WO2012019650A1 - Radial diffuser vane for centrifugal compressors - Google Patents
Radial diffuser vane for centrifugal compressors Download PDFInfo
- Publication number
- WO2012019650A1 WO2012019650A1 PCT/EP2010/061788 EP2010061788W WO2012019650A1 WO 2012019650 A1 WO2012019650 A1 WO 2012019650A1 EP 2010061788 W EP2010061788 W EP 2010061788W WO 2012019650 A1 WO2012019650 A1 WO 2012019650A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- diffuser
- function
- diffuser vanes
- vanes
- camber line
- Prior art date
Links
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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/281—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for fans or blowers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
-
- 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
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
-
- 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
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
- F04D29/542—Bladed diffusers
-
- 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
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
Definitions
- the present invention relates generally to compressors and, more specifically, to diffuser vanes for centrifugal compressors.
- a compressor is a machine which accelerates gas particles to, ultimately, increase the pressure of a compressible fluid, e.g., a gas, through the use of mechanical energy.
- Compressors are used in a number of different applications, including operating as an initial stage of a gas turbine engine.
- centrifugal compressors in which mechanical energy operates on gas input to the compressor by way of centrifugal acceleration, e.g., by rotating a centrifugal impeller (sometimes also called a "rotor") by which the compressible fluid is passing.
- centrifugal compressors can be said to be part of a class of machinery known as “turbo machines” or “turbo rotating machines”.
- Centrifugal compressors can be fitted with a single impeller, i.e., a single stage configuration, or with a plurality of impellers in series, in which case they are frequently referred to as multistage compressors.
- Each of the stages of a centrifugal compressor typically includes an inlet conduit (inducer section) for gas to be compressed, an impeller which is capable of imparting kinetic energy to the input gas and a diffuser which converts the kinetic energy of the gas leaving the rotor/impeller into pressure energy.
- a centrifugal compressor stage 100 includes an impeller 102 attached to a rotor 104 followed by a diffuser 106 and a return channel or exit scroll 108.
- the diffuser 106 collects the high velocity fluid from the impeller 102's exit and allows the fluid to slow down, thereby converting the dynamic pressure to a static pressure.
- Figure 1(b) shows a cross-sectional view of the compressor stage 100 taken along the other axis, i.e., perpendicular to the direction of the process gas flow.
- the rotor 104 is seen in the center of the Figure surrounded by an impeller 102 having a number of impeller blades 114.
- the impeller blades 114 can be connected, on one end, to a hub portion 116 of the impeller 112, and on the other end to a shroud portion 1 18 of the impeller 102.
- Vaned diffusers 106 i.e., those diffusers having a circumferential array of airfoils (diffuser blades 110) along the flow passage as best seen in Figure 1(b)
- Vaned diffusers 106 are employed to achieve higher stage efficiency by directing the highly tangential fluid flow at the impeller exit to be more radial towards the diffuser exit.
- some centrifugal compressors have vaneless diffuser sections 120, as shown in Figure 1(c). Making the fluid flow more radial inside the diffuser 106 by using vanes reduces the distance taken by the fluid to travel through the diffuser 106. This concept is illustrated by the flow arrows in the centrifugal pump illustrated in Figure 1(d).
- the operating range of a centrifugal compressor 100 including a vaned diffuser 106 is determined based, at least in part, on the shape of the diffuser blades 1 10 which are employed.
- the shape of a diffuser blade (or more generally any airfoil) can be expressed by its camber line, (i.e., a line drawn halfway between the upper surface of the diffuser blade and the lower surface of the diffuser blade), and the thickness distribution along the camber line. Two previously used diffuser blade shapes are shown in Figures 2(a) and 2(b).
- a diffuser blade 200 having a straight camber line 202, i.e., a camber line with no change in slope, drawn as a dotted line between the upper diffuser blade surface 204 and the lower diffuser blade surface 206 is illustrated.
- Figure 2(b) shows an alternative diffuser blade 208 having a different shape which is referred to as a conformal mapped blade camber.
- the conformal mapped blade camber line can be defined, e.g., using coordinates of the camber line of an airfoil in the rectangular plane (x, y), and polar coordinates (r, ⁇ ) in the circular plane, as:
- r 0 is the radius of the diffuser vane leading edge radial position
- a 3 is the angle of absolute velocity at diffuser vane leading edge.
- This diffuser blade shape also results in certain drawbacks when employed as part of a diffuser in a centrifugal compressor.
- employing diffuser blades 208 having a conformal mapped camber line in a centrifugal compressor is problematic because the trailing edge of the diffuser vane with that shape is relatively highly loaded and the compressor has a relatively low choke limit.
- Various devices, systems and methods according to exemplary embodiments of the present invention provide diffusers, e.g., as part of a turbo machine, with diffuser vanes having S-shaped camber lines.
- S-shaped camber lines are defined by functions having an inflection point along their length, or a portion of such curves.
- Using diffuser vanes having such shapes results in, among other things, an operational characteristic wherein a portion of the diffuser vanes disposed near a leading edge is substantially unloaded when operating at design conditions and wherein the load gradually increases to a maximum loading value towards a middle portion of the diffuser vanes.
- a turbo machine includes a rotor assembly having at least one impeller, a bearing connected to, and for rotatably supporting, the rotor assembly, and a stator including at least one diffuser connected to an exit portion of the impeller, wherein the at least one diffuser includes a plurality of diffuser vanes, at least one of the plurality of diffuser vanes having a camber line defined by a function having an inflection point.
- a method of manufacturing a turbo machine includes providing a rotor assembly including at least one impeller, connecting the rotor assembly to a bearing assembly to rotatably support the rotor assembly, and providing a stator assembly including at least one diffuser connected to an exit portion of the impeller, wherein the at least one diffuser includes a plurality of diffuser vanes, at least one of the plurality of diffuser vanes having a camber line defined by a function having an inflection point.
- a diffuser includes an inner annular wall, an outer annular wall, a plate portion disposed between the inner annular wall and the outer annular wall, and a plurality of diffuser vanes disposed on the plate portion, at least one of the plurality of diffuser vanes having a camber line defined by a function having an inflection point.
- Figures 1(a)- 1(d) illustrate background art associated with diffusers used in centrifugal compressors
- Figures 2(a) and 2(b) show conventional straight camber line and conformal mapped camber line diffuser blades, respectively;
- Figure 3 depicts an exemplary centrifugal compressor in which diffusers manufactured according to exemplary embodiments can be employed
- FIG. 4 illustrates airfoil concepts
- Figure 5 describes beta angles associated with diffuser implementations according to exemplary embodiments
- Figure 6 depicts a diffuser blade profile having an S-shaped camber line according to an exemplary embodiment
- Figure 7 is a graph depicting an S-shaped camber line according to an exemplary embodiment relative to other camber lines
- Figure 8 is a graph depicting an S-shaped camber line and its inflection point according to an exemplary embodiment
- Figures 9-1 1 are plots depicting simulation results according to exemplary embodiments
- Figure 12 is a flowchart illustrating a method of manufacturing a turbo machine according to an exemplary embodiment
- Figure 13 shows a diffuser according to an exemplary embodiment
- Figure 14 illustrates usage of Bezier curves to define an S-shaped camber line according to an exemplary embodiment.
- the multistage centrifugal compressor 300 operates to take an input process gas from duct inlet 312, to accelerate the process gas particles through operation of the rotor assembly 308, and to subsequently deliver the process gas through various interstage ducts 314 (which include diffusers and diffuser blades described below) at an output pressure which is higher than its input pressure.
- the process gas may, for example, be any one of atmospheric air, carbon dioxide, hydrogen sulfide, butane, methane, ethane, propane, natural gas, or a combination thereof.
- sealing systems (not shown) are provided to prevent the process gas from flowing to the bearings 310.
- the housing 302 is configured so as to cover both the bearings 310 and the sealing systems, so as to prevent the escape of gas from the centrifugal compressor 300.
- the centrifugal compressor 300 illustrated in Figure 3 is purely exemplary and that the diffusers and diffuser blades described below can be used in other compressors, e.g., in-line, back-to-back, axial compressors, centrifugal pumps, turbines, turbo expanders, etc.
- a generic airfoil 400 has a leading edge (LE) 402 and a trailing edge (TE) 404, the leading edge 402 being the end of the airfoil which first contacts the fluid and which thereby separates the fluid into upper and lower streams, and the trailing edge 404 being the other end of the airfoil where the fluid streams converge.
- LE leading edge
- TE trailing edge
- the chord line 406 is a straight line between the LE 402 and TE 404, while the mean camber line 408 (also sometimes called simply “the camber line”) is disposed midway between an upper surface 410 of the airfoil 400 and a lower surface 412 of the airfoil 400.
- An airfoil 400 can have a point of maximum thickness 414 which may be located at a predetermined distance from the leading edge 402. Varying these (and other) parameters associated with the airfoil 400 will result in varying aerodynamic performance.
- FIG. 5 illustrates some additional terminology which is relevant for the usage of airfoils as diffuser blades 500 in a diffuser section 502 of a centrifugal compressor 300.
- Camber lines can, for example, be plotted as a function of beta angles (or change in beta angles) across the length of a diffuser blade 500.
- the orientation of the diffuser blades 500, as well as their shape, defines inlet and outlet beta angles relative to the leading and trailing edges, respectively, of the diffuser blades 500.
- the inlet and outlet beta angles are defined relative to (1) radii 504, 506 associated with circles or arcs, and representing the position of the leading edge and the trailing edge, drawn through (from the axis of rotation of shaft 104) and (2) the projections (tangent to the blade camber line) 508, 510 associated with the instantaneous curvature at the point of interest.
- the beta angles of the metallic diffuser vanes 500 can also be computed for any point between the leading and trailing edges and are used to plot the camber lines as a function of the distribution of beta angles as described below.
- camber lines 602 associated with diffuser blades 600 can be defined by functions of the form:
- FIG. 8 Another S-shaped camber line 800 associated with a diffuser blade according to an exemplary embodiment is illustrated in Figure 8. Therein, the change in beta angle is plotted across the length of the diffuser blade revealing again the s-shape characteristic of the camber line.
- a characteristic of third order equations is that they possess an inflection point 802, i.e., a point in the function or graph wherein the curvature (second derivative) changes signs.
- this provides for diffuser shapes having camber lines according to some exemplary embodiments with ⁇ values which are greater than those associated with a straight camber line shape (and also, therefore, a conformal mapped camber line as seen in Figure 8).
- the phrase "diffuser vanes having a camber line defined by a function having an inflection point” includes diffuser vanes having shapes defined by a cutoff version of such functions, e.g., including those where the inflection point defined by the function has been cutoff.
- Figure 9 illustrates results associated with two simulations carried out for (1) a vaned diffuser with a straight camber line, plotted as lines 910, 912 and (2) a vaned diffuser with an S-shaped profile (based on a Sigmoid function as described below) according to these exemplary embodiments, shown by lines 900 and 902.
- the turbulence model used in the simulation was the Wilcox k-w turbulence model, with a computational domain consisting of one impeller blade passage (inducer, one full-length blade and one splitter blade in case of splitter impeller), and one diffuser blade passage.
- the diffuser vanes in this simulation were designed as low solidity vanes.
- the interface between the rotating domain and the non-rotating domain in this simulation was specified as 50% of the distance between the impeller trailing edge and the diffuser vane leading edge.
- Computations associated with this simulation were carried out with total pressure and total temperature specified at inlet and mass flow rate specified at outlet. All external walls were assumed adiabatic and leakage flow through the impeller seals is assumed negligible and was not modeled.
- the impeller upstream was simulated as having a design flow coefficient of 0.0206 and peripheral Mach number of 0.3.
- FIG. 10 illustrates the higher overall efficiency of the exemplary embodiments. More specifically, this comparison shows that, for example, this exemplary embodiment had an efficiency improvement of about 1.5 points on the left hand side of the operating range relative to the centrifugal compressor employing the straight camber line diffusers, albeit a slightly lower efficiency than the conformal mapped camber line compressor. Additionally, on the right hand side of the graph in Figure 10, it can be seen that the S-shaped camber according to exemplary embodiments performed much better in terms of efficiency than the conformal mapped camber, and only slightly below the straight camber.
- some of the efficiency benefits and advantages associated with using diffuser vanes or blades having S-shaped camber lines in centrifugal compressors include: higher efficiency toward the left (lower) operating range, thereby increasing the stall limit of the compressor, better or comparable efficiency at the design point relative to other designs and lower efficiency towards the choke limit relative to some designs (i.e., except conformal mapped camber line designs).
- This simulation also showed a higher polytropic head raise for the S-shaped camber line diffuser according to an exemplary embodiment relative to the straight camber line diffuser and vaneless diffuser as shown in Figure 11.
- a head raise of 6.5% was measured for the S-shaped camber line diffuser function 1102 according to an exemplary embodiment relative to a 5.2% head raise for the straight camber line diffuser function 1104 and 6.2% head raise for the vaneless diffuser.
- the conformal mapped diffuser function 1 100 shows a just slightly better head raise than that of the exemplary embodiment 1102.
- Exemplary embodiments also include a method of manufacturing a turbo machine which can be expressed a shown in the flowchart of Figure 12.
- a rotor assembly including at least one impeller.
- the rotor assembly is connected, at step 1202, to a bearing assembly which rotatably supports the rotor assembly.
- a stator assembly is provided at step 1204 including at least one diffuser connected to an exit portion of the impeller, wherein the at least one diffuser includes a plurality of diffuser vanes, at least one of the plurality of diffuser vanes having a camber line defined by a function having an inflection point.
- centrifugal compressors with diffuser vanes having S- shaped camber lines it may further be desirable to retrofit existing centrifugal compressors having vaneless diffusers or diffusers with differently shaped diffuser vanes, with diffusers having S- shaped camber lines according to the exemplary embodiments to, for example, increase efficiency relative to vaneless diffusers or reduce the loss of range associated with existing vaned diffusers.
- exemplary embodiments further contemplate the manufacture of diffusers themselves for retrofitting and/or repair of existing compressors.
- Figure 13 illustrates an exemplary diffuser 1300 including an inner annular wall 1302, an outer annular wall 1304, a plate portion 1306 disposed between the inner annular wall 1302 and the outer annular wall 1304, and a plurality of diffuser vanes 1308 disposed on the plate portion 1306.
- One or more of the diffuser vanes or blades 1308 have an S-shaped camber line, i.e., defined by a function having an inflection point.
- the diffuser 1300 can be a high solidity airfoil diffuser or a low solidity airfoil diffuser.
- the S-shaped diffuser vanes discussed herein can be employed with diffusers 1300 which have more than 10 vanes 1308.
- higher order polynomial functions e.g., fourth order or higher
- higher order polynomial functions can also be used to obtain the same s-shape.
- more complicated shapes can be custom designed for a particular application.
- One way to define such generalized curves is through Bezier Curves.
- a Bezier curve forming the s-shape of camber lines according to exemplary embodiments can be described as shown in Figure 14. Therein, the shape of the camber line is defined by the values of co-ordinates of the control points 1401 and 1402 having coordinates (XI, Yl) and (X2, Y2), respectively.
- a greater number of control points can be used to define higher order curves having multiple inflection points.
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Abstract
Description
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Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP10744692.4A EP2603703A1 (en) | 2010-08-12 | 2010-08-12 | Radial diffuser vane for centrifugal compressors |
US13/880,817 US20130224004A1 (en) | 2010-08-12 | 2010-08-12 | Radial Diffuser Vane for Centrifugal Compressors |
KR1020137006210A KR20140005145A (en) | 2010-08-12 | 2010-08-12 | Radial diffuser vane for centrifugal compressors |
CA2811348A CA2811348A1 (en) | 2010-08-12 | 2010-08-12 | Radial diffuser vane for centrifugal compressors |
CN2010800695922A CN103154526A (en) | 2010-08-12 | 2010-08-12 | Radial diffuser vane for centrifugal compressors |
PCT/EP2010/061788 WO2012019650A1 (en) | 2010-08-12 | 2010-08-12 | Radial diffuser vane for centrifugal compressors |
AU2010358891A AU2010358891A1 (en) | 2010-08-12 | 2010-08-12 | Radial diffuser vane for centrifugal compressors |
RU2013110571/06A RU2581686C2 (en) | 2010-08-12 | 2010-08-12 | Radial diffuser blade for centrifugal compressors |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/EP2010/061788 WO2012019650A1 (en) | 2010-08-12 | 2010-08-12 | Radial diffuser vane for centrifugal compressors |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2012019650A1 true WO2012019650A1 (en) | 2012-02-16 |
Family
ID=43876985
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2010/061788 WO2012019650A1 (en) | 2010-08-12 | 2010-08-12 | Radial diffuser vane for centrifugal compressors |
Country Status (8)
Country | Link |
---|---|
US (1) | US20130224004A1 (en) |
EP (1) | EP2603703A1 (en) |
KR (1) | KR20140005145A (en) |
CN (1) | CN103154526A (en) |
AU (1) | AU2010358891A1 (en) |
CA (1) | CA2811348A1 (en) |
RU (1) | RU2581686C2 (en) |
WO (1) | WO2012019650A1 (en) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102996504A (en) * | 2012-12-14 | 2013-03-27 | 清华大学 | Centrifugal impeller flow passage design method for controlling slope distribution |
WO2014154997A1 (en) | 2013-03-28 | 2014-10-02 | Turbomeca | Radial or mixed-flow compressor diffuser having vanes |
WO2016184548A1 (en) * | 2015-05-20 | 2016-11-24 | Daimler Ag | Guide vane for a diffuser of a radial compressor |
US9574562B2 (en) | 2013-08-07 | 2017-02-21 | General Electric Company | System and apparatus for pumping a multiphase fluid |
US10527059B2 (en) | 2013-10-21 | 2020-01-07 | Williams International Co., L.L.C. | Turbomachine diffuser |
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CN103541774B (en) * | 2013-11-14 | 2015-06-17 | 上海汽轮机厂有限公司 | Method for designing turbine blades |
US10024335B2 (en) | 2014-06-26 | 2018-07-17 | General Electric Company | Apparatus for transferring energy between a rotating element and fluid |
EP3088663A1 (en) * | 2015-04-28 | 2016-11-02 | Siemens Aktiengesellschaft | Method for profiling a blade |
DE102015107907A1 (en) * | 2015-05-20 | 2016-11-24 | Ebm-Papst Mulfingen Gmbh & Co. Kg | Eben Strömungsleitgitter |
CN104912850B (en) * | 2015-05-21 | 2017-03-01 | 合肥通用机械研究院 | Radial guide vane structure with streamline structure |
CN105201916B (en) * | 2015-09-17 | 2017-08-01 | 浙江工业大学之江学院 | A kind of spatial guide blade centrifugal pump Hydraulic Design Method |
US11143195B2 (en) * | 2017-11-06 | 2021-10-12 | Isaacs Hydropermutation Technologies, Inc. | Machine and process for filterless wet removal of particles from and humidification of air |
KR102083168B1 (en) * | 2017-11-07 | 2020-03-02 | 주식회사 에어로네트 | Impeller having primary blades and secondary blades |
RU185913U1 (en) * | 2018-09-24 | 2018-12-24 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения им. П.И. Баранова" | Centrifugal compressor blade diffuser |
US11286952B2 (en) | 2020-07-14 | 2022-03-29 | Rolls-Royce Corporation | Diffusion system configured for use with centrifugal compressor |
US11536286B2 (en) | 2020-07-30 | 2022-12-27 | Microsoft Technology Licensing, Llc | Systems and methods for improving airflow in a centrifugal blower |
CN113653649B (en) * | 2021-09-09 | 2022-12-02 | 江苏大学 | Interstage flow channel structure for improving performance of secondary impeller of multi-stage pump |
US20240060507A1 (en) * | 2022-08-22 | 2024-02-22 | FoxRES LLC | Sculpted Low Solidity Vaned Diffuser |
US11873730B1 (en) * | 2022-11-28 | 2024-01-16 | Rtx Corporation | Gas turbine engine airfoil with extended laminar flow |
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BRPI0909929B1 (en) * | 2008-06-20 | 2019-02-19 | Philadelphia Mixing Solutions, Ltd. | IMPELLER, SYSTEM FOR SHAKING A FLUID AND METHOD FOR SHAKING A FLUID IN A TANK |
US8511981B2 (en) * | 2010-07-19 | 2013-08-20 | Cameron International Corporation | Diffuser having detachable vanes with positive lock |
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2010
- 2010-08-12 EP EP10744692.4A patent/EP2603703A1/en not_active Withdrawn
- 2010-08-12 RU RU2013110571/06A patent/RU2581686C2/en active
- 2010-08-12 KR KR1020137006210A patent/KR20140005145A/en not_active Application Discontinuation
- 2010-08-12 WO PCT/EP2010/061788 patent/WO2012019650A1/en active Application Filing
- 2010-08-12 AU AU2010358891A patent/AU2010358891A1/en not_active Abandoned
- 2010-08-12 CN CN2010800695922A patent/CN103154526A/en active Pending
- 2010-08-12 CA CA2811348A patent/CA2811348A1/en not_active Abandoned
- 2010-08-12 US US13/880,817 patent/US20130224004A1/en not_active Abandoned
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CN102996504A (en) * | 2012-12-14 | 2013-03-27 | 清华大学 | Centrifugal impeller flow passage design method for controlling slope distribution |
CN105247223B (en) * | 2013-03-28 | 2017-05-17 | 涡轮梅坎公司 | Radial or mixed-flow compressor diffuser having vanes |
FR3003908A1 (en) * | 2013-03-28 | 2014-10-03 | Turbomeca | DIFFUSER WITH FINES OF A RADIAL OR MIXED COMPRESSOR |
CN105247223A (en) * | 2013-03-28 | 2016-01-13 | 涡轮梅坎公司 | Radial or mixed-flow compressor diffuser having vanes |
WO2014154997A1 (en) | 2013-03-28 | 2014-10-02 | Turbomeca | Radial or mixed-flow compressor diffuser having vanes |
US9890792B2 (en) | 2013-03-28 | 2018-02-13 | Turbomeca | Radial or mixed-flow compressor diffuser having vanes |
RU2651905C2 (en) * | 2013-03-28 | 2018-04-24 | Тюрбомека | Radial or mixed-flow compressor diffuser having vanes |
US9574562B2 (en) | 2013-08-07 | 2017-02-21 | General Electric Company | System and apparatus for pumping a multiphase fluid |
US10527059B2 (en) | 2013-10-21 | 2020-01-07 | Williams International Co., L.L.C. | Turbomachine diffuser |
WO2016184548A1 (en) * | 2015-05-20 | 2016-11-24 | Daimler Ag | Guide vane for a diffuser of a radial compressor |
CN107624150A (en) * | 2015-05-20 | 2018-01-23 | 戴姆勒股份公司 | Guide vane for the diffuser of radial flow compressor |
JP2018514699A (en) * | 2015-05-20 | 2018-06-07 | ダイムラー・アクチェンゲゼルシャフトDaimler AG | Guide vanes for diffuser of radial compressor |
US10619647B2 (en) | 2015-05-20 | 2020-04-14 | Daimler Ag | Guide vane for a diffuser of a radial compressor |
CN107624150B (en) * | 2015-05-20 | 2022-06-17 | 戴姆勒卡车股份公司 | Guide vane, radial compressor, exhaust gas turbocharger |
Also Published As
Publication number | Publication date |
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US20130224004A1 (en) | 2013-08-29 |
RU2013110571A (en) | 2014-09-20 |
CN103154526A (en) | 2013-06-12 |
CA2811348A1 (en) | 2012-02-16 |
KR20140005145A (en) | 2014-01-14 |
EP2603703A1 (en) | 2013-06-19 |
RU2581686C2 (en) | 2016-04-20 |
AU2010358891A1 (en) | 2013-03-21 |
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