WO2005054681A1 - 圧縮機のインペラ - Google Patents
圧縮機のインペラ Download PDFInfo
- Publication number
- WO2005054681A1 WO2005054681A1 PCT/JP2004/017916 JP2004017916W WO2005054681A1 WO 2005054681 A1 WO2005054681 A1 WO 2005054681A1 JP 2004017916 W JP2004017916 W JP 2004017916W WO 2005054681 A1 WO2005054681 A1 WO 2005054681A1
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- WO
- WIPO (PCT)
- Prior art keywords
- impeller
- compressor
- boundary layer
- hub
- flow
- Prior art date
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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
- F04D29/26—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
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D23/00—Other rotary non-positive-displacement pumps
-
- 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
- F04D29/002—Details, component parts, or accessories especially adapted for elastic fluid pumps
-
- 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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
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- 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
- F05D2210/00—Working fluids
- F05D2210/10—Kind or type
- F05D2210/12—Kind or type gaseous, i.e. compressible
-
- 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
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S416/00—Fluid reaction surfaces, i.e. impellers
-
- 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
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S417/00—Pumps
Definitions
- the present invention relates to a centrifugal compressor ⁇ impeller for a mixed flow compressor, for example, a centrifugal compressor used for an aircraft gas turbine, a marine supercharger, a supercharger for an automobile, etc. It is.
- Patent Document 1 JP-A-55-35173
- This centrifugal force F1 can be divided into a direction perpendicular to the hub surface 12c and a direction perpendicular to the perpendicular direction.
- the force F2 acting in a direction perpendicular to the hub surface 12c Acting in the direction of peeling from the surface 12c, which causes the boundary layer of the flow to expand (or, in severe cases, to flow back near the hub surface, or to separate from the hub surface 12c),
- the loss inside the impeller increases, causing the efficiency of the centrifugal compressor 100 to decrease.
- the direction of the centrifugal force F1 and the direction of the tangent line to the hub surface 12c Since the force F2 acting in the direction perpendicular to the hub surface is 0 (zero), there is no force acting in the direction of removing the flow from the hub surface 12c.
- reference numerals 12, 12a, 12b, LE, TE, and B represent a hub and a hub, respectively.
- 3 shows a small diameter portion, a large diameter portion of the hub, a leading edge of the blade 11, a trailing edge of the blade 11, and a region where the boundary layer is particularly greatly expanded (that is, a region where the thickness of the boundary layer is significantly increased).
- the present invention has been made in view of the above circumstances, and prevents the local concentration of the boundary layer generated on the surface of the hub and reduces the thickness of the boundary layer, thereby improving the efficiency of the compressor.
- the purpose is to aim.
- the present invention employs the following means in order to solve the above problems.
- An impeller of a compressor according to the present invention has a plurality of blades and a hub disposed at a root portion of the plurality of blades, and at least a part of a surface of the hub through which fluid flows is at least part of a rotation axis.
- the boundary layer reduction portion provided on the hub surface prevents local concentration of the boundary layer formed on the hub surface, and also reduces the boundary layer reduction portion.
- the thickness of the boundary layer is smaller than that of the impeller.
- the boundary layer reducing portion may be provided at a location where a centrifugal force acting on the flow of the fluid acts in a direction in which the flow of the fluid is removed from the surface force of the hub. preferable.
- a relatively large centrifugal force acts, and the surface of the hub having an inclination angle with respect to the rotation axis of the impeller, that is, the rotation axis force of the impeller has a certain distance. It is preferable that a boundary layer reducing portion is provided on the surface of the boss.
- the boundary layer reducing section is provided downstream of the position of about 1Z4 of the inlet end force of the impeller, which is the length to the inlet end force and the outlet end of the impeller. It is preferred that
- the starting point of the boundary layer reducing unit is located at a position separated by a predetermined distance from the inlet end force of the impeller.
- the boundary layer reduction section is not provided for a while from the impeller inlet end to the downstream side.
- the boundary layer reducing portion is formed as a convex portion projecting in a direction perpendicular to the surface of the hub.
- the force (F2) acting in a direction perpendicular to the surface of the hub causes the surface force of the hub on the surface of the convex portion to flow toward the flow path formed between the blades.
- a flow (hereinafter, referred to as “secondary flow”) is generated.
- the boundary layer formed on the surface of the hub or the surface of the protrusion moves toward the flow path formed between the blades by the secondary flow, and is dragged by the main flow flowing through the flow path. It will be carried downstream with this mainstream (by suction).
- the convex portion is provided as at least one small wing formed between the blades along a blade surface of the blade.
- the secondary impeller is formed on the surface of the small wing having a larger surface area than the above-mentioned convex portion, which is formed so as not to obstruct the mainstream flow and to minimize the generation of loss.
- the flow is generated, and the boundary layer formed on the surface of the hub or the surface of the small wing is transported more downstream by the main flow flowing through the flow path.
- the height of the small wing is preferably set to about 1 Z10 to about 1 Z2 of the height of the blade.
- the tip of the small wing looks like it enters into the main flow of the fluid, so the secondary flow force generated on the surface of the small wing ensures an effect in the main flow passing between the blades. And the thickness of the boundary layer is further reduced.
- the maximum distance between the small blades is set on the surface of the hub so as to be larger than twice the thickness of the boundary layer caused by the flow of the fluid! It is preferred that
- the space force between the small wings and the small wings It is formed so as to be more than twice the thickness of the boundary layer generated on the surface of the blade, and the main flow of fluid passes between the winglets, causing The merge of the secondary flow and the main flow of the fluid is promoted, and the thickness of the boundary layer is further reduced.
- the impeller of the compressor according to the present invention is an impeller of a centrifugal compressor, and the boundary layer reducing unit is provided to a position where a force acting in a direction perpendicular to the hub surface becomes zero. Is preferred.
- the boundary layer reducing section is configured such that the centrifugal force acting on the flow of the fluid acts in a direction in which the surface flow of the hub removes the flow of the fluid, that is, from the inlet end of the impeller. It is provided from the position where the impeller inlet end force is about 1Z4 to the outlet end to the position where the force acting in the direction perpendicular to the hub surface becomes zero, thereby forming near the hub surface. Reduced boundary layer thickness is reduced over the entire hub surface.
- the boundary layer reducing portion may be extended to a position force at which a force acting in a direction perpendicular to the hub surface becomes zero and further to a downstream side. Is preferred.
- the boundary layer reducing portion is provided so as to extend to the position force at which the force acting in the direction perpendicular to the hub surface becomes zero and further to the downstream side, The boundary layer is discharged radially outward of the impeller along the extended boundary layer reduction portion, and the thickness of the boundary layer is further reduced.
- the boundary layer reducing portion is provided up to an outlet end of the impeller.
- the boundary layer reducing portion is provided so as to extend to the impeller outlet end, so that the boundary layer extends radially outward of the impeller along the extended boundary layer reducing portion. Released and the thickness of the boundary layer is further reduced.
- the fluid that has also flowed out from the impeller outlet end force of the boundary layer reduction section reaches the diffuser provided on the downstream side in the shortest distance, so that loss due to fluid velocity distortion in the entire centrifugal compressor is reduced.
- the impeller of the compressor according to the present invention is an impeller of a mixed flow compressor, wherein the boundary layer is enlarged. It is preferable that the prevention portion is provided to the outlet end of the impeller.
- the boundary layer reducing section is configured such that the centrifugal force acting on the flow of the fluid acts in a direction in which the surface flow of the hub removes the flow of the fluid, that is, from the inlet end of the impeller. It is provided from the position of the impeller inlet end force of about 1Z4 to the outlet end to the impeller outlet end, whereby the thickness of the boundary layer formed near the hub surface is reduced over the entire hub surface. Over time.
- An impeller of a compressor according to the present invention includes a plurality of blades and a hub disposed at a root of the plurality of blades, and at least a part of a surface of the hub through which fluid flows has a rotation axis.
- the impeller of the compressor may be provided with a boundary layer expansion preventing portion provided on the surface of the hub to prevent expansion of the boundary layer caused by the flow of the fluid.
- the boundary layer formed on the surface of the hub (hub surface) is prevented from expanding by the boundary layer formed on the surface of the hub.
- the thickness of the boundary layer is smaller than that of the impeller.
- the boundary layer expansion preventing portion is provided at a portion where the centrifugal force acting on the flow of the fluid acts in a direction in which the surface force of the hub separates the flow of the fluid. Is preferred.
- the boundary layer expansion preventing portion is provided on the downstream side of a position from the inlet end to the outlet end of the impeller, where the impeller inlet end force is about 1Z4. U, preferred to be.
- the starting point of the boundary layer expansion preventing portion is located at a position separated by a predetermined distance from the inlet end force of the impeller. That is, at the inlet end of the impeller For a while from the downstream to the downstream side, the boundary layer expansion preventing portion is not provided.
- the boundary layer reducing section includes a plurality of grooves.
- the flow flowing along the hub surface near the hub surface flows into the adjacent groove valley beyond the groove crest, or adjoins beyond the groove crest.
- the flow will proceed diagonally toward the top of the groove, and the flow near the hub surface will be tongue-shaped.
- the plurality of grooves are formed linearly between the blades along a blade surface of the blade.
- the flow flowing along the hub surface near the hub surface flows into the adjacent groove valley beyond the groove crest, or adjoins beyond the groove crest.
- the flow proceeds obliquely toward the upper side of the groove, and the flow flowing along the hub surface near the hub surface is disturbed, and the expansion of the boundary layer or the separation of the flow is prevented.
- the linear groove is divided into a plurality of regions from the upstream side to the downstream side.
- the flow flowing along the hub surface near the hub surface flows into the adjacent groove valley beyond the groove crest, or adjoins beyond the groove crest.
- the flow proceeds obliquely toward the upper side of the groove, and the flow flowing along the hub surface near the hub surface is disturbed, and the expansion of the boundary layer or the separation of the flow is prevented.
- the plurality of grooves are formed in a waveform in plan view between the blades.
- the plurality of grooves may be formed in a plane sawtooth shape between the blades! I prefer to do it.
- strong turbulence is caused by the flow flowing along the knob surface near the hub surface. As a result, expansion of the boundary layer or separation of the flow is further prevented.
- the impeller of the compressor according to the present invention is characterized in that the plurality of grooves are formed between the blades so as to obliquely cross a flow path from one blade to another blade. It is preferable that the groove be formed so as to intersect with these grooves, and to include a plurality of grooves formed so as to obliquely cross the flow path from the blade on the other side to the blade on one side.
- a plurality of projections are formed, and a flow flowing along the hub surface near the hub surface collides with the projections or a groove adjacent to the hub beyond the projections. Flow into the valleys of the valleys, or proceed diagonally toward the top of the adjacent grooves beyond these protrusions. Expansion of the boundary layer or separation of the flow is prevented.
- the plurality of grooves are formed between the blades on a concentric circle centered on the rotation axis of the impeller. According to the impeller of such a compressor, all of the flow flowing along the hub surface near the hub surface flows into the adjacent groove valley beyond the groove crest, or beyond the groove crest. It will move diagonally upwards of the adjacent groove, causing strong turbulence due to the flow flowing along the hub surface near the hub surface, preventing expansion of the boundary layer or separation of the flow .
- the boundary layer reducing section has a plurality of uneven forces.
- the flow flowing along the knob surface near the hub surface collides with these convex portions, or flows into the adjacent concave portion beyond these convex portions, or Convex part adjacent beyond the convex part ⁇ ⁇
- turbulence occurs in the flow near the hub surface and along the hub surface, preventing the boundary layer from expanding or the flow from separating.
- each of the plurality of irregularities is formed in a circular shape in plan view.
- the maximum depth of the groove or the unevenness is preferably 0.3% or more and 2.0% or less, more preferably 0.5% or more 2 of the outer diameter of the impeller. 0% or less.
- the maximum depth of the groove is 0.3 mm—2.0 mm, preferably 0.5 mm—2.0 mm. It will be formed more than the groove of the machining trace (generally having a width of about 0.2% of the outer diameter of the impeller and the maximum depth) remaining on the hub surface of the impeller created by IJ re-machining. Deep and wide, grooves are formed.
- the impeller of the compressor according to the present invention is an impeller of a centrifugal compressor, wherein the boundary layer expansion preventing portion is provided up to a position where a force acting in a direction perpendicular to the hub surface becomes zero. Is preferred.
- the boundary layer expansion preventing portion is configured so that the centrifugal force acting on the flow of the fluid acts in a direction in which the flow of the fluid is released in the direction of peeling the surface force of the hub, that is, the impeller.
- the inlet end force of the impeller is also the length to the outlet end, and the impeller inlet end force is set from about 1Z4 to the position where the force acting in the direction perpendicular to the hub surface becomes zero. Disturbances occur in the flow near the surface along the knob surface, preventing the boundary layer from spreading or the flow from separating over the entire hub surface.
- the impeller of the compressor according to the present invention is an impeller of a mixed flow compressor, and it is preferable that the boundary layer expansion preventing portion is provided up to an outlet end of the impeller.
- the boundary layer expansion preventing portion is configured such that the centrifugal force acting on the flow of the fluid acts in a direction in which the flow of the fluid separates the surface force of the hub, that is, the impeller.
- the inlet end force of the impeller is also the length to the outlet end, and the impeller inlet end force is also about 1Z4 From the point to the outlet end, which causes a disturbance in the flow near the hub surface and the flow flowing along the hub surface, and enlargement of the boundary layer or separation of the flow spreads over the entire hub surface. Is prevented.
- a compressor according to the present invention includes any one of the above impellers.
- the compressor is formed on the impeller provided with the boundary layer reducing portion for reducing the thickness of the boundary layer, or on the surface of the hub.
- An impeller having a boundary layer expansion preventing portion for preventing expansion of the boundary layer is provided.
- the boundary layer reducing section can prevent local concentration of the boundary layer generated on the surface of the hub, and can reduce the thickness of the boundary layer.
- the boundary layer expansion preventing portion causes turbulence in the flow flowing near the hub surface and along the hub surface, thereby preventing expansion of the boundary layer or separation of the flow.
- FIG. 1 (a)-(c) are diagrams showing a first embodiment of an impeller according to the present invention, wherein (a) is a perspective view of a main part, and (b) is an II arrow of (a).
- FIG. 2C is a sectional view taken along line II-II of FIG.
- FIG. 2 (a) and 2 (b) are views showing a second embodiment of the impeller according to the present invention, wherein (a) is a perspective view of a main part, and (b) is a sectional view taken along line III-III of (a).
- FIG. 1 is a perspective view of a main part, and (b) is a sectional view taken along line III-III of (a).
- FIG. 3 is an essential part perspective view showing a third embodiment of an impeller according to the present invention.
- FIG. 4 is an essential part perspective view showing a fourth embodiment of an impeller according to the present invention.
- FIG. 5 is an essential part perspective view showing a fifth embodiment of an impeller according to the present invention.
- FIGS. 6 (a) and (b) are views showing a fifth embodiment of the impeller according to the present invention, wherein (a) is a cross-sectional view taken along line aa of FIG. 5, and (b) is a cross-sectional view of FIG. FIG. 4 is a cross-sectional view taken along the line b-b.
- FIG. 7 is an essential part perspective view showing a sixth embodiment of an impeller according to the present invention.
- FIGS. 8 (a) and (b) are views showing a seventh embodiment of an impeller according to the present invention, wherein (a) is a perspective view of a main part, and (b) is a plan view of a boundary layer expansion preventing part. is there.
- FIGS. 9 (a) and 9 (b) are views showing an eighth embodiment of an impeller according to the present invention, wherein (a) is a perspective view of a main part, and (b) is a plan view of a boundary layer expansion preventing portion. is there.
- FIGS. 10 (a) and (b) are views showing a ninth embodiment of an impeller according to the present invention, wherein (a) is a perspective view of a main part, and (b) is a cross-sectional view of FIG. It is.
- FIG. 11 is an essential part perspective view showing a tenth embodiment of an impeller according to the present invention.
- FIGS. 12 (a) and (b) are views showing an eleventh embodiment of an impeller according to the present invention.
- FIGS. 13 (a) and (b) are the same as FIG. 6 (b), showing other cross-sectional shapes of the groove as the boundary layer expansion preventing portion.
- FIG. 14 (a) and (b) are diagrams for explaining the problems of the conventional impeller, (a) is a cross-sectional view of the impeller of the centrifugal compressor, and (b) is a diagram of the mixed flow compressor. It is sectional drawing of an impeller.
- FIGS. 1 (a) to 1 (c) a first embodiment of an impeller of a compressor according to the present invention will be described with reference to FIGS. 1 (a) to 1 (c). It should be noted that the impeller of the present embodiment shows a specific example when applied to a centrifugal compressor.
- FIG. 1A is a perspective view of a main part of the impeller 10 according to the present embodiment, in which an end of the impeller 10 on the entrance side is omitted.
- FIG. 1 (b) is a cross-sectional view taken along the line II of FIG. 1 (a).
- FIG. 1 (c) is a cross-sectional view taken along the arrow ⁇ - ⁇ of FIG. 1 (a).
- the impeller 10 As shown in FIGS. 1 (a) to 1 (c), the impeller 10 according to the present embodiment includes a plurality of blades 11 and a hub 12 arranged at a root R of the blades 11. It is composed as a main element.
- Each of the blades 11 is mounted on the surface of the hub 12 such that the leading edge LE is located at the small diameter end 12a of the hub 12 and the trailing edge TE is located at the large diameter end 12b of the hub 12. (See Fig. 14 (a)).
- the centrifugal force F1 (see Fig. 14 (a)) of the hub surface (the surface of the hub) 12c is perpendicular to the hub surface 12c.
- the impeller inlet end force is about 1Z4 on the inlet side of the length to the outlet end (the most upstream position of the centrally located small wing 13a in Fig. 1 (a). ))
- the force is also in the area up to the position where the force F2 acting in the direction perpendicular to the hub surface 12c becomes 0 (the most downstream position (end point) of the small blades 13a and 13b in Fig. 1 (a)), and
- small wings (boundary layer reduction portions; convex portions) 13a and 13b are formed along the blade surface (or the root R of the blade 11), for example.
- Three are provided.
- the winglet 13a located at the center (that is, the winglet located at the center) of the three winglets 13a and 13b is moved from the impeller inlet end to the winglet 13a.
- the length to the outlet end in the area from the position of about 1Z4 on the inlet side to the position where the force F2 acting in the direction perpendicular to the hub surface 12c becomes 0, and in the approximate center of the blade 11 Is provided.
- the small wings 13b located on both sides of the small wings 13a act in a direction perpendicular to the hub surface 12c at a position force of about 1Z2 on the entrance side of the length from the impeller entrance end to the exit end.
- the blade 11 and the small wing 13a are provided in a region up to a position where the force F2 becomes zero.
- the cross-sectional shapes of these small wings 13a and 13b are formed so as to become gradually thinner as they move away from the hub surface 12c. Further, the leading edge and the trailing edge of these small wings 13a and 13b are also formed so as to become gradually thinner toward the upstream side and the downstream side, respectively.
- the height h of these winglets 13a, 13b (ie, the shortest distance from the hub surface 12c to the tip of the winglets 13a, 13b) is about 1Z10-about 1H10 of the height H of the blade 11 at the same radial position. Formed to be 1/2!
- the distance W between the small wing 13a and the small wing 13b (that is, the shortest distance between the tip of the small wing 13a and the tip of the small wing 13b) W is the thickness of the boundary layer BL generated on the hub surface 12c by the fluid flow. It is formed to be larger than twice ⁇ !
- the small wings 13a, 13b Is provided, on the surfaces of the small wings 13a and 13b, in a direction substantially perpendicular to the hub surface 12c (open arrows in the figure). Secondary flow occurs in the direction).
- the boundary layer BL on the hub surface 12c and the small wings 13a and 13b is dragged by this secondary flow (passes), and passes through the flow path formed between the blades 11, that is, between the blades 11.
- the fluid is guided toward the main flow, and finally merges with the main flow of the fluid and flows downstream, so that local concentration of the boundary layer BL can be prevented and the boundary layer BL can be prevented. Thickness ⁇ can be reduced.
- the height h of the small blades 13a and 13b is formed to be about 1Z10 to about 1Z2 of the height H at the same radial position of the blade 11, the surface of the small blades 13a and 13b The next flow can be reliably and effectively guided into the main flow passing between the blades 11, and the thickness ⁇ of the boundary layer BL can be further reduced.
- the gap between the small wings 13a and the small wings 13b is formed so as to be larger than twice the thickness ⁇ of the boundary layer BL generated on the hub surface 12c by the flow of the fluid and the small wings 13a and the small wings 13b
- the main flow of the fluid passes between the wings 13a and 13b, so that the secondary flow generated on the surfaces of the small blades 13a and 13b and the main flow of the fluid are promoted, and the thickness ⁇ of the boundary layer BL is further reduced. It can be done.
- leading and trailing edge forces of the small blades 13a, 13b are formed so as to gradually become thinner toward the upstream side and the downstream side, respectively. Vortex loss that occurs when colliding or moving away from the trailing edge of these winglets 13a, 13b can be minimized.
- FIG. 2A is a view similar to FIG. 1A described above, in which the end of the impeller 20 on the inlet side is omitted.
- FIG. 2 (b) is a cross-sectional view taken along the line III-III of FIG. 2 (a).
- the starting points of all the small blades 23 as the boundary layer reducing portion (convex portion) are provided at the same Cf standing position as the starting point of the small blade 13a of the first embodiment described above.
- the end points of all the small wings 23 are higher than the end points of the small wings 13a and 13b of the first embodiment described above.
- the third embodiment differs from the first embodiment in that it is provided on the downstream side, that is, on the outlet end side.
- the other components are the same as those of the first embodiment described above, so that the description of those components will be omitted here, and only the small blade 23 will be described.
- each of the cross-sectional shapes of these small wings 23 is formed so as to gradually become thinner as V away from the hub surface 12c, and gradually! RU
- leading edge and the trailing edge of these small wings 23 are formed so as to become gradually narrower toward the upstream side and the downstream side, respectively, as in the first embodiment (FIGS. 1 (b) and 1 (c)). See).
- the height h of the small wings 23 (ie, the shortest distance from the hub surface 12c to the tip of the small wings 23) h is equal to the height H of the blade 11 at the same radial position as in the first embodiment. It is formed to be about 1Z10—about 1Z2.
- the distance W between the small wings 23 (ie, the shortest distance between the tip of one of the small wings 23 and the tip of the small wing 23 adjacent to the one small wing 23) W As in the first embodiment, it is formed so as to be larger than twice the thickness ⁇ of the boundary layer BL generated on the hub surface 12c by the flow of the fluid.
- the starting force of all the small wings 23 is about 1Z4 on the inlet side of the length from the impeller inlet end to the outlet end, that is, the same position as the starting point of the small wing 13a of the first embodiment described above. Therefore, it is assumed that the surface area of the small wings 23 is larger than that of the first embodiment described above, and the secondary flow is accordingly increased, so that the concentration of the boundary layer BL can be further prevented. In particular, the thickness ⁇ of the boundary layer BL can be further reduced.
- all the end points of the small wings 23 are located at about 1Z5 on the outlet side of the length from the impeller inlet end to the outlet end, that is, from the end points of the small wings 13a and 13b of the first embodiment described above. Is also extended downstream (exit end side), so that the boundary layer BL is discharged radially outward of the impeller 20 along the surface of the extended small wing 23.
- the thickness ⁇ of the boundary layer BL can be further reduced.
- FIG. 3 is a view similar to FIGS. 1 (a) and 2 (a) described above, with the end of the impeller 30 on the inlet side omitted.
- the impeller 30 of the present embodiment differs from that of the second embodiment in that the end points of all the small wings 33 as the boundary layer reducing portion (convex portion) are provided to extend to the outlet end of the impeller 30. .
- the other components are the same as those of the second embodiment described above, so that the description of those components is omitted here, and only the small wing 33 will be described.
- each of the cross-sectional shapes of these small wings 33 is formed so as to gradually become thinner as V away from the hub surface 12c, and so on! RU
- leading edge and the trailing edge of these small wings 33 are formed so as to gradually become narrower toward the upstream side and the downstream side, respectively, as in the first embodiment (FIGS. 1 (b) and 1 (c)). See).
- the height h of the small wings 33 (that is, the shortest distance from the hub surface 12c to the tip of the small wings 33) is the same as that of the height H at the same radial position of the blades 11 as in the first embodiment described above. It is formed to be about ⁇ —about 1Z2.
- the distance W between the small wings 33 (ie, the shortest distance between the tip of one small wing 33 and the tip of the small wing 33 adjacent to the one small wing 33) W As in the first embodiment, it is formed so as to be larger than twice the thickness ⁇ of the boundary layer BL generated on the hub surface 12c by the flow of the fluid.
- the boundary layer is discharged radially outward of the impeller 30 along the surface of the extended small wings 33.
- the thickness ⁇ of the boundary layer BL can be further reduced.
- FIG. 4 is a view similar to FIGS. 1 (a), 2 (a), and 3 described above, and is a view in which the end of the impeller 40 on the inlet side is omitted.
- the impeller 40 according to the present embodiment is applied to a mixed flow compressor, and includes impellers 13a and 13b as boundary layer reduction portions (convex portions) shown in FIG. 1 (a) and FIG. 1 (c). A similar small wing force is formed on the hub surface 12c.
- the impeller 40 includes a plurality of blades 11 and a hub 12 disposed at a root R of the blades 11 as main elements. You.
- Each of the blades 11 is mounted on the surface of the hub 12 such that the leading edge LE is located at the small diameter end 12a of the hub 12 and the trailing edge TE is located at the large diameter end 12b of the hub 12. (See Fig. 14 (b)).
- the entrance side From the position of about 1Z4 (the most upstream position of the winglet located at the center in Fig. 4 (starting point)) to the outlet end of the impeller (the most downstream position of the winglet in Fig. 4 (endpoint)) In the area up to and between blades 11 and 11, the wings 43a, 43b force along the wing surface of blade 11 (there is! /! Is the root R of blade 11) Book is provided.
- the winglet located at the center (that is, the winglet located at the center) 43a has the impeller inlet end force and the impeller end force up to the outlet end. Of the length, it is provided in a region from a position of about 1Z4 on the entrance side to an exit end of the impeller, and substantially at the center between the blades 11.
- the small wings 43b located on both sides of the small wings 43a are in the area from the position about 1Z2 on the inlet side to the outlet end of the impeller, and It is provided at a substantially central portion between 11 and the small wing 13a.
- each of the cross-sectional shapes of these small wings 43a and 43b is formed so as to become gradually thinner away from the hub surface 12c.
- leading edge and the trailing edge of these small wings 43a, 43b are formed so as to gradually become narrower toward the upstream side and the downstream side, respectively, as in the first embodiment (FIGS. 1 (b) and 1 (c)). )reference).
- the heights h of the small blades 43a and 43b are the same as those in the first embodiment described above, at the same radial position of the blade 11.
- the height H is about 1Z10—about 1Z2.
- the distance between the small wings 43a and the small wings 43b (i.e., the shortest distance between the tip of the small wings 43a and the small wings 43b) w is the thickness of the boundary layer BL generated on the hub surface 12c by the fluid flow. It is formed to be larger than twice ⁇ !
- the small wings 43a, 43b extend along the blade surface of the blade 11 in the region of the hub surface 12c where the centrifugal force F1 (see FIG. 14 (b)) acts perpendicular to the hub surface 12c.
- the secondary flow on the surfaces of the small wings 43a and 43b in a direction substantially perpendicular to the hub surface 12c (the same direction as the white arrows in FIGS. 1 (a) and 1 (b)). Occurs.
- the boundary layer BL on the hub surface 12c and the small wings 43a and 43b is dragged by the secondary flow (together) to form a flow path formed between the blades 11, that is, the main flow of the fluid passing between the blades 11 Will be led to the final Since the fluid merges with the main flow of the fluid and flows downstream, local concentration of the boundary layer BL can be prevented, and the thickness ⁇ of the boundary layer BL can be reduced.
- the height h of the blades 43a, 43b is formed so that the height H at the same radial position of the blade 11 is about 1Z10 to about 1Z2.
- the next flow can be reliably and effectively guided into the main flow passing between the blades 11, and the thickness ⁇ of the boundary layer BL can be further reduced.
- the gap W between the small wings 43a and the small wings 43b is formed so as to be larger than twice the thickness ⁇ of the boundary layer BL generated on the hub surface 12c due to the flow of the fluid. Since the main flow of the fluid passes between the main flow of the fluid and the secondary flow generated on the surfaces of the small blades 43a and 43b, the thickness of the boundary layer BL is further increased. It can be reduced.
- leading and trailing edge forces of the small blades 43a and 43b are formed so that they gradually become thinner toward the upstream side and the downstream side, respectively, so that the main flow of the fluid is applied to the leading edge of the small blades 43a and 43b. Vortex loss that occurs when colliding or moving away from the trailing edge of these winglets 43a, 43b can be minimized.
- the tip force of the small wings 43a, 43b is formed so that it gradually becomes thinner as it moves away from the hub surface 12c, so that the secondary flow generated on the surfaces of the small wings 43a, 43b is The vortex loss that occurs when the tip force of 43b also moves away can be minimized
- the present invention is not limited to the above-described embodiment.
- the starting point of the small wing 43b shown in Fig. 4 is changed from the impeller inlet end to the outlet end as in Fig. 2 (a) or Fig. 3. Of the lengths up to, it can be located at about 1Z4 on the entrance side.
- the number of small wings is not limited to three. Any number of small wings may be used as long as the main flow velocity can exist between the small wings.
- a fifth embodiment of the impeller of the compressor according to the present invention will be described with reference to Figs. 5, 6 (a) and 6 (b).
- the impeller of the embodiment described below is a centrifugal compressor. It is applied to
- FIG. 5 is a perspective view of a main part of the impeller 310 according to the present embodiment, in which about 1Z4 on the inlet side is omitted from the inlet end of the impeller to the outlet end of the impeller.
- 6 (a) is a sectional view taken along the line aa of FIG. 5, and
- FIG. 6 (b) is a sectional view taken along the line bb of FIG.
- an impeller 310 is configured such that a plurality of blades 11 and a hub 12 arranged at a root portion R of the blades 11 are main components. is there.
- Each of the blades 11 is mounted on the surface of the hub 12 such that the leading edge LE is located at the small diameter end 12a of the hub 12 and the trailing edge TE is located at the large diameter end 12b of the hub 12. (See Fig. 14 (a)).
- the centrifugal force F1 see Fig. 14 (a)
- the centrifugal force F1 acts perpendicularly to the hub surface 12c, for example, the length of the impeller inlet end force to the outlet end also.
- the position of about 1 Z4 on the inlet side the position indicated by hatching in Fig. 5
- there are a plurality of straight grooves (boundary layer expansion preventing portions) 313 along the blade surface of the blade 11 (or the root R of the blade 11) (FIG. 5). 5 are shown in the figure.
- Reference numeral 314 in FIG. 5 is a machining trace when the impeller 310 is manufactured by cutting using a ball end mill, and the force F2 acting on the hub surface 12c in a direction perpendicular to the hub surface 12c is 0. 12 shows twelve small grooves provided in the region. Each of the maximum depth and width of this groove is generally about 0.2% of the outer diameter of the impeller as described above. Therefore, if the impeller diameter is 100 mm, the maximum depth and width are each about 0.2 mm.
- the groove 313 provided as the boundary layer expansion preventing portion is formed deeper than the groove 314 of the machined trace formed at the time of manufacturing the impeller. It is something. That is, it is formed so that HI> hl.
- HI is the maximum depth of the groove 313, and hi is the depth of the trace of kauge that was formed when the hub surface 12c was cut.
- the maximum depth H1 of the groove 313 is set to about the excluded thickness of the hub surface boundary layer, Specifically, it is preferably 0.3% or more and 2.0% or less of the impeller outer diameter, and most preferably 0.5% or more and 2.0% or less. That is, if the outer diameter of the impeller is 100 mm, the maximum depth HI of the groove 313 is preferably 0.3 mm to 2.0 mm, most preferably 0.5 mm to 2.0 mm.
- the groove 313 is formed in a straight line, the processing of the groove 313 can be easily performed, and the manufacturing cost can be suppressed.
- FIG. 7 is a view similar to FIG. 5 described above, and is a perspective view of a main part in which about 1Z4 on the inlet side is omitted from the length from the inlet end of the impeller to the outlet end of the impeller.
- the impeller 320 of the present embodiment differs from that of the fifth embodiment in that the shape of the groove 323 as a boundary layer expansion preventing portion in a plan view is formed in a waveform.
- the other components are the same as those of the fifth embodiment described above, and thus the description of those components will be omitted here, and only the plan view shape of the groove 323 will be described.
- the groove 323 as the boundary layer expansion preventing portion in the present embodiment has a shape in plan view having a waveform, that is, a peak portion and a valley portion in plan view are each formed by a smooth curve. These ridges and valleys are formed so as to be continuous. Since the depth of the groove 323 is the same as that of the groove 313 of the fifth embodiment described above, the description is omitted here.
- the groove 323 flows into the adjacent groove 323 beyond the peak of the groove 323, or flows into the groove 323 of the adjacent groove 323. Since there is a portion where the angle between the direction of the flow that proceeds obliquely toward the top of the adjacent groove 323 beyond the peak and the peak of the groove 323 and the peak of the groove 323 is larger than that of the fifth embodiment, the portion is formed at that portion.
- the flow near the hub surface 12c along the hub surface 12c causes strong and turbulent flow, which prevents expansion of the boundary layer or separation of the flow.
- FIG. 8 (a) is a view similar to FIGS. 5 and 7 described above, and is a perspective view of the main part of the length from the inlet end of the impeller to the outlet end of the impeller, in which about 1Z4 on the inlet side is omitted. You.
- the impeller 330 according to the present embodiment is different from the above-described embodiment in that the groove 333 as the boundary layer expansion preventing portion has a sawtooth shape in plan view.
- Other components are the same as those of the above-described embodiment, and therefore, the description of those components will be omitted here, and only the shape of the groove 333 in plan view will be described.
- the groove 333 as the boundary layer expansion preventing portion in the present embodiment has a sawtooth shape in plan view, that is, has two peaks and two valleys in plan view. And the ridges and valleys are continuous, and the ridges and valleys are connected by a straight line. Since the width and depth of the groove 333 are the same as those of the above-described embodiment, the description is omitted here.
- the groove 333 flows into a valley portion of the adjacent groove 333 beyond the peak portion of the groove 333, or There is a portion where the angle between the direction of the flow that proceeds obliquely upward of the adjacent groove 333 beyond the peak of the groove 333 and the peak of the groove 333 is larger than that of the fifth embodiment, and Since such a portion can be formed more than in the sixth embodiment, strong turbulence occurs near the hub surface 12c due to the flow flowing along the hub surface 12c and the expansion of the boundary layer or the flow of the flow. Peeling can be prevented.
- FIGS. 9 (a) and 9 (b) An eighth embodiment of the impeller of the compressor according to the present invention will be described with reference to FIGS. 9 (a) and 9 (b).
- Fig. 9 (a) is a view similar to Fig. 5, Fig. 7, and Fig.
- FIG. 4 is a perspective view of a main part of the length from the inlet end to the outlet end of the impeller, in which about 1Z4 on the inlet side is omitted.
- the impeller 340 of this embodiment is different from that of the above-described embodiment in that grooves 343 serving as boundary layer expansion preventing portions are formed so as to intersect each other.
- the other components are the same as those of the above-described embodiment, so that the description of those components is omitted here, and only the groove 343 will be described.
- the groove 343 as the boundary layer expansion preventing portion in the present embodiment is formed by obliquely extending the flow path formed between the blades 11 from one side to the other side. And a plurality of grooves 343a formed so as to intersect with each other, and are formed so as to intersect with the grooves 343a. And a plurality of grooves 343b formed so as to intersect. That is, in the figure, the groove 343a extending downward and to the upper right and the groove 343b extending upward and to the lower right also intersect with each other.
- solid lines indicating the grooves 343a and 343b indicate lines formed by the deepest portions of the grooves.
- Reference numeral 343c denotes a portion that remains after the grooves 343a and 343b are carved, that is, a protrusion on the top surface where machining marks formed during the impeller fabrication are left.
- the grooves 343 as the boundary layer expansion preventing portions so as to intersect with each other, a plurality of projections 343c are formed, and the vicinity of the hub surface 12c extends along the knob surface 12c.
- the flow that flows through the protrusions 343c collides with the protrusions 343c, or flows into the valleys of the adjacent grooves 343a and 343b beyond the protrusions 343c, or flows upwards beyond the protrusions 343c and the adjacent grooves 343a and 343b.
- the flow flows obliquely near the hub surface 12c, and the flow flowing along the hub surface 12c is disturbed, so that the boundary layer can be prevented from expanding or the flow from separating.
- Fig. 10 (a) is a view similar to Fig. 5, Fig. 7, Fig. 8 (a), and Fig. 9 (a), and shows the length between the impeller inlet end and the impeller outlet end.
- FIG. 4 is a perspective view of a main part in which about 1Z4 is omitted.
- the impeller 350 of this embodiment is different from that of the above-described embodiment in that a groove 353 as a boundary layer expansion preventing portion is formed on a concentric circle centered on the rotation axis of the impeller 350.
- the other components are the same as those of the above-described embodiment, and therefore the description of those components will be omitted here, and only the groove 353 will be described.
- the groove 353 as the boundary layer expansion preventing portion in the present embodiment is formed on a concentric circle centered on the rotation axis of the impeller 350, that is, from the rotation axis of the impeller 350 to the impeller 350. It is formed so as to be orthogonal to the radiation extending toward the outer peripheral edge of the target.
- FIG. 10 (b) is a cross-sectional view taken along the line c-c in FIG. 10 (a).
- the groove 353 as the boundary layer expansion preventing portion on a concentric circle centered on the rotation axis of the impeller 350, all the flows flowing along the hub surface 12c near the hub surface 12c are formed. Flow into the valley of the adjacent groove 353 over the crest of the groove 353, or go obliquely toward the upper side of the adjacent groove 353 beyond the crest of the groove 353, and slip. On the other hand, a strong turbulence is generated by the flow flowing along the knob surface 12c near the hub surface 12c, and it is possible to prevent the boundary layer from expanding or the flow from being separated.
- the groove 353 is formed in a straight line, the processing of the groove 353 can be easily performed, and the manufacturing cost can be suppressed.
- grooves on the concentric circles may be formed in a corrugated manner as in the sixth embodiment, or may be formed in a sawtooth shape as in the seventh embodiment.
- Fig. 11 is a view similar to Fig. 5, Fig. 7, Fig. 8 (a), Fig. 9 (a), and Fig. 10 (a), and shows the impeller inlet end force length to the impeller outlet end. Of which about 1Z4 on the entrance side is omitted It is a part perspective view.
- the impeller 360 of the present embodiment is different from the above-described embodiment in that the groove 363 as the boundary layer expansion preventing portion is formed in a plurality of regions (three regions 363a, 363b, and 363c in the present embodiment). Different from the ones. Other components are the same as those of the above-described embodiment, and therefore, the description of those components will be omitted here, and only the groove 363 will be described.
- the groove 363 as the boundary layer expansion preventing portion in this embodiment is basically the same as the groove in the fifth embodiment shown in FIG.
- the third embodiment differs from that of the fifth embodiment in that three regions 363a, 363b, and 363c are harmed ij by working toward the downstream side. That is, in the area of the hub surface 12c where the centrifugal force acts perpendicular to the hub surface 12c, for example, the position of about 1Z4 on the inlet side of the length from the inlet end to the outlet end of the impeller (see FIG. 5).
- the area from the position indicated by hatching to the position where the force F2 acting in the direction perpendicular to the hub surface 12c becomes 0 is divided into three areas 363a, 363b, and 363c, and each area is divided into three areas.
- a plurality of linear grooves 363 along the surface of blade 11 between blades 11 (four in area 363a, four in area 363b, and five in area 363c in FIG. 11) Shown! /, Ru) are provided!
- FIGS. 12 (a) and 12 (b) An eleventh embodiment of the impeller of the compressor according to the present invention will be described with reference to FIGS. 12 (a) and 12 (b).
- Fig. 12 (a) is a view similar to Fig. 5, Fig. 7, Fig. 8 (a), Fig. 9 (a), Fig. 10 (a), and Fig. 11, in which the impeller outlet is connected to the impeller inlet end.
- FIG. 3 is a perspective view of a main part in which about 1Z4 on the entrance side is omitted from the length to the end.
- the impeller 370 in the present embodiment is provided with a plurality of convex portions 373a and a plurality of concave portions (dimples) 373b instead of the grooves described so far as the boundary layer expansion preventing portion. This is different from the embodiment described above.
- the description of those components is omitted here, and only the convex portion 373a and the concave portion 373b will be described.
- each of the convex portion 373a and the concave portion 373b as the boundary layer expansion preventing portion in the present embodiment has a circular shape in plan view, and has a cross-section as shown in FIG. 12 (b). It has a semicircular view.
- the diameter and depth of the convex portion 373a and the concave portion 373b are preferably not less than 0.3% and not more than 2.0% of the outer diameter of the impeller, as in the above-described embodiment. % Is most preferable.
- the flow flowing along the hub surface 12c near the hub surface 12c is achieved. It collides with 373a, flows into these adjacent concave portions 373b over these convex portions 373a, or goes diagonally upwards over these convex portions 373a and concave portions 373b beyond these convex portions 373a. As a result, the flow flowing near the hub surface 12c along the knob surface 12c is disturbed, and the expansion of the boundary layer or the separation of the flow can be prevented.
- the present invention can be applied not only to a centrifugal compressor but also to a mixed flow compressor.
- the centrifugal force F1 acts perpendicularly to the hub surface 12c up to the outlet end of the impeller in the mixed flow compressor.
- the area where the boundary layer expansion prevention section is provided covers the area up to the exit end of the impeller. That is, the portion of the groove 314 shown in FIGS. 5, 7, 8 (a), 9 (a), 10 (a), 11 and 12 (a) also corresponds to the boundary layer shown in these drawings. This is the target area where the expansion prevention part is to be provided.
- the cross-sectional shapes of the grooves 313, 323, 333, 343a, 343b, 353, and 363 are not limited to those shown in Fig. 6B, for example, as shown in Figs.
- the cross section should be as shown in b). That is, as shown in FIG. 13 (a), the valley of the groove can be formed by a curve, and the groove can have a cross-sectional shape like a sawtooth connecting the valley and the peak of the mountain with a straight line, or As shown in FIG. 13 (b), it is better to leave the processing mark 314 left at the beginning of the impeller production at the top of the groove.
- the present invention is not limited to being applied only to impellers produced by shaving, but can also be applied to animal impellers produced by machining.
- a device for forming the above-described boundary layer expansion preventing portion may be formed on the surface of the ⁇ shape in advance.
- boundary layer expansion preventing portion according to the present invention is not limited to the groove, the convex portion, or the concave portion described above. The same effect as the effect obtained can be obtained.
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US10/577,715 US20070134086A1 (en) | 2003-12-03 | 2004-12-02 | Impeller for compressor |
EP04819881A EP1707824A4 (en) | 2003-12-03 | 2004-12-02 | WHEEL FOR COMPRESSORS |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2003403957A JP2005163640A (ja) | 2003-12-03 | 2003-12-03 | 圧縮機のインペラ |
JP2003-403957 | 2003-12-03 | ||
JP2003-424283 | 2003-12-22 | ||
JP2003424283A JP2005180372A (ja) | 2003-12-22 | 2003-12-22 | 圧縮機のインペラ |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005054681A1 true WO2005054681A1 (ja) | 2005-06-16 |
Family
ID=34656208
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/JP2004/017916 WO2005054681A1 (ja) | 2003-12-03 | 2004-12-02 | 圧縮機のインペラ |
Country Status (4)
Country | Link |
---|---|
US (1) | US20070134086A1 (ja) |
EP (1) | EP1707824A4 (ja) |
KR (1) | KR20060086960A (ja) |
WO (1) | WO2005054681A1 (ja) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103270310A (zh) * | 2010-12-28 | 2013-08-28 | 三菱重工业株式会社 | 离心压缩机 |
JP2015031180A (ja) * | 2013-07-31 | 2015-02-16 | 三菱重工業株式会社 | 回転機械 |
CN106499665A (zh) * | 2016-11-23 | 2017-03-15 | 西安交通大学 | 一种避免叶轮振动中靶向能量传递现象发生的叶轮优化设计方法 |
WO2021234863A1 (ja) * | 2020-05-20 | 2021-11-25 | 三菱重工エンジン&ターボチャージャ株式会社 | 遠心圧縮機のインペラ及び遠心圧縮機 |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP5762641B2 (ja) * | 2012-09-06 | 2015-08-12 | 三菱重工業株式会社 | 斜流タービン |
JP5611379B2 (ja) | 2013-01-23 | 2014-10-22 | 株式会社豊田自動織機 | ターボチャージャ用インペラ、ターボチャージャ用インペラの製造方法、ターボチャージャ、及びターボユニット |
DE102014222877A1 (de) * | 2014-11-10 | 2016-05-12 | Siemens Aktiengesellschaft | Laufrad einer Radialturbofluidenergiemaschine, Stufe |
WO2016185570A1 (ja) * | 2015-05-19 | 2016-11-24 | 株式会社日立製作所 | 遠心圧縮機 |
FR3059735B1 (fr) * | 2016-12-05 | 2020-09-25 | Safran Aircraft Engines | Piece de turbomachine a surface non-axisymetrique |
WO2019097611A1 (ja) * | 2017-11-15 | 2019-05-23 | 三菱重工エンジン&ターボチャージャ株式会社 | コンプレッサインペラ、コンプレッサ及びターボチャージャ |
KR102537524B1 (ko) * | 2018-07-06 | 2023-05-30 | 엘지전자 주식회사 | 팬 |
JP7310739B2 (ja) * | 2020-07-14 | 2023-07-19 | 株式会社豊田自動織機 | インペラおよびその製造方法 |
DE102021133772B3 (de) * | 2021-12-18 | 2023-01-19 | Borgwarner Inc. | Verdichterrad |
DE102021133773B3 (de) | 2021-12-18 | 2023-02-09 | Borgwarner Inc. | Verdichterrad |
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US3069072A (en) * | 1960-06-10 | 1962-12-18 | Birmann Rudolph | Impeller blading for centrifugal compressors |
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JP2002349488A (ja) * | 2001-05-23 | 2002-12-04 | Hitachi Ltd | 空気調和機用室内機 |
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US3481531A (en) * | 1968-03-07 | 1969-12-02 | United Aircraft Canada | Impeller boundary layer control device |
DE2141262A1 (de) * | 1971-08-18 | 1973-02-22 | Daimler Benz Ag | Verdichter |
SU1059217A1 (ru) * | 1982-09-08 | 1983-12-07 | Всесоюзный Научно-Исследовательский Институт "Гелиевая Техника" | Рабочее колесо центростремительной турбины |
WO1990002265A1 (en) * | 1988-08-16 | 1990-03-08 | Dresser-Rand Company | Partial height blades in a compressor impeller |
US5215439A (en) * | 1991-01-15 | 1993-06-01 | Northern Research & Engineering Corp. | Arbitrary hub for centrifugal impellers |
DE4319628A1 (de) * | 1993-06-15 | 1994-12-22 | Klein Schanzlin & Becker Ag | Strukturierte Oberflächen von Strömungsmaschinenbauteilen |
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2004
- 2004-12-02 EP EP04819881A patent/EP1707824A4/en not_active Withdrawn
- 2004-12-02 US US10/577,715 patent/US20070134086A1/en not_active Abandoned
- 2004-12-02 WO PCT/JP2004/017916 patent/WO2005054681A1/ja not_active Application Discontinuation
- 2004-12-02 KR KR1020067009028A patent/KR20060086960A/ko not_active Application Discontinuation
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US3069072A (en) * | 1960-06-10 | 1962-12-18 | Birmann Rudolph | Impeller blading for centrifugal compressors |
JPH0212096U (ja) * | 1988-07-07 | 1990-01-25 | ||
JPH09264296A (ja) * | 1996-03-28 | 1997-10-07 | Mitsubishi Heavy Ind Ltd | 遠心流体機械のインペラ |
JP2002349488A (ja) * | 2001-05-23 | 2002-12-04 | Hitachi Ltd | 空気調和機用室内機 |
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Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103270310A (zh) * | 2010-12-28 | 2013-08-28 | 三菱重工业株式会社 | 离心压缩机 |
CN103270310B (zh) * | 2010-12-28 | 2016-05-25 | 三菱重工业株式会社 | 离心压缩机 |
US9638208B2 (en) | 2010-12-28 | 2017-05-02 | Mitsubishi Heavy Industries, Ltd. | Centrifugal compressor |
JP2015031180A (ja) * | 2013-07-31 | 2015-02-16 | 三菱重工業株式会社 | 回転機械 |
CN106499665A (zh) * | 2016-11-23 | 2017-03-15 | 西安交通大学 | 一种避免叶轮振动中靶向能量传递现象发生的叶轮优化设计方法 |
WO2021234863A1 (ja) * | 2020-05-20 | 2021-11-25 | 三菱重工エンジン&ターボチャージャ株式会社 | 遠心圧縮機のインペラ及び遠心圧縮機 |
Also Published As
Publication number | Publication date |
---|---|
EP1707824A1 (en) | 2006-10-04 |
US20070134086A1 (en) | 2007-06-14 |
KR20060086960A (ko) | 2006-08-01 |
EP1707824A4 (en) | 2007-05-09 |
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