 has aerodynamic profile (such as, airfoil), and it has the surface, suction side 108 and pressure side surface 110 relative to orientation identification, and the angle of attack of leading edge 104 relative to the flowing F of working fluid.At leading edge 104 place, stator body 102 converges to the tip 112 with spin axis 114.
As shown in the details of Fig. 2, tip 112 is circular, and/or has by the radius R extended from central axis 118
tIPthe crooked outer surface 116 limited.The tip 112 of other example presents the aerodynamic shape (such as, point) keeping diffuser body 102.But present disclosure has also envisioned the structure of the tip 112 had lower than optimum air aerodynamic figure as desired (such as, obtuse shape).
Spin axis 114 is positioned at the nearside of leading edge 104, and such as, in 5% of chord length L or less (measuring from leading edge 104).Depend on the size and dimension of tip 112, other exemplary position of spin axis 114 can at radius R
tIPfind in the region that central axis 118 limits.In an example, spin axis 114 is coaxial with the central axis 118 of tip 112.
As best seen in fig. 3, diffuser stator 100 is actuated around spin axis 114.In an example, diffuser stator 100 rotates the position of trailing edge 106 is become the second place marked by hachure and numeral 122 from primary importance 120.This change can allow the change in the direction along stream F, such as, becomes second F2 directed from first-class F1 orientation.Such as, but the relatively large angular displacement of the trailing edge 106 no matter occurred, leading edge 104 is all fixed on spin axis 114, to limit the position fading to leading edge 104, when trailing edge 106 moves between primary importance 120 and the second place 122.This feature maintains the orientation of leading edge 104 and second F2, and to reduce the possibility of flow separation, the change of the performance of such as compressor set is pointed out in the abundant adjustment of the trailing edge 106 simultaneously provided.
Fig. 4 shows the schematic diagram of the diffuser stator 100 of the part as diffuser assembly 124.In the example in figure 4, diffuser assembly 124 comprises stator array 126, it is characterized by along the multiple diffuser stators 100 around the axial orientation of impeller axis 128.The leading edge 104 of diffuser stator 100 is positioned at the nearside on pivot border 130, and it is marked by the hachure circle with central axis 132 substantially.In one embodiment, multiple pivotal parts 134 is fixed on diffuser stator 100.Pivotal parts 134 keeps the position of leading edge 104, and in an example, power is given diffuser stator 100 and rotate to diverse location to make trailing edge 106, such as, and the primary importance 120 shown in Fig. 3 and between the second place 122.
Pivot border 130 limits the leading edge 104 of diffuser stator 100 such as relative to the circumferential position of impeller axis 128.The movement that the attachable diffuser stator 100 of structure of diffuser assembly 124 limits diffuser stator 100 rotates around spin axis 114.This structure reduces leading edge 104 to greatest extent relative to pivot border 130 and displacement relative to each other.In an example, the spin axis 114 on diffuser stator 100 is aimed at pivot border 130.But in other example, one or more diffuser stator 100 can be spaced apart with pivot border 130, such as, aim at the different circumferential positions relative to impeller axis 128.As shown in Figure 4, diffuser stator can be equally spaced each other.By the angular separation between the attached leading edge 104 of adjacent diffuser stator 100 in position for diffuser stator 100.This structure can guarantee consistent flow separation, such as, by the leading edge 104 of diffuser stator 100 being placed in the known location through stator array 126.
As described above, in the operation period of diffuser assembly 124, the diffuser stator 100 in stator array 126 can rotate (or pivotable) around spin axis 114, such as, to change the Angle Position of trailing edge 106.Angle Position allows to change along the flow direction of working fluid.But, the orientation of leading edge 104 relative to the stream F of working fluid direction and/or directedly keep relatively constant.This feature runs through stator array 126 and provides the more consistent point of contact of working fluid in leading edge 104.Therefore, regardless of the change in location of trailing edge 106, the change in location of leading edge 104 is very little, and the diffuser stator 100 in diffuser assembly 124 then present again working fluid and diffuser stator 100 surface (such as, Fig. 1 suction side surface 108 and pressure side surface 110) minimal flow be separated.
The example of pivotal parts 134 can use the device of some and mechanism to carry out the leading edge 104 of stationary diffuser stator 100 rotatably.Pivotal parts 134 can be the overall extension part of diffuser stator 100, or can as by welding manufacture, or it can be the material pieces of attachment separately.Such as, pin and bearing can insert in diffuser stator 100 along spin axis 114.These elements provide pivot and/or pivoting point, and diffuser stator 100 can rotate around it.In an example, diffuser assembly 124 can comprise multiple bearing device, and one of them bearing device is fixed in the lower surface of each diffuser stator 100.The example of bearing device can connect with actuator, linkage mechanism and other mechanism, moving the diffuser stator 100 given in stator array 126.Bearing device can be aimed at spin axis 114, and/or constructively skew allows diffuser stator 100 to rotate around spin axis 114 as described herein.
Fig. 5 depicts the side cross-sectional view of the diffuser assembly 124 intercepted at the line A-A place of Fig. 4.Diffuser assembly 124 comprises one or more wall member (such as, first wall parts 136 and the second wall member 138).Wall member 136,138 form diffuser chamber 140, and the array 126 of diffuser stator 100 finds in diffuser chamber 140.In one embodiment, diffuser stator 100 is connected to a wall member 136 by pivotal parts 134, on 138.This structure allows diffuser stator 100 to change the position of trailing edge 104 on diffuser stator 100 around spin axis 114 rotation.
Fig. 6 depicts can in conjunction with the perspective view of the example of the compressor set 200 of diffuser assembly (diffuser assemblies 124 such as, in Figure 4 and 5).Compressor 200 has entrance 202 and forms the spiral case 204 of outlet 206.Compressor 200 also comprises driver element 208, and its rotary blade 210 absorbs working fluid (such as, air) via entrance 202.Impeller 210 compression working fluid.The working fluid of compression to flow in spiral case 204 and flows out outlet 206.The example of compressor 200 is used in multiple environment and industry, comprises automobile industry, electronic equipment industry, Aviation Industry, gas industries, power industry, petrochemical industry etc.
Fig. 7 shows the front elevation of compressor set 200, and in order to know, removing illustrates an illustrative embodiments of diffuser assembly to some of them component.Spiral case 204 forms diffuser chamber (such as, the diffuser chamber 140 of Fig. 5) at least partially.Array 126 is arranged in this part of spiral case 204.In an example, array 126 is in the upstream of outlet 206.In compressor 200 operation period, the rotation of impeller 210 is by working fluid suction inlet (such as, the entrance 202 of Fig. 6).Working fluid flows in spiral case 204 via array 126, and flows out outlet 206.As described above, the structure of the array 126 in compressor 200 allows diffuser stator 100 to rotate around leading edge 104, to change the direction of trailing edge 104 relative to flowing and the position of further feature.Diffuser stator 100 is as combination or handle the operation regulating compressor set 200 independently, to optimize various behavior characteristics (such as, exporting the flow parameter of the working fluid at 206 places, energy use etc.).
Now also referring to Fig. 1,2,3,4,5 and 6, in operation, driver element 208 makes impeller 210 rotate, to absorb working fluid via entrance 202.Impeller 210 makes working fluid pressurize.The working fluid of pressurization passes diffuser assembly, and specifically, through the passage adjacent diffuser stator 100.At a high level, diffuser assembly slows down the speed of working fluid.Diffuser assembly is discharged in spiral case 204, and working fluid is such as delivered to and exports 206 downstream tubes connected by turbine 204.
Substantially, compressor set 200 experiences a large amount of testing property and adjustment, with for given optimizing application performance.This regulates the operation of Change Example as driver element 208, and to adjust the speed of impeller 210, this changes the flow parameter (such as, pressure, flow velocity etc.) of the working fluid flowing out outlet 206 effectively.Orientation in response to diffuser stator also changes by the performance of compressor set 200.In an example, regulate the orientation by relating to adjustment diffuser stator, this especially can change the pressure of the working fluid at outlet 206 place.Jointly, the optimization of flow parameter may comprise the increment change of some operating parameters of compressor set 200, to realize common combination, comprise the orientation of diffuser stator, this allow that compressor set 200 operates the flow parameter realizing expecting efficiently.
The example of diffuser stator 100 can be made up of various material and combination, composition and derivative.These materials comprise metal (such as, steel, stainless steel, aluminium), highstrenghtpiston and similar composite.Material selec-tion can be depending on type and the composition of working fluid.Such as, the working fluid with corrosion property can need diffuser stator to comprise the material of relative inertness and/or the material relative to working fluid chemically non-activity.
The geometrical shape of diffuser stator 100 can determine a part for the design of the compressor set 200 for application, structure and cooperation.Geometrical shape can comprise the airfoil shape of stator body 102, and such as, the shape shown in Fig. 1, the example is taked the wing and blade and/or can be generated other form of lift.In one embodiment, diffuser stator 100 such as can use the fastening piece that allows diffuser stator to rotate around leading edge and fastening metal to be installed on a wall member.Screw, bolt, pin, bearing and similar component can be used for the position keeping leading edge, also allow leading edge to change position herein as conceived simultaneously.These fastening pieces can be fixed on the wall member of diffuser assembly, and wall member can comprise the part separated with the component of compressor set, or can with compressor set in find existing hardware entirety combine.
In view of aforementioned discussion, the diffuser stator conceived herein and the embodiment of diffuser assembly improve the performance of compressor and relevant apparatus.Such as, and as described above, the trailing edge of diffuser stator rotates around leading edge, this significantly reduces the flow separation on the surface of working fluid and diffuser stator.This feature improves the performance of the compressor in larger flow range, because leading edge keeps directed with the flow direction of working fluid.
Describe with odd number as used herein and should be understood to not get rid of multiple described element or function, unless enunciated this type of eliminating titled with the element of word " " or " one " or function.In addition, " embodiment " of the present invention that the request mentioned obtains patent protection not should be understood to eliminate the existence of the additional embodiment yet combining the feature described.
This written description employs example and carrys out the open theme comprised herein, comprises optimal mode, and also allows those of ordinary skill in the art to implement the present invention, comprises and makes and use any device or system, and perform the method for any combination.The scope of the claims of the present invention is defined by the claims, and can comprise other example that those skilled in the art expects.If they have the structural element of the written language being not different from claim, if or they comprise and the equivalent structural elements of the written language of claim without essence difference, then these other examples will within the scope of the claims.
Claims (20)
1., for a diffuser assembly for compressor, described diffuser assembly comprises:
Wall member;
The pivot element connected with described wall member; And
The diffuser stator connected with described pivot element, described diffuser stator has the spin axis of leading edge, trailing edge and contiguous described leading edge, and the trailing edge of described diffuser stator rotates around described spin axis.
2. diffuser assembly according to claim 1, is characterized in that, described pivot element is aimed at described spin axis.
3. diffuser assembly according to claim 1, is characterized in that, described diffuser stator has airfoil shape, and it converges to the tip with central axis and crooked outer surface at described leading edge place.
4. diffuser assembly according to claim 3, is characterized in that, described crooked outer surface is limited by the radius from described centre axis, and wherein said spin axis finds in the region limited by described radius.
5. diffuser assembly according to claim 3, is characterized in that, the central axis coaxial of described spin axis and described tip.
6. diffuser assembly according to claim 1, is characterized in that, described spin axis is positioned at 5% of the chord length recorded from described leading edge or less, and wherein said chord length measures the crow flight distance between described leading edge and described trailing edge.
7. diffuser assembly according to claim 1, is characterized in that, described spin axis and pivot boundary alignment, and described in described pivot borders, leading edge is relative to the circumferential position of the impeller of described compressor.
8. diffuser assembly according to claim 7, is characterized in that, when described trailing edge rotates between the first location and the second location, described pivot element prevents described leading edge from described pivot border translation.
9. diffuser assembly according to claim 7, is characterized in that, described diffuser stator is a part for the diffuser stator array of external described impeller.
10., for a diffuser assembly for compressor, described diffuser assembly comprises:
Wall member;
Diffuser stator, it has the leading edge be fixed on described wall member, rotates around described leading edge to allow trailing edge between primary importance and the second place departed from from described primary importance angulation.
11. diffuser assemblies according to claim 10, is characterized in that, described diffuser stator has airfoil shape, and it converges to the tip with central axis and crooked outer surface at described leading edge place.
12. diffuser assemblies according to claim 11, is characterized in that, described crooked outer surface is limited by the radius from described centre axis, and wherein said diffuser stator is centered around the spin axis found in the region that limited by described radius rotates.
13. diffuser assemblies according to claim 11, is characterized in that, the central axis coaxial of described spin axis and described tip.
14. diffuser assemblies according to claim 10, it is characterized in that, described diffuser stator has spin axis, and it is positioned at 5% or less of the chord length measured from described leading edge, and wherein said chord length measures the crow flight distance between described leading edge and described trailing edge.
15. diffuser assemblies according to claim 10, is characterized in that, described leading edge has central axis, described central axis and pivot boundary alignment, and described in described pivot borders, leading edge is relative to the circumferential position of impeller axis.
16. 1 kinds of compressors, comprising:
Comprise wall member and there is the diffuser assembly of diffuser stator array of leading edge and trailing edge, wherein said diffuser stator is fixed on described wall member at described leading edge place, rotates around described leading edge to allow described trailing edge between primary importance and the second place departed from from described primary importance angulation.
17. diffuser assemblies according to claim 16, it is characterized in that, described diffuser assembly also comprises the impeller with impeller axis, the external described impeller of wherein said diffuser stator array, and wherein said leading edge has central axis, described central axis and pivot boundary alignment, described in described pivot borders, leading edge is relative to the circumferential position of described impeller axis.
18. diffuser assemblies according to claim 16, it is characterized in that, described diffuser stator has airfoil shape, it converges to the tip with central axis and crooked outer surface at described leading edge place, wherein said crooked outer surface is limited by the radius from described centre axis, and wherein said diffuser stator is centered around the spin axis found in the region that limited by described radius rotates.
19. diffuser assemblies according to claim 18, is characterized in that, the central axis coaxial of described spin axis and described tip.
20. diffuser assemblies according to claim 18, is characterized in that, described spin axis is positioned at 5% of the chord length recorded from described leading edge or less, and wherein said chord length measures the crow flight distance between described leading edge and described trailing edge.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/601,352 US20140064933A1 (en) | 2012-08-31 | 2012-08-31 | Diffuser assembly comprising diffuser vanes pivoting about the leading edge |
| US13/601352 | 2012-08-31 | ||
| PCT/US2013/056328 WO2014035806A1 (en) | 2012-08-31 | 2013-08-23 | Diffuser assembly comprising diffuser vanes pivoting about the leading edge |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104755768A true CN104755768A (en) | 2015-07-01 |
Family
ID=49118797
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380051296.3A Pending CN104755768A (en) | 2012-08-31 | 2013-08-23 | Diffuser assembly comprising diffuser vanes pivoting about the leading edge |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20140064933A1 (en) |
| EP (1) | EP2890898A1 (en) |
| CN (1) | CN104755768A (en) |
| BR (1) | BR112015004608A2 (en) |
| RU (1) | RU2015107885A (en) |
| WO (1) | WO2014035806A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115199587A (en) * | 2022-09-07 | 2022-10-18 | 中国核动力研究设计院 | Diffuser for compressor and compressor |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111601972B (en) * | 2018-01-19 | 2022-09-23 | 概创机械设计有限责任公司 | Turbine with separate collectors |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1307113A (en) * | 1961-11-29 | 1962-10-19 | L J Gilchrist & Co Engineers L | Improvement in blowers or centrifugal vane wheels |
| US4531356A (en) * | 1981-06-15 | 1985-07-30 | The Garrett Corporation | Intake vortex whistle silencing apparatus and methods |
| US4770605A (en) * | 1981-02-16 | 1988-09-13 | Mitsubishi Jukogyo Kabushiki Kaisha | Diffuser device in a centrifugal compressor and method for manufacturing the same |
| DE102007023915A1 (en) * | 2006-06-09 | 2007-12-13 | Borgwarner Inc., Auburn Hills | Exhaust gas turbo charger, has adjustment ring with adjustment units, where ring is rotatably supported at compressor rear wall using rolling element, and adjustment units are arranged axle centrically to rolling element |
| CN101663466A (en) * | 2007-06-26 | 2010-03-03 | 博格华纳公司 | Variable geometry turbocharger |
-
2012
- 2012-08-31 US US13/601,352 patent/US20140064933A1/en not_active Abandoned
-
2013
- 2013-08-23 EP EP13759369.5A patent/EP2890898A1/en not_active Withdrawn
- 2013-08-23 RU RU2015107885A patent/RU2015107885A/en not_active Application Discontinuation
- 2013-08-23 WO PCT/US2013/056328 patent/WO2014035806A1/en active Application Filing
- 2013-08-23 CN CN201380051296.3A patent/CN104755768A/en active Pending
- 2013-08-23 BR BR112015004608A patent/BR112015004608A2/en not_active IP Right Cessation
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1307113A (en) * | 1961-11-29 | 1962-10-19 | L J Gilchrist & Co Engineers L | Improvement in blowers or centrifugal vane wheels |
| US4770605A (en) * | 1981-02-16 | 1988-09-13 | Mitsubishi Jukogyo Kabushiki Kaisha | Diffuser device in a centrifugal compressor and method for manufacturing the same |
| US4531356A (en) * | 1981-06-15 | 1985-07-30 | The Garrett Corporation | Intake vortex whistle silencing apparatus and methods |
| DE102007023915A1 (en) * | 2006-06-09 | 2007-12-13 | Borgwarner Inc., Auburn Hills | Exhaust gas turbo charger, has adjustment ring with adjustment units, where ring is rotatably supported at compressor rear wall using rolling element, and adjustment units are arranged axle centrically to rolling element |
| CN101663466A (en) * | 2007-06-26 | 2010-03-03 | 博格华纳公司 | Variable geometry turbocharger |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115199587A (en) * | 2022-09-07 | 2022-10-18 | 中国核动力研究设计院 | Diffuser for compressor and compressor |
Also Published As
| Publication number | Publication date |
|---|---|
| US20140064933A1 (en) | 2014-03-06 |
| BR112015004608A2 (en) | 2018-04-17 |
| WO2014035806A1 (en) | 2014-03-06 |
| EP2890898A1 (en) | 2015-07-08 |
| RU2015107885A (en) | 2016-10-20 |
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Application publication date: 20150701 |
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