WO2004007970A1 - インデューサ及びインデューサ付ポンプ - Google Patents
インデューサ及びインデューサ付ポンプ Download PDFInfo
- Publication number
- WO2004007970A1 WO2004007970A1 PCT/JP2003/008605 JP0308605W WO2004007970A1 WO 2004007970 A1 WO2004007970 A1 WO 2004007970A1 JP 0308605 W JP0308605 W JP 0308605W WO 2004007970 A1 WO2004007970 A1 WO 2004007970A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- inducer
- blade
- angle
- leading edge
- wing
- 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
- F04D29/18—Rotors
- F04D29/22—Rotors specially for centrifugal pumps
- F04D29/2261—Rotors specially for centrifugal pumps with special measures
- F04D29/2277—Rotors specially for centrifugal pumps with special measures for increasing NPSH or dealing with liquids near boiling-point
Definitions
- the present invention relates to an inducer and a pump with an inducer, and particularly to a pump such as a turbo pump, in order to improve the suction performance, so that the axis of the main impeller coincides with the axis of the main impeller.
- the axial flow also disposed upstream relates Indeyusa and inducer pump with mixed flow type c
- an inducer may be attached to the tip of the main shaft to improve the suction performance of the pump.
- the inducer located upstream of the centrifugal main impeller is of the mixed flow type or axial flow type, and has a smaller number of blades and a longer blade length than a normal impeller. It is a unique impeller.
- This inducer is arranged on the upstream side of the main impeller so that the rotation axis is the same as that of the main impeller, and is rotated by the main shaft at the same rotation speed as the main impeller.
- Conventional inducer blades are designed in a helical shape (helical shape). In the cross-sectional shape of the blade, the tip, hub and shaft center are located on a straight line. In the conventional design method of the inducer, only the blade angle along the tip is designed, and the blade angle along the hub is determined by the helical conditions.
- the tip angle at the leading edge of a conventional inducer blade is designed to be larger than the inlet flow angle calculated from the axial inflow velocity of the inlet flow and the circumferential velocity of the blade at the design point flow rate.
- Tip Wing Angle and Inlet Flow at Wing Leading Edge The angle of the angle difference is called an incident angle. This angle of incidence is typically designed to be between 35% and 50% of the leading edge wing angle.
- the wing angle from the inlet (leading edge) to the outlet (tailing edge) of the inducer chip should be constant or stepped to meet the required head for the inducer. Designed to increase, increase linearly, increase quadratic.
- the pressure upstream of the blade inlet that is, the pressure of the fluid upstream of the pump impeller
- the pressure of the liquid locally falls below the saturated vapor pressure, and cavitation is reduced. Even if it occurs, the cavitation prevents the flow path after the throat portion from being blocked, and the pressure of the liquid can be increased even when cavitation occurs. Therefore, by arranging the inducer upstream of the main impeller, it is possible to improve the suction performance of the pump as compared with the case where the centrifugal main impeller alone is used, and to increase the speed and size of the pump. Will be possible.
- the tip blade angle at the leading edge of the blade has an angle of incidence with respect to the inlet flow at the design point flow rate, and the distribution of the tip blade angle from the inlet to the outlet Is designed to be constant or increased, so that the load concentrates near the inlet of the inducer and the inlet tends to flow backward.
- the incident angle at the inlet of the inducer increases, and the size of the backflow generated at the inlet also increases. If backflow occurs at the inlet with cavitation, the cavitation interferes with the upstream member, and this member is damaged by the impact pressure of the cavitation.
- thermodynamic effect of hydrogen having the function of improving the suction performance is reduced by the backflow at the inlet, and the suction performance of the pump is reduced.
- the present invention has been made in view of such problems of the prior art, and provides a highly reliable inducer and a pump with an inducer that satisfy the required head and suction performance while suppressing the occurrence of inlet backflow. It is intended to provide.
- a first aspect of the present invention relates to an inducer arranged on the upstream side of the main impeller, wherein a blade angle from a tip to a hub at a blade leading edge is This is a user who is characterized by being formed so as to be almost the same as the inlet flow angle at the design point flow rate.
- the blade angle distribution on the tip from the wing leading edge to the wing trailing edge is higher in the upstream from the vicinity of the throat portion than in the downstream from the vicinity of the throat portion. The decreasing rate of the blade angle increases toward the leading edge of the blade, and the dimensionless flow direction distance from the vicinity of the slot
- the throat portion is an inlet portion of a flow path formed by a suction surface of the blade and an adjacent blade.
- the rate of decrease of the blade angle from the vicinity of the throat to the leading edge of the blade is increased from the vicinity of the throat to the leading edge of the blade, and the dimensionless flow direction distance from the vicinity of the throat is zero.
- the change rate of the blade angle from the vicinity of the throat section to the upstream side is smaller than that of the upstream side, so that the load is distributed all over the chip but the pressure drop on the suction surface is large.
- the part can be brought upstream from the slot. Therefore, most of the cavitation occurs in the first half of the suction surface of the inducer blade.
- the flow path after the throat is not easily blocked, and sufficient suction performance can be secured.
- a sufficient head can be secured.
- the blade angle distribution on the hub from the blade leading edge to the blade trailing edge has an inflection point near the throat portion, and the blade angle distribution is located upstream of the throat portion.
- the characteristic feature is that the rate of change of the blade angle increases along the flow direction downstream of the throat portion.
- the rate of change of the blade angle in the flow direction along the hub at the upstream side of the throat portion is reduced, and at the downstream side of the throat portion along the hub.
- a main impeller mounted on a rotatable main shaft, wherein the inducer is arranged on the upstream side of the main impeller such that the axis is coincident with the axis of the main impeller.
- This is a pump with an inducer.
- FIG. 1 is a sectional view showing a part of a turbo pump provided with an inducer according to an embodiment of the present invention.
- FIG. 2 is a perspective view of the inducer shown in FIG.
- Fig. 3A is an external view showing the tip blade angle of the inducer according to the present invention
- Fig. 3B is an external view showing the hub blade angle
- Fig. 3C is the incident angle, the inlet flow angle, and the tip blade angle.
- FIG. 4A is a meridional section of the inducer according to the present invention
- FIG. 4B is a perspective view of the inducer shown in FIG. 4A.
- Fig. 5A is a meridional section of a conventional inducer
- Fig. 5B is a perspective view of the inducer shown in Fig. 5 ⁇ .
- Fig. 6A is a graph showing the tip blade angle distribution from the leading edge to the trailing edge of the inducer according to the present invention and the conventional inducer
- Fig. 6B is a graph showing the respective hub blade angle distributions. It is.
- FIGS.7A and 7B show the hub and tip at the flow rate of 75% of the design point flow rate at the position 5 mm upstream from the leading edge of the inducer according to the present invention and the conventional inducer.
- the velocity distribution of the fluid between FIG. 7A shows the circumferential velocity distribution of the fluid
- FIG. 7B shows the axial velocity distribution of the fluid.
- FIG. 8A and 8B are graphs showing the static pressure distribution on the blade surface along the tip at the design point flow rate, and FIG. 8A shows the static pressure distribution of the conventional inducer-FIG. 8B shows the present invention. 3 shows a static pressure distribution of such an inducer.
- 9A and 9B are graphs showing the results of measuring the velocity distribution of the fluid at a flow rate of 75% of the design point flow rate for the inducer according to the present invention and the conventional inducer.
- 9A shows the results of measuring the circumferential velocity distribution of the fluid
- FIG. 9B shows the results of measuring the axial velocity distribution of the fluid
- c shows the results of the inducer according to the present invention and the conventional inducer. This is a graph showing the results of measuring the suction performance at a flow rate of 75% of the design point flow rate.
- FIG. 11A and 11B are schematic diagrams showing the state of cavitation occurring upstream from the leading edge when the flow rate is 75% of the design point flow rate and the cavitation coefficient is 0.08.
- FIG. 11A shows a conventional inducer
- FIG. 11B shows an inducer according to the present invention.
- FIG. 1 is a sectional view showing a part of a turbo pump provided with an inducer according to an embodiment of the present invention
- FIG. 2 is a perspective view of the inducer shown in FIG.
- the turbo pump shown in FIG. 1 includes a rotatable main shaft 1, a main impeller 2 attached to the main shaft 1, and an inducer 3 arranged upstream of the main impeller 2.
- the axis of the inducer 3 matches the axis of the main impeller 2, and the Is rotated at the same rotation speed as the main impeller 2 with the rotation of the main shaft 1.
- Inducer 3 has multiple blades
- Fig. 2 shows an inducer with three blades.
- the working fluid of the pump flows into the indicator 3 from the direction indicated by the arrow F in FIG.
- the working fluid that has flowed into the inducer 3 is pressurized while generating cavitation in the inducer 3, and further pressurized by the downstream main impeller 2 to the required head of the pump.
- the working fluid is increased to a pressure at which no cavitation occurs in the main impeller 2 by the inducer 3, so that the suction performance of the pump is improved as compared with the case where the main impeller 2 is used alone. .
- the inducer 3 according to the present invention has the following shape characteristics.
- the blade angle at the blade leading edge 31 from the tip T 1 to the hub H 1 is formed so as to be approximately the same as the inlet flow angle at the design point flow rate.
- the blade angle distribution on tip T1 from wing leading edge (inlet) 31 to wing trailing edge (outlet) 32 is from upstream to near the throat, and downstream from near the throat.
- the rate of decrease in the blade angle toward the leading edge 31 of the blade is greater than that in the vicinity of the throat. Therefore, the rate of change of the wing angle is small.
- the wing angle on the tip T1 (tip wing angle) means the angle indicated by j3bt in FIG. 3A.
- the blade angle distribution on the hub Hi from the leading edge (entrance) 31 of the blade to the trailing edge (exit) 32 of the blade has an inflection point near the throat, and is upstream from the throat.
- the change rate of the blade angle is small along the flow direction on the side, and the rate of increase of the blade angle is large downstream of the throat.
- hub H 1 The upper blade angle (hub blade angle) means the angle indicated by / 3 bh in Fig. 3B.
- the wing portion of the inducer is indicated by a dotted line.
- Fig. 4A is a meridional section of the designed inducer 3 according to the present invention
- Fig. 4B is a perspective view
- Fig. 5B is a meridional section of the designed conventional inducer 103
- Fig. 5B is a perspective view. It is.
- each of the inducers 3 and 103 is a complete axial flow type.
- the leading edge 31 and 131, and the trailing edge 3 2, 1 32 are straight lines perpendicular to the flow direction F.
- the diameters Dt of the tips Tl and T0 were 89 mm, and the diameters Dh of the hubs Hi and H0 were 30 mm.
- the actual blade length along the tip was the same for the conventional inducer 103 and the inducer 3 according to the present invention.
- the conventional inducer 103 is a planar inducer with the same blade angle from the leading edge 13 1 to the trailing blade 13 2 .
- the blade angle at the tip T 0 is Was designed to be 35% of the wing angle of the wing leading edge 13 1.
- the inducer 3 according to the present invention is configured such that the hub H The blade angle of the blade leading edge 31 toward 1 was designed to be almost the same as the inlet flow angle at the design point flow rate.
- the axial velocity VX of the inlet flow at the design point flow rate can be obtained from the meridional shape of the inducer and the essentials by the following equation (1). ⁇
- the circumferential rotational speed V0-t at the tip of the inducer blade is obtained by the following equation (2).
- the inlet flow angle ⁇ 1 ⁇ t at the tip is obtained by the following equation (3).
- the inducer 3 according to the present invention is formed such that the blade angle of the blade leading edge 31 at the tip T1 is substantially the same as the inlet flow angle J3 l-t at this design point flow rate. ing.
- the tip blade angle / 3b0-t is designed so that the incident angle is 35% of the tip blade angle] 3b0-t.
- Figure 3C shows the relationship between the incident angle, the inlet flow angle B l-t, and the tip blade angle Bb0-t, as shown in Fig. 3C.
- the incident angle is calculated from the tip blade angle Bb0-t.
- Fig. 6A is a graph showing the respective tip blade angle distributions from the leading edge to the trailing edge of the inducer according to the present invention and the conventional inducer
- Fig. 6B shows the respective hub blade angle distributions. It is a graph. 6A and 6B, the horizontal axis represents the dimensionless meridional plane position normalized by the distance from the leading edge to the trailing edge of the meridian plane, and the vertical axis in FIG. The vertical axis in FIG. 6B indicates the blade angle of the hub.
- the blade angle changes continuously from the blade leading edge (entrance) to the blade trailing edge (outlet), and the tip and hub blade angles are It has a three-dimensional wing surface shape that changes differently. It is preferable to use the three-dimensional inverse method to design the three-dimensional blade surface shape of the inducer, in which the blade angle at the leading edge of the blade becomes substantially the same as the inlet flow angle at the design point flow rate and satisfies the required requirements.
- This three-dimensional inverse method is a method that Dr. Zangeneh's power of UCL (University College London) in 1991, and that the load distribution on the wing surface is specified and the load distribution is satisfied.
- the inducer according to the present invention was designed by this three-dimensional inverse solution.
- input the load as a whole so that the requirements are the same as those of the conventional inducer, and input the load distribution so that the load at the leading edge of the tip and the hub becomes zero.
- the first half load distribution was input so that the load was concentrated in front of the whole.
- the inducer according to the present invention is designed such that the blade angle from the tip to the hub at the leading edge of the blade is substantially the same as the inlet flow angle at the design point flow rate.
- the incident angle of the flow becomes 0 °. Due to the feature that the blade angle at the leading edge of the blade is almost the same as the inlet flow angle, the angle of incidence of the flow decreases from the design point flow to the partial flow, so that the inlet backflow can be effectively suppressed. Become.
- the blade angle distribution on the tip from the leading edge to the trailing edge of the inducer according to the present invention is, as shown in FIG.6A, from the vicinity of the throat to the upstream, and from the vicinity of the throat.
- the rate of decrease of the blade angle toward the leading edge of the blade is greater than that on the downstream side.From the vicinity of the throat to the dimensionless flow direction distance of about 0.9, the blade angle from the vicinity of the throat to the upstream is greater than the upstream.
- the rate of change has become smaller.
- the rate of decrease in the blade angle is increased from the vicinity of the throat toward the leading edge of the blade from the vicinity of the throat to the downstream from the vicinity of the throat, and the dimensionless dimension is increased from the vicinity of the throat.
- the rate of change of the blade angle from the vicinity of the throat portion to the upstream side is smaller than that of the upstream side, so that the pressure on the suction surface is large while the load is distributed all along the tip.
- the lowered part can be brought upstream from the throat. did As a result, most of the cavitation occurs in the first half of the suction surface of the inducer wing, and the flow path after the throat is not easily blocked, and sufficient suction performance can be secured. In addition, a sufficient lift can be secured by distributing the load along the tip over the entire wing.
- the blade angle distribution on the hub from the leading edge to the trailing edge of the inducer according to the present invention has an inflection point near the throat portion as shown in FIG. From the vicinity to the upstream side, the rate of change of the hub blade angle is smaller along the flow direction from the vicinity of the throat section to the downstream side, and from the vicinity of the throat section to the downstream side, and from the vicinity of the throat section to the upstream side.
- the rate of increase of the hub wing angle is larger than that of. In this way, the rate of change of the blade angle in the flow direction along the hub on the upstream side of the throat portion is reduced, and the increase rate of the blade angle in the flow direction along the hub downstream of the slot portion is large.
- Figures 7A and 7B are graphs showing the velocity distribution of fluid between the hub and tip at a flow rate of 75% of the design point flow rate at a position 5 mm upstream from the leading edge of the inducer blade.
- FIG. 7A shows the circumferential velocity distribution of the fluid
- FIG. 7B shows the axial velocity distribution of the fluid.
- the horizontal axis shows the dimensionless radial position normalized by the distance from the hub to the tip.
- the vertical axis in Fig. 7A shows the circumferential velocity of the flow with the tip circumferential velocity of the inducer blade.
- the vertical axis in Fig. 7B shows the dimensionless axial velocity obtained by normalizing the axial velocity of the flow with the circumferential velocity of the tip of the inducer blade. ing.
- the blade angle at the blade leading edge from the tip to the hub is formed so as to be substantially the same as the inlet flow angle at the design point flow rate. Even at a flow rate of 75% of the design point flow rate, there is no velocity distribution of fluid that shows inlet backflow unlike a conventional inducer (Fig. 7A and Fig. 7A). (See Fig. 7B).
- Fig. 8A shows the static pressure distribution on the blade surface (pressure surface and suction surface) along the tip at the design point flow rate for the conventional inducer
- Fig. 8B shows the inducer according to the present invention. It shows the static pressure distribution on the blade surface (pressure surface and suction surface) along the tip at the design point flow rate.
- the horizontal axis represents the dimensionless meridional plane position normalized by the distance from the front to the trailing edge of the meridian plane
- the vertical axis represents the static pressure coefficient.
- the pressure surface is the downstream blade surface
- the suction surface is the upstream blade surface.
- the static pressure on the suction surface is large at the blade leading edge (inlet). And greatly differs from the static pressure on the pressure surface. Since the conventional inducer has such a pressure distribution, when the pressure at the leading edge of the wing (inlet) decreases, strong cavitation occurs near the leading edge of the wing. It can be predicted that the flow path after the point G is not blocked.
- the inducer according to the present invention as shown in FIG. 8B, the static pressure on the suction surface at the leading edge (entrance) of the blade is small, and is restored to the level of the static pressure at the leading edge of the blade by the throat. ing.
- the inducer according to the present invention has such a pressure distribution, when the pressure at the leading edge (inlet) of the blade decreases, weak cavitation occurs on the blade surface upstream of the throat portion. However, it can be expected that the flow path after the throat portion will be able to exhibit the same suction performance as the conventional inducer without being blocked.
- the load on the blade surface (the difference between the static pressure between the pressure surface and the suction surface) is concentrated near the leading edge (inlet) of the blade, and there is almost no load downstream (Fig. 8). A).
- the load on the blade surface in the inducer according to the present invention is distributed from the leading edge (entrance) to the trailing edge (exit) of the blade (see FIG. 8B). For this reason, despite the fact that the tip blade angle of the inducer according to the present invention is generally smaller than that of the conventional inducer (see FIG. 6A), the same lift as the conventional inducer is used. Can be expected.
- FIG. 9A and 9B are graphs showing the velocity distribution of the fluid when the flow rate is 75% of the design point flow rate, FIG. 9A shows the circumferential velocity distribution of the fluid, and FIG. 9B shows the axis of the fluid.
- the directional velocity distribution is shown. 9A and 9B, the horizontal axis represents the dimensionless radial position normalized by the distance from the hub to the tip, and the vertical axis in FIG.
- FIG. 9A represents the circumferential velocity of the flow in the tip circumference of the inducer blade.
- Dimensionless circumferential velocity normalized by the direction velocity the vertical axis in Fig. 9B represents the axial velocity of the flow in the circumferential direction of the tip of the inducer blade. The dimensionless axial velocity normalized by the velocity is shown.
- Figure 10 shows the measurement results of the suction performance at a flow rate of 75% of the design point flow rate.
- the horizontal axis shows the cavitation coefficient obtained by reducing the pressure level at the leading edge (entrance) of the wing
- the vertical axis shows the lift coefficient obtained by reducing the dimension of the inducer head.
- This graph shows the change in the head of the inducer as the pressure level at the leading edge (inlet) of the wing is reduced.
- the suction performance of the pump is higher as the head coefficient does not decrease to a lower cavitation coefficient.
- the inducer according to the present invention is The head when the cavitation coefficient is high is almost the same as that of the conventional inducer, and the cavitation coefficient at which the head suddenly drops is almost the same as that of the conventional inducer. From these measurement results, it can be seen that the inducer according to the present invention has the same head and suction performance as the conventional inducer (Fig. 11A and Fig. 5% flow rate, cavity Fig. 11A is a diagram showing a state of cavitation upstream of the leading edge of the blade when the coefficient of rotation is 0.8. Fig. 11A is a conventional inducer, and Fig. 11B is an indicator according to the present invention. Are respectively shown.
- the inducer according to the present invention has an effect of suppressing the backflow of the inlet as compared with the conventional inducer, and the flow path after the throat portion is not blocked by the cavity. Suction performance equivalent to that of a conventional inducer can be exhibited.
- the inducer of the present invention As described above, according to the inducer of the present invention, the backflow generated at the inlet is suppressed, and the cavitation develops upstream from the throat portion and the flow passage is not easily blocked, so that high suction performance is maintained. be able to. Also, since the load is distributed over the entire wing surface, a high head can be secured. As a result, in the pump having the configuration in which the inducer of the present invention is arranged upstream of the centrifugal main impeller, problems such as damage to the upstream member, vibration, and a decrease in suction performance, which were caused by the backflow in the conventional technology, were found. , And high reliability as a pump can be obtained. Industrial potential
- the present invention can be used for an axial flow type or mixed flow type inducer arranged on the upstream side of a main impeller in order to improve the suction performance of a pump such as a turbo pump.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/520,760 US7207767B2 (en) | 2002-07-12 | 2003-07-07 | Inducer, and inducer-equipped pump |
JP2004521147A JP4436248B2 (ja) | 2002-07-12 | 2003-07-07 | インデューサ及びインデューサ付ポンプ |
AU2003244214A AU2003244214A1 (en) | 2002-07-12 | 2003-07-07 | Inducer, and inducer-equipped pump |
EP03764135.4A EP1536143B1 (en) | 2002-07-12 | 2003-07-07 | Inducer, and inducer-equipped pump |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2002204734 | 2002-07-12 | ||
JP2002-204734 | 2002-07-12 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2004007970A1 true WO2004007970A1 (ja) | 2004-01-22 |
Family
ID=30112734
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2003/008605 WO2004007970A1 (ja) | 2002-07-12 | 2003-07-07 | インデューサ及びインデューサ付ポンプ |
Country Status (6)
Country | Link |
---|---|
US (1) | US7207767B2 (ja) |
EP (1) | EP1536143B1 (ja) |
JP (1) | JP4436248B2 (ja) |
CN (1) | CN100338366C (ja) |
AU (1) | AU2003244214A1 (ja) |
WO (1) | WO2004007970A1 (ja) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2010265761A (ja) * | 2009-05-12 | 2010-11-25 | Ihi Corp | インデューサ装置 |
JP2011106455A (ja) * | 2009-11-16 | 2011-06-02 | Pratt & Whitney Rocketdyne Inc | ポンプ要素およびポンプ要素設計方法 |
CN103080561A (zh) * | 2010-09-10 | 2013-05-01 | 普拉特及惠特尼火箭达因公司 | 泵送元件设计 |
WO2013108832A1 (ja) * | 2012-01-18 | 2013-07-25 | 株式会社 荏原製作所 | インデューサ |
KR102302048B1 (ko) * | 2021-03-30 | 2021-09-15 | 주식회사 우승산업 | 수중펌프용 임펠러 설치각 조정방법 |
Families Citing this family (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ES2628353T3 (es) | 2007-05-21 | 2017-08-02 | Weir Minerals Australia Ltd | Impulsor de bomba centrífuga con álabes auxiliares en la cubierta frontal, adyacentes a la abertura de entrada del impulsor |
DE112008002609T5 (de) * | 2007-10-03 | 2010-10-28 | Lawrence Pumps Inc., Lawrence | Einlauf-Zerkleinerer |
EP2427632B1 (en) * | 2009-05-06 | 2016-12-21 | Curtiss-Wright Electro-Mechanical Corporation | Gas tolerant subsea pump |
WO2011017372A1 (en) * | 2009-08-03 | 2011-02-10 | Ebara International Corporation | Multi-stage inducer for centrifugal pumps |
US8550771B2 (en) * | 2009-08-03 | 2013-10-08 | Ebara International Corporation | Inducer for centrifugal pump |
US8506236B2 (en) * | 2009-08-03 | 2013-08-13 | Ebara International Corporation | Counter rotation inducer housing |
US9631622B2 (en) | 2009-10-09 | 2017-04-25 | Ebara International Corporation | Inducer for centrifugal pump |
US9163516B2 (en) * | 2011-11-14 | 2015-10-20 | Concepts Eti, Inc. | Fluid movement system and method for determining impeller blade angles for use therewith |
CN102678617B (zh) * | 2012-05-18 | 2015-06-10 | 江苏大学 | 一种基于离心泵的诱导轮设计方法 |
US9574562B2 (en) * | 2013-08-07 | 2017-02-21 | General Electric Company | System and apparatus for pumping a multiphase fluid |
CA3207986A1 (en) * | 2014-06-17 | 2015-12-23 | James W. Schleiffarth | Aqueous stream cleaning system |
JP6489225B2 (ja) | 2015-09-14 | 2019-03-27 | 株式会社Ihi | インデューサ及びポンプ |
CN105257588B (zh) * | 2015-11-05 | 2017-10-20 | 江苏大学 | 一种前后盖板非等厚叶片混流泵 |
US20190345955A1 (en) * | 2018-05-10 | 2019-11-14 | Mp Pumps Inc. | Impeller pump |
JP7140030B2 (ja) * | 2019-03-28 | 2022-09-21 | 株式会社豊田自動織機 | 燃料電池用遠心圧縮機 |
CN112302927A (zh) * | 2019-07-26 | 2021-02-02 | 桂龙阀门(上海)有限公司 | 水泵吸入扩散过滤器 |
KR102519317B1 (ko) * | 2021-05-04 | 2023-04-10 | 한국생산기술연구원 | 익형 형상을 이용한 펌프의 임펠러 설계 방법, 이에 의하여 설계된 임펠러 및 펌프 |
KR102519320B1 (ko) * | 2021-07-16 | 2023-04-10 | 한국생산기술연구원 | 자오면 형상 설계에 의한 설계사양 및 성능을 만족하는 축류펌프의 임펠러 설계 방법, 이에 의하여 설계된 임펠러 및 펌프 |
KR102519323B1 (ko) * | 2021-07-16 | 2023-04-10 | 한국생산기술연구원 | 다양한 비속도에서 수력학적 성능이 향상되도록 날개각 분포 설계가 적용된 축류펌프의 임펠러 설계 방법, 이에 의하여 설계된 임펠러 및 펌프 |
KR102623889B1 (ko) * | 2021-12-17 | 2024-01-11 | 한국생산기술연구원 | 대유량 및 고양정을 만족하도록 자오면 및 날개각 분포의 수력학적 설계를 통한 축류펌프 임펠러의 설계방법, 이에 의하여 설계된 임펠러 및 펌프 |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3299821A (en) * | 1964-08-21 | 1967-01-24 | Sundstrand Corp | Pump inducer |
US3522997A (en) * | 1968-07-01 | 1970-08-04 | Rylewski Eugeniusz | Inducer |
GB1409714A (en) | 1971-10-16 | 1975-10-15 | Rolls Royce | Rotary impeller pumps |
JPS60164698U (ja) * | 1984-04-11 | 1985-11-01 | 株式会社日立製作所 | インデユ−サ |
JPH01178800A (ja) * | 1987-12-29 | 1989-07-14 | Torishima Seisakusho:Kk | ポンプ用平板直線形インデューサ |
EP0874161A1 (de) | 1997-04-25 | 1998-10-28 | KSB Aktiengesellschaft | Kreiselpumpe |
JP2000314390A (ja) * | 1999-05-07 | 2000-11-14 | Matsushita Electric Ind Co Ltd | ポンプ |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3442220A (en) * | 1968-08-06 | 1969-05-06 | Rolls Royce | Rotary pump |
JPS60164698A (ja) | 1984-02-08 | 1985-08-27 | Hitachi Ltd | 送風機 |
CN86204176U (zh) * | 1986-06-16 | 1987-06-10 | 中国石化销售公司山西省石油公司 | 有诱导轮的多级卧式离心泵 |
US6595746B1 (en) * | 1998-04-24 | 2003-07-22 | Ebara Corporation | Mixed flow pump |
US6435829B1 (en) * | 2000-02-03 | 2002-08-20 | The Boeing Company | High suction performance and low cost inducer design blade geometry |
-
2003
- 2003-07-07 JP JP2004521147A patent/JP4436248B2/ja not_active Expired - Lifetime
- 2003-07-07 US US10/520,760 patent/US7207767B2/en not_active Expired - Lifetime
- 2003-07-07 CN CNB038165848A patent/CN100338366C/zh not_active Expired - Lifetime
- 2003-07-07 WO PCT/JP2003/008605 patent/WO2004007970A1/ja active Application Filing
- 2003-07-07 EP EP03764135.4A patent/EP1536143B1/en not_active Expired - Lifetime
- 2003-07-07 AU AU2003244214A patent/AU2003244214A1/en not_active Abandoned
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3299821A (en) * | 1964-08-21 | 1967-01-24 | Sundstrand Corp | Pump inducer |
US3522997A (en) * | 1968-07-01 | 1970-08-04 | Rylewski Eugeniusz | Inducer |
GB1409714A (en) | 1971-10-16 | 1975-10-15 | Rolls Royce | Rotary impeller pumps |
JPS60164698U (ja) * | 1984-04-11 | 1985-11-01 | 株式会社日立製作所 | インデユ−サ |
JPH01178800A (ja) * | 1987-12-29 | 1989-07-14 | Torishima Seisakusho:Kk | ポンプ用平板直線形インデューサ |
EP0874161A1 (de) | 1997-04-25 | 1998-10-28 | KSB Aktiengesellschaft | Kreiselpumpe |
JP2000314390A (ja) * | 1999-05-07 | 2000-11-14 | Matsushita Electric Ind Co Ltd | ポンプ |
Non-Patent Citations (1)
Title |
---|
See also references of EP1536143A4 * |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2010265761A (ja) * | 2009-05-12 | 2010-11-25 | Ihi Corp | インデューサ装置 |
JP2011106455A (ja) * | 2009-11-16 | 2011-06-02 | Pratt & Whitney Rocketdyne Inc | ポンプ要素およびポンプ要素設計方法 |
JP2014058980A (ja) * | 2009-11-16 | 2014-04-03 | Pratt & Whitney Rocketdyne Inc | ポンプ要素 |
CN103080561A (zh) * | 2010-09-10 | 2013-05-01 | 普拉特及惠特尼火箭达因公司 | 泵送元件设计 |
JP2013537274A (ja) * | 2010-09-10 | 2013-09-30 | プラット アンド ホイットニー ロケットダイン,インコーポレイテッド | ポンプ部材設計 |
WO2013108832A1 (ja) * | 2012-01-18 | 2013-07-25 | 株式会社 荏原製作所 | インデューサ |
KR20140123949A (ko) * | 2012-01-18 | 2014-10-23 | 가부시키가이샤 에바라 세이사꾸쇼 | 인듀서 |
JPWO2013108832A1 (ja) * | 2012-01-18 | 2015-05-11 | 株式会社荏原製作所 | インデューサ |
US9964116B2 (en) | 2012-01-18 | 2018-05-08 | Ebara Corporation | Inducer |
KR101968372B1 (ko) | 2012-01-18 | 2019-08-13 | 가부시키가이샤 에바라 세이사꾸쇼 | 인듀서 |
KR102302048B1 (ko) * | 2021-03-30 | 2021-09-15 | 주식회사 우승산업 | 수중펌프용 임펠러 설치각 조정방법 |
Also Published As
Publication number | Publication date |
---|---|
EP1536143A4 (en) | 2010-12-01 |
JP4436248B2 (ja) | 2010-03-24 |
EP1536143A1 (en) | 2005-06-01 |
EP1536143B1 (en) | 2015-06-24 |
AU2003244214A1 (en) | 2004-02-02 |
JPWO2004007970A1 (ja) | 2005-11-10 |
US20060110245A1 (en) | 2006-05-25 |
CN1682034A (zh) | 2005-10-12 |
CN100338366C (zh) | 2007-09-19 |
US7207767B2 (en) | 2007-04-24 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
WO2004007970A1 (ja) | インデューサ及びインデューサ付ポンプ | |
JP3693121B2 (ja) | 遠心または斜流ターボ機械 | |
US20060222490A1 (en) | Axial turbine | |
Goto | Study of internal flows in a mixed-flow pump impeller at various tip clearances using three-dimensional viscous flow computations | |
Guleren et al. | Numerical simulation of the stalled flow within a vaned centrifugal pump | |
CN109790853B (zh) | 离心压缩机以及涡轮增压器 | |
JP6740271B2 (ja) | 羽根車及びこの羽根車を備えた遠心圧縮機 | |
EP2535597B1 (en) | Centrifugal compressor using an asymmetric self-recirculating casing treatment | |
KR19990028419A (ko) | 터보기계 및 이의 제작 방법 | |
US20140314557A1 (en) | Centrifugal fluid machine | |
KR100700375B1 (ko) | 선박용 물분사 추진장치를 위한 임펠러 | |
Goto et al. | Suppression of secondary flows in a mixed-flow pump impeller by application of three-dimensional inverse design method: Part 2—Experimental Validation | |
Cheah et al. | Unsteady analysis of impeller-volute interaction in centrifugal pump | |
WO2017145686A1 (ja) | 遠心圧縮機インペラ | |
Cooper et al. | Computational fluid dynamical analysis of complex internal flows in centrifugal pumps | |
JP6785623B2 (ja) | 流体機械 | |
WO1999036701A1 (fr) | Turbomachines centrifuges | |
Imamura et al. | Suppression of cavitating flow in inducer by J-Groove | |
JP2021063456A (ja) | ターボ機械の羽根、羽根の設計方法、及び羽根車の製造方法 | |
JP6758924B2 (ja) | 羽根車 | |
JP6758923B2 (ja) | 羽根車 | |
JP4183612B2 (ja) | 軸流ポンプ | |
JP3353668B2 (ja) | 水力機械の壊食予測法 | |
JP2008133766A (ja) | タービンインペラ | |
JP2000104501A (ja) | タービン動翼及びガスタービン及び蒸気タービン |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
AK | Designated states |
Kind code of ref document: A1 Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW |
|
AL | Designated countries for regional patents |
Kind code of ref document: A1 Designated state(s): GH GM KE LS MW MZ SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LU MC NL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG |
|
DFPE | Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101) | ||
121 | Ep: the epo has been informed by wipo that ep was designated in this application | ||
WWE | Wipo information: entry into national phase |
Ref document number: 2004521147 Country of ref document: JP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2003764135 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 20038165848 Country of ref document: CN |
|
WWP | Wipo information: published in national office |
Ref document number: 2003764135 Country of ref document: EP |
|
ENP | Entry into the national phase |
Ref document number: 2006110245 Country of ref document: US Kind code of ref document: A1 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 10520760 Country of ref document: US |
|
WWP | Wipo information: published in national office |
Ref document number: 10520760 Country of ref document: US |