US3069070A - Diffuser vane system for turbomachinery - Google Patents
Diffuser vane system for turbomachinery Download PDFInfo
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- US3069070A US3069070A US152301A US15230161A US3069070A US 3069070 A US3069070 A US 3069070A US 152301 A US152301 A US 152301A US 15230161 A US15230161 A US 15230161A US 3069070 A US3069070 A US 3069070A
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- vanes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
Definitions
- a turbomachine which comprises a casing having an inlet means and an outlet means therein.
- An impeller is disposed in the casing between the inlet means and the outlet means.
- at least two rows of radially sapced vanes are disposed in the outlet means with one vane from each of the rows of vanes mounted on each of the members.
- Means are operatively associated with each of the rotatable members and adapted to rotate the members to maintain the optimum incidence angle of the vanes mounted on the members.
- One of the objects of this invention is to minimize the frictional losses by controlling the solidity ratio and aspect ratio of the diffuser vane system.
- Another object of this invention is to lower the energy loss by limiting the boundary layer growth of the diffuser vane system.
- Another object of this invention is to simplify the mechanical arrangement of the rotatable diffuser vane system.
- Another object of this invention is to provide for improved efficiency throughout a wide range of flow by rotatable diffuser vane means.
- Another object of this invention is to prevent resonance and excessive vibration of the vane members.
- Still another object of this invention is to balance the forces acting on the rotatable diffuser vanes so as to reduce the torque required to rotate the discs the vanes are mounted on.
- Still another object of this invention is to eliminate stalling of the fluid flowing in the diffuser vane system thereby preventing surge.
- FIGURE 1 is a partial section perpendicular to the axis of the impeller and embodying the novel diffuser vane system.
- FIGURE 2 is a section taken in the direction of lin 2--2 of FIGURE 1.
- FIGURE 3 is a section taken in the 3-3 of FIGURE 2.
- FIGURE 4 is a partial section perpendicular to the axis of the impeller and showing the vane angle changed.
- FIGURE 1 shows a turbomachine 10 in which the novel diffuser vane system 11 is used.
- the turbomachine 10 could be any type of pump or compressor, for example, having a driving impeller 12 in a casing 13 and mounted on a shaft 14, the shaft 14 being connected to a suitable source of power (not shown).
- the diffuser vane system 11 as shown in FIGURES 1 and 2 is located in the discharge passageway 15 of the casing 13 adjacent the outlet 16 but it is understood that certain applications may warrant the use of this type system in a suitable inlet and it is understood that such a modification is within the scope of this invention as hereinafter described and claimed.
- the diffuser vane system 11 utilizes vanes 17 and 18 arranged in radially spaced rows, there being shown an inner row of vanes 19 and an outer row of vanes 20 but it is clear that any suitable number of rows of vanes could be used.
- One vane 17 from the inner row of vanes 19 and one vane 18 from the outer row of vanes 20 is mounted on a plurality of rotatable discs 21 which are disposed in equidistant circumferentially spaced circular recesses 22 in the wall 38 of the passageway 15.
- the vanes 17 and 18 are of shorter length than could be used in a single vane row system. This is especially important in considering and designing for each row of vanes the optimum aspect ratio b/a, the solidity ratio a/c, in order to limit boundary layer growth, friction losses, vane vibration and surging; where b is the span of the vane; a is the length of the vane; c is the distance between leading edges of adjacent vanes of the same row.
- vanes 17 and 18 are mounted on the outboard side 23 of the discs 21 substantially perpendicular to a line passing through the axis 24 of the impeller 12 and the center 25 of the disc 21 and the vane 17 has its leading edge 26 located substantially on this line. Vane 18 is then positioned, as shown in FIGURE 1, So that the forces acting on vanes 17 and 18 will be balanced about the center 25 of the disc 21 and no resulting moment will be created about shaft 27.
- Shaft 27 is connected to the inboard side 28 of the discs 21 as illustrated in FIGURE 2.
- the recess 22 has a bore 29 and a counterbore 30 therein.
- Bearing members 31 are provided, one being put on before the shaft 27 is placed through the bore 29 and one put on thereafter. Bearing members 31 do not restrict the rotation of the discs 21 and prevent leakage about shaft 27.
- a clevis 32 is mounted outside the casing 13 on the outer end 33 of each shaft.
- the clevis 32 is held in position by a locking pin 34.
- Linkage 35 is connected to the clevis 32 by pins 36 as illustrated in FIGURE 3. This linkage interconnects all the shafts and may be moved in any suitable manner such as by a lever (not shown).
- the simultaneous rotation of a plurality of discs is well know in the art and can be coupled with an angle indicator '(not shown) which is also well known to show the rotation angle of the vanes.
- the discs 21 as shown in FIGURE 1 are marked as at 37 which corresponds to a mark 39 on the wall 38 of the passageway 15 and indicates the normal operative position. This position can be changed as shown in FIGURE 4 by rotating the discs 21 to maintain an optimum incidence angle corresponding to the flow characteristics.
- vanes 17 and 18 are equidistantly circumferentially spaced in their respective rows in the balanced position hereinbefore described. This spacing allows the boundary layers formed on the vanes 17 of the inner row of vanes 19 to be shed between the vanes 18 of the outer row of vanes 20.
- vanes 17 are adjacent the discharge tip 40 of the impeller 12 and therefore in an area in which the fluid flow will have the highest Mach number. Because of this the vanes are designed to be lightly loaded or in other words vanes 17 are of a smaller profile than vanes 18. Also on rotation of discs 21 the leading edge 26 of the vanes 17 describes an arcuate path away from the axis 24 of the impeller 12 as it is located normally at the closest radial distance to the axis 24 of the impeller 12. Thus the vane 17 will not enter an area of higher Mach number than that encountered during normal operation.
- trailing end 41 of the vanes 17 extend over the side of disc 21 and has an d/e ratio which does not exceed to prevent resonance and consequent high amplitude vibration from developing; where e is vane thickness at the point of extending over the side of disc 21 and d is vane overhang length.
- vanes 18 of the outer row of vanes 29 are designed to be highly loaded as they are in an area of lower Mach number.
- vanes 17 and 18 are fixedly connected to each of the discs 21 substantially parallel to each other in a balance position to facilitate easy rotation of the discs 21 and to prevent creating a moment about the shaft 27. But the angular relationship of vanes 17 and 18 may be varied within 20 from this parallel relationship in order to accommodate a wide range of design conditions.
- This invent-ion permits a greater overall conversion of kinetic energy to pressure energy for a given loading on a single vane row system.
- inlet guide vanes 42 illustrated in FIGURE 5 are used in the inlet 43 it is preferred that they be provided in the same number as that of the discs 21 to prevent development of non-symmetrical flow caused by the wakes from the inlet guide vanes 42 interacting with the vanes 17 and 18. It Will be understood that this invention is not to be limited to the specific construction or arrangement of parts shown, but that they may be widely modified within the invention defined by the claims.
- a turbomachine comprising:
- each of said vanes of said rows of vanes are mounted on said rotatable member in a normally operative position in a substantially perpendicular relationship with a line passing through the axes of said impeller and said rotatable member and on rotation of said rotatable member the incidence angle of said vanes thereon can be selectively positioned.
- each of said vanes of said first row of vanes having the leading edge thereof located on the plane passing through the axis of said impeller and said rotatable member in a normally operative position
- the leading edge of said vanes to prescribe an arcuate path away from the axis of said impeller on rotation of said rotatable member in a direction opposite to the rotational direction of said impeller to prevent the leading edge of said vane from getting closer to the discharge tip of said impeller and thereby entering a higher Mach number area of fluid flow.
- each of said vanes of said second row of vanes disposed on said rotatable member in normal operative position a greater radial distance from the axis of said impeller than the radial distance of each of said vanes of said first row of vanes
- the leading edge of each of said vanes of each row of vanes facing the direction of rotation of said impeller (c) the leading edge of said vanes of said second row of vanes to extend over the side of said rotatable member whereby the weight of said vanes of said first row of vanes will not impinge on said vanes of said second row of vanes.
- a turbo machine comprising (a) a casing having an inlet means and an outlet means therein (b) said outlet means including an annular passageway means in said casing (c) an impeller in said casing between said inlet means and said passageway means (a') said passageway means having a plurality of circular recesses equal distantly spaced in circumferencial relationship to each other (e) each of said recesses having a bore therethrough (f) a disc member disposed in said recess and having a shaft connected to the inward side thereof to extend through the bore in said recess (g) means connecting each of said shafts and adapted to rotate each of said shafts thereby rotating said discs (h) an inner row of vanes and an outer row of vanes radially spaced from the axis of said impeller and one vane from each of said rows of vanes mounted on each of said discs (1') each of said vanes of said inner row of vanes having the leading edge thereof located on the plane passing through the center of said disc and the axis
- each of said vanes in said inner row of vanes has a trailing end extending over the side of said disc
- said trailing end of said vanes has a ratio of the total extension to the thickness at the point of extending over the side of said disc not to exceed 5 to prevent high amplitude vibration and resonance.
- each of said discs having said vane of said inner row of vanes normally mounted on the half of said disc below the center thereof adjacent the discharge tip of said impeller,
- each of said discs having said vane of said outer row of vanes normally mounted on the half of said disc above the center thereof remote from the discharge tip of said impeller,
- each of said discs having said vanes from said inner row of vanes and said outer row of vanes mounted thereon in a normally operative position in substantially perpendicular relationship with a line passing through the axis of said impeller and the center of said disc whereby said vanes act to diffuse the fluid flowing in said passageway means.
- each of said discs adapted to be rotated simultaneously by said means operatively associated therewith to maintain the optimum incidence angle of said vanes mounted substantially parallel thereon whereby the diifuser vane efficiency can be maintained over a Wide range of flow.
- a turbomachine comprising:
- said outlet means including an annular passageway means in said casing
- each of said discs having a pair of radially spaced substantially parallel vanes mounted thereon,
- the inner vane is closer to the axis of said impeller and of substantially smaller profile than the outer vane
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Description
air;
Dec. 18, 1962 Filed Nov. 14, 1961 C. A. MACALUSO ETAL DIFFUSER VANE SYSTEM FOR TURBOMACHINERY Z4 P16. P.
2 Sheets-Sheet l FIG.3
HUNT DAViS CHARLES A. MACALUSO INVENTORS WMMM Dec. 18, 1962 c. A. MACALUSO ETAL 3,
DIFFUSER VANE SYSTEM FOR TURBOMACHINERY Filed NOV. 14, 1961 2 She'etsSheet 2 HUNT DAVIS CHARLES A. MACALUSO IN V EN TORS United States Patent Ofifice 3,069,070 Patented Dec. 18, 1962 3,069,070 DIFFUSER VANE SYSTEM FOR TURBO- MACHINERY Charles A. Macaluso, Wayne, and Hunt Davis, Summit, N.J., assignors to Worthington Corporation, Harrison, N.J., a corporation of Delaware Filed Nov. 14, 1961, Ser. No. 152,301 16 Claims. (Cl. 230-115) This invention relates generally to turbomachinery. More particularly the invention relates to a rotatable diffuser vane system for turbomachinery.
The use of rotatable diffuser vanes in turbomachinery is well known in the art, but their use has been limited to that of systems using a single row of diffuser vanes. However, for many operations the use of the prior art single row diffuser vane systems has led to a lowered efficiency resulting from losses due to friction, boundary layer separation, vane vibration and surging.
It is the object of the present invention to raise the .efiiciency throughout a wide range of flow and to improve performance by using a novel diffuser vane system which prevents or avoids the difficulties in the prior art.
In accordance with the present invention a turbomachine is provided which comprises a casing having an inlet means and an outlet means therein. An impeller is disposed in the casing between the inlet means and the outlet means. There are a plurality of rotatable members circumferentially spaced in said outlet means. Also at least two rows of radially sapced vanes are disposed in the outlet means with one vane from each of the rows of vanes mounted on each of the members. Means are operatively associated with each of the rotatable members and adapted to rotate the members to maintain the optimum incidence angle of the vanes mounted on the members.
One of the objects of this invention is to minimize the frictional losses by controlling the solidity ratio and aspect ratio of the diffuser vane system.
Another object of this invention is to lower the energy loss by limiting the boundary layer growth of the diffuser vane system.
Another object of this invention is to simplify the mechanical arrangement of the rotatable diffuser vane system.
Another object of this invention is to provide for improved efficiency throughout a wide range of flow by rotatable diffuser vane means.
Another object of this invention is to prevent resonance and excessive vibration of the vane members.
Still another object of this invention is to balance the forces acting on the rotatable diffuser vanes so as to reduce the torque required to rotate the discs the vanes are mounted on.
Still another object of this invention is to eliminate stalling of the fluid flowing in the diffuser vane system thereby preventing surge.
With these and other objects in view, as may appear from the accompanying specification, the invention consists of various features of construction and combination of parts which will be first described in connection with the accompanying drawings, showing a diffuser. vane system of a preferred form and the features forming the invention will be specifically pointed out in the claims.
In the drawings:
FIGURE 1 is a partial section perpendicular to the axis of the impeller and embodying the novel diffuser vane system.
FIGURE 2 is a section taken in the direction of lin 2--2 of FIGURE 1.
FIGURE 3 is a section taken in the 3-3 of FIGURE 2.
direction of line FIGURE 4 is a partial section perpendicular to the axis of the impeller and showing the vane angle changed.
FIGURE 5 is a front view of the turbomachine partly broken away and showing the inlet guide vanes and the novel diffuser vane system.
Referring more particularly to the drawings FIGURE 1 shows a turbomachine 10 in which the novel diffuser vane system 11 is used.
The turbomachine 10 could be any type of pump or compressor, for example, having a driving impeller 12 in a casing 13 and mounted on a shaft 14, the shaft 14 being connected to a suitable source of power (not shown).
The diffuser vane system 11 as shown in FIGURES 1 and 2 is located in the discharge passageway 15 of the casing 13 adjacent the outlet 16 but it is understood that certain applications may warrant the use of this type system in a suitable inlet and it is understood that such a modification is within the scope of this invention as hereinafter described and claimed.
Accordingly the diffuser vane system 11 utilizes vanes 17 and 18 arranged in radially spaced rows, there being shown an inner row of vanes 19 and an outer row of vanes 20 but it is clear that any suitable number of rows of vanes could be used. One vane 17 from the inner row of vanes 19 and one vane 18 from the outer row of vanes 20 is mounted on a plurality of rotatable discs 21 which are disposed in equidistant circumferentially spaced circular recesses 22 in the wall 38 of the passageway 15.
The vanes 17 and 18 are of shorter length than could be used in a single vane row system. This is especially important in considering and designing for each row of vanes the optimum aspect ratio b/a, the solidity ratio a/c, in order to limit boundary layer growth, friction losses, vane vibration and surging; where b is the span of the vane; a is the length of the vane; c is the distance between leading edges of adjacent vanes of the same row. These symbols are shown in FIGURES 1 and 2.
The vanes 17 and 18 are mounted on the outboard side 23 of the discs 21 substantially perpendicular to a line passing through the axis 24 of the impeller 12 and the center 25 of the disc 21 and the vane 17 has its leading edge 26 located substantially on this line. Vane 18 is then positioned, as shown in FIGURE 1, So that the forces acting on vanes 17 and 18 will be balanced about the center 25 of the disc 21 and no resulting moment will be created about shaft 27.
To provide for simultaneous rotation of the discs 21 which in turn will adjust the incidence angle f of the vanes 17 and 18 a clevis 32 is mounted outside the casing 13 on the outer end 33 of each shaft. The clevis 32 is held in position by a locking pin 34.
The discs 21 as shown in FIGURE 1 are marked as at 37 which corresponds to a mark 39 on the wall 38 of the passageway 15 and indicates the normal operative position. This position can be changed as shown in FIGURE 4 by rotating the discs 21 to maintain an optimum incidence angle corresponding to the flow characteristics.
The vanes 17 and 18 are equidistantly circumferentially spaced in their respective rows in the balanced position hereinbefore described. This spacing allows the boundary layers formed on the vanes 17 of the inner row of vanes 19 to be shed between the vanes 18 of the outer row of vanes 20.
The vanes 17 are adjacent the discharge tip 40 of the impeller 12 and therefore in an area in which the fluid flow will have the highest Mach number. Because of this the vanes are designed to be lightly loaded or in other words vanes 17 are of a smaller profile than vanes 18. Also on rotation of discs 21 the leading edge 26 of the vanes 17 describes an arcuate path away from the axis 24 of the impeller 12 as it is located normally at the closest radial distance to the axis 24 of the impeller 12. Thus the vane 17 will not enter an area of higher Mach number than that encountered during normal operation. Further the trailing end 41 of the vanes 17 extend over the side of disc 21 and has an d/e ratio which does not exceed to prevent resonance and consequent high amplitude vibration from developing; where e is vane thickness at the point of extending over the side of disc 21 and d is vane overhang length.
The vanes 18 of the outer row of vanes 29 are designed to be highly loaded as they are in an area of lower Mach number.
The vanes 17 and 18 are fixedly connected to each of the discs 21 substantially parallel to each other in a balance position to facilitate easy rotation of the discs 21 and to prevent creating a moment about the shaft 27. But the angular relationship of vanes 17 and 18 may be varied within 20 from this parallel relationship in order to accommodate a wide range of design conditions.
As the flow characteristics change the discs 21 and correspondingly the fixed vanes 17 and 18 thereon are rotated to adjust the incidence angle f illustrated in FIGURE 4 thus eliminating incidence losses and stalling of the fluid flowing in the diffuser vane system 11 and preventing surge.
This invent-ion permits a greater overall conversion of kinetic energy to pressure energy for a given loading on a single vane row system.
If inlet guide vanes 42 illustrated in FIGURE 5 are used in the inlet 43 it is preferred that they be provided in the same number as that of the discs 21 to prevent development of non-symmetrical flow caused by the wakes from the inlet guide vanes 42 interacting with the vanes 17 and 18. It Will be understood that this invention is not to be limited to the specific construction or arrangement of parts shown, but that they may be widely modified within the invention defined by the claims.
What is claimed is:
l. A turbomachine comprising:
(a) a casing having an inlet means and an outlet means therein,
(b) an impeller disposed in said casing between said inlet means and said outlet means,
(0) a plurality of rotatable members circumferentially spaced in said outlet means,
(d) at least two rows of radially vanes disposed in said outlet means with one vane from each of said rows of vanes mounted on each of said rotatable members,
(e) means operatively associated with each of said rotatable members and adapted to rotate said rotatable members to maintain the optimum incidence angle of said vanes mounted on said rotatable members.
2. The combination claimed in claim 1 wherein the vane from each of said rows of vanes has the cord line thereof forming an angle between 0 and 20 with the plane passing through the axes of said impeller and said rotatable member.
3. The combination claimed in claim 1 wherein the vanes of each of said rows of vanes are mounted on said rotatable members in substantially parallel relationship with each other.
4. The combination claimed in claim 15 wherein each of said vanes of said rows of vanes are mounted on said rotatable member in a normally operative position in a substantially perpendicular relationship with a line passing through the axes of said impeller and said rotatable member and on rotation of said rotatable member the incidence angle of said vanes thereon can be selectively positioned.
5. The combination claimed in claim 1 wherein (a) said first row of vanes closest the discharge tip of said impeller and of substantially smaller profile than the profile of said second row of vanes remote from the discharge tip of said impeller (11) said first row of vanes in a higher Mach number area than said second row of vanes and for a corresponding incidence angle said first row of vanes adapted to the more lightly loaded than said second row of vanes whereby boundry layer growth thereon is reduced.
6. The combination claimed in claim 1 wherein said second row of vanes of a substantially larger profile than the profile of said first row of vanes be said second row of vanes in a lower Mach number area than said first row of vanes and for a corresponding incidence angle said second row of vanes adapted to convert a maximum of the velocity energy of the fluid flowing in the outlet means into pressure energy.
7. The combination claimed in claim 6 wherein:
(a) each of said vanes of said first row of vanes having the leading edge thereof located on the plane passing through the axis of said impeller and said rotatable member in a normally operative position (b) the leading edge of said vanes to prescribe an arcuate path away from the axis of said impeller on rotation of said rotatable member in a direction opposite to the rotational direction of said impeller to prevent the leading edge of said vane from getting closer to the discharge tip of said impeller and thereby entering a higher Mach number area of fluid flow.
8. The combination claimed in claim 7 wherein (a) each of said vanes of said second row of vanes disposed on said rotatable member in normal operative position a greater radial distance from the axis of said impeller than the radial distance of each of said vanes of said first row of vanes (b) the leading edge of each of said vanes of each row of vanes facing the direction of rotation of said impeller (c) the leading edge of said vanes of said second row of vanes to extend over the side of said rotatable member whereby the weight of said vanes of said first row of vanes will not impinge on said vanes of said second row of vanes.
9. A turbo machine comprising (a) a casing having an inlet means and an outlet means therein (b) said outlet means including an annular passageway means in said casing (c) an impeller in said casing between said inlet means and said passageway means (a') said passageway means having a plurality of circular recesses equal distantly spaced in circumferencial relationship to each other (e) each of said recesses having a bore therethrough (f) a disc member disposed in said recess and having a shaft connected to the inward side thereof to extend through the bore in said recess (g) means connecting each of said shafts and adapted to rotate each of said shafts thereby rotating said discs (h) an inner row of vanes and an outer row of vanes radially spaced from the axis of said impeller and one vane from each of said rows of vanes mounted on each of said discs (1') each of said vanes of said inner row of vanes having the leading edge thereof located on the plane passing through the center of said disc and the axis of said impeller in a normally operative position and on rotation of said disc in the direction opposite to the rotational direction of said impeller the leading edge of said vane will describe an arcuate path away from the axis of said impeller to prevent the leading edge from entering a higher Mach number area of fluid flow nearer the discharge tip of said impeller.
10. The combination claimed in claim 9 wherein (a) said inner row of vanes closer to the axis of said impeller and of a substantially smaller profile than said outer row of vanes (b) said inner row of vanes in a higher Mach number area of flow than said outer row of vanes and for a corresponding incidence angle each vane of said inner row of vanes is so constructed and arranged that they can be lightly loaded to reduce boundary layer growth thereon while each vane of said outer row of vanes is so constructed and arranged that they can convert a maximum of velocity energy of the fluid flowing in the outlet means into pressure energy.
11. The combination claimed in claim 10 wherein:
(a) each of said vanes in said inner row of vanes has a trailing end extending over the side of said disc (b) said trailing end of said vanes has a ratio of the total extension to the thickness at the point of extending over the side of said disc not to exceed 5 to prevent high amplitude vibration and resonance.
12. The combination claimed in claim 11 wherein (a) each of said discs having said vane of said outer row of vanes normally mounted on the half of said disc above and a predetermined distance from the center thereof (b) each of said discs having said vane of said inner row of vanes normally mounted on the half of said discs below the center thereof a suflicient distance therefrom to create a substantially equal amount acting about the center of said disc for corresponding incidence angles to permit easy rotation of said discs.
13. The combination claimed in claim 12 wherein:
(a) each of said discs having said vane of said inner row of vanes normally mounted on the half of said disc below the center thereof adjacent the discharge tip of said impeller,
(b) each of said discs having said vane of said outer row of vanes normally mounted on the half of said disc above the center thereof remote from the discharge tip of said impeller,
() each of said discs having said vanes from said inner row of vanes and said outer row of vanes mounted thereon in a normally operative position in substantially perpendicular relationship with a line passing through the axis of said impeller and the center of said disc whereby said vanes act to diffuse the fluid flowing in said passageway means.
14. The combination claimed in claim 13 wherein:
(a) each of said discs adapted to be rotated simultaneously by said means operatively associated therewith to maintain the optimum incidence angle of said vanes mounted substantially parallel thereon whereby the diifuser vane efficiency can be maintained over a Wide range of flow.
15. A turbomachine comprising:
(a) a'casing having an inlet means and an outlet means therein,
(12) said outlet means including an annular passageway means in said casing,
(c) an impeller disposed in said casing between said inlet means and said passageway means,
(d) a plurality of discs disposed in said passageway means with substantially equidistant circumferential relationship therebetween and adapted to be rotated,
(e) each of said discs having a pair of radially spaced substantially parallel vanes mounted thereon,
(1) said pairs of vanes extending substantially the full width of said passageway means,
(g) the inner vane is closer to the axis of said impeller and of substantially smaller profile than the outer vane,
(h) said inner vane and said outer vane to coact to diffuse the fluid flowing in said passageway means whereby the velocity energy of the fluid can be converted to pressure energy,
(1) means interconnected between each of said discs to rotate said discs whereby the incidence angle of said pairs of vanes can be changed to obtain diffusion corresponding with the fluid flow conditions.
16. The combination claimed in claim 15 wherein:
(a) guide vanes are disposed in said inlet means,
(b) said guide vanes of the inlet means and said pairs of vanes of said passageway means of equal number to prevent non-symmetry of flow in said outlet means caused by guide vane wakes interacting in the passageway means.
References Cited in the file of this patent FOREIGN PATENTS 158,915 Switzerland Feb. 16, 1933 294,452 Switzerland Jan. 16, 1954 911,839 Germany May 20, 1954-
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US152301A US3069070A (en) | 1961-11-14 | 1961-11-14 | Diffuser vane system for turbomachinery |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US152301A US3069070A (en) | 1961-11-14 | 1961-11-14 | Diffuser vane system for turbomachinery |
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| US3069070A true US3069070A (en) | 1962-12-18 |
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| US152301A Expired - Lifetime US3069070A (en) | 1961-11-14 | 1961-11-14 | Diffuser vane system for turbomachinery |
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Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3861826A (en) * | 1972-08-14 | 1975-01-21 | Caterpillar Tractor Co | Cascade diffuser having thin, straight vanes |
| US4094631A (en) * | 1976-01-15 | 1978-06-13 | Grieve Douglas V | Multiple outlet blower scroll for an industrial oven |
| US4642026A (en) * | 1983-07-26 | 1987-02-10 | Ruff John D | Centrifugal compressor with adjustable diffuser |
| US4685869A (en) * | 1984-10-04 | 1987-08-11 | Toyota Jidosha Kabushiki Kaisha | Device for supporting nozzle vanes of a turbocharger |
| US4824325A (en) * | 1988-02-08 | 1989-04-25 | Dresser-Rand Company | Diffuser having split tandem low solidity vanes |
| US4836747A (en) * | 1987-07-06 | 1989-06-06 | Aktiengesellschaft Kuehnle, Kopp & Kausch | Adjusting device for a compressor |
| US4850795A (en) * | 1988-02-08 | 1989-07-25 | Dresser-Rand Company | Diffuser having ribbed vanes followed by full vanes |
| EP0378343A1 (en) * | 1989-01-10 | 1990-07-18 | Ishikawajima-Harima Jukogyo Kabushiki Kaisha | Variable geometry turbochargers |
| US5207559A (en) * | 1991-07-25 | 1993-05-04 | Allied-Signal Inc. | Variable geometry diffuser assembly |
| US5316441A (en) * | 1993-02-03 | 1994-05-31 | Dresser-Rand Company | Multi-row rib diffuser |
| US5342168A (en) * | 1992-07-30 | 1994-08-30 | Mtu Motoren- Und Turbinen-Union Gmbh | Adjustable radial-flow diffuser |
| US5498128A (en) * | 1993-03-25 | 1996-03-12 | Abb Management Ag | Radial-flow exhaust gas turbocharger turbine with adjustable guide vanes |
| US5518365A (en) * | 1993-03-25 | 1996-05-21 | Abb Management Ag | Radial-flow exhaust gas turbocharger turbine with adjustable guide vanes |
| US20070068303A1 (en) * | 2005-08-30 | 2007-03-29 | Snecma | Link device of controllable variable length |
| US20090208331A1 (en) * | 2008-02-20 | 2009-08-20 | Haley Paul F | Centrifugal compressor assembly and method |
| US20100124487A1 (en) * | 2008-11-19 | 2010-05-20 | Rolls-Royce Deutschland Ltd & Co Kg | Multi-vane variable stator unit of a fluid flow machine |
| EP2071134A3 (en) * | 2007-12-13 | 2010-10-27 | Bosch Mahle Turbo Systems GmbH & Co. KG | Turbine with variable geometry |
| CN102261344A (en) * | 2011-08-31 | 2011-11-30 | 无锡杰尔压缩机有限公司 | Synchronous regulating device of high-speed centrifugal fan outlet guide vane |
| US20130034425A1 (en) * | 2010-04-14 | 2013-02-07 | Turbomeca | Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same |
| EP2397652A3 (en) * | 2010-06-20 | 2014-12-17 | Honeywell International Inc. | Multiple airfoil vane for a turbocharger |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH158915A (en) * | 1931-10-13 | 1932-12-15 | Theodor Bell & Cie Ag | Hydraulic machine system with open or closed chamber. |
| CH294452A (en) * | 1942-05-26 | 1953-11-15 | Daimler Benz Ag | Charging fans for internal combustion engines, in particular aircraft engines. |
| DE911839C (en) * | 1945-04-17 | 1954-05-20 | Charmilles Sa Ateliers | Rotating machine for fluids working as a motor or generator |
-
1961
- 1961-11-14 US US152301A patent/US3069070A/en not_active Expired - Lifetime
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH158915A (en) * | 1931-10-13 | 1932-12-15 | Theodor Bell & Cie Ag | Hydraulic machine system with open or closed chamber. |
| CH294452A (en) * | 1942-05-26 | 1953-11-15 | Daimler Benz Ag | Charging fans for internal combustion engines, in particular aircraft engines. |
| DE911839C (en) * | 1945-04-17 | 1954-05-20 | Charmilles Sa Ateliers | Rotating machine for fluids working as a motor or generator |
Cited By (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3861826A (en) * | 1972-08-14 | 1975-01-21 | Caterpillar Tractor Co | Cascade diffuser having thin, straight vanes |
| US4094631A (en) * | 1976-01-15 | 1978-06-13 | Grieve Douglas V | Multiple outlet blower scroll for an industrial oven |
| US4642026A (en) * | 1983-07-26 | 1987-02-10 | Ruff John D | Centrifugal compressor with adjustable diffuser |
| US4685869A (en) * | 1984-10-04 | 1987-08-11 | Toyota Jidosha Kabushiki Kaisha | Device for supporting nozzle vanes of a turbocharger |
| US4836747A (en) * | 1987-07-06 | 1989-06-06 | Aktiengesellschaft Kuehnle, Kopp & Kausch | Adjusting device for a compressor |
| US4824325A (en) * | 1988-02-08 | 1989-04-25 | Dresser-Rand Company | Diffuser having split tandem low solidity vanes |
| US4850795A (en) * | 1988-02-08 | 1989-07-25 | Dresser-Rand Company | Diffuser having ribbed vanes followed by full vanes |
| EP0378343A1 (en) * | 1989-01-10 | 1990-07-18 | Ishikawajima-Harima Jukogyo Kabushiki Kaisha | Variable geometry turbochargers |
| US5028208A (en) * | 1989-01-10 | 1991-07-02 | Ishikawajima-Harima Jukogyo Kabushiki Kaisha | Nozzle blade angle adjustment device for variable geometry turbocharger |
| US5207559A (en) * | 1991-07-25 | 1993-05-04 | Allied-Signal Inc. | Variable geometry diffuser assembly |
| US5342168A (en) * | 1992-07-30 | 1994-08-30 | Mtu Motoren- Und Turbinen-Union Gmbh | Adjustable radial-flow diffuser |
| US5316441A (en) * | 1993-02-03 | 1994-05-31 | Dresser-Rand Company | Multi-row rib diffuser |
| US5498128A (en) * | 1993-03-25 | 1996-03-12 | Abb Management Ag | Radial-flow exhaust gas turbocharger turbine with adjustable guide vanes |
| US5518365A (en) * | 1993-03-25 | 1996-05-21 | Abb Management Ag | Radial-flow exhaust gas turbocharger turbine with adjustable guide vanes |
| US20070068303A1 (en) * | 2005-08-30 | 2007-03-29 | Snecma | Link device of controllable variable length |
| US7802964B2 (en) * | 2005-08-30 | 2010-09-28 | Snecma | Link device of controllable variable length |
| EP2071134A3 (en) * | 2007-12-13 | 2010-10-27 | Bosch Mahle Turbo Systems GmbH & Co. KG | Turbine with variable geometry |
| US20090208331A1 (en) * | 2008-02-20 | 2009-08-20 | Haley Paul F | Centrifugal compressor assembly and method |
| US9353765B2 (en) | 2008-02-20 | 2016-05-31 | Trane International Inc. | Centrifugal compressor assembly and method |
| US8672618B2 (en) * | 2008-11-19 | 2014-03-18 | Rolls-Royce Deutschland Ltd & Co Kg | Multi-vane variable stator unit of a fluid flow machine |
| EP2189664A3 (en) * | 2008-11-19 | 2015-11-04 | Rolls-Royce Deutschland Ltd & Co KG | Multivane variable stator arrangement for turbomachine |
| US20100124487A1 (en) * | 2008-11-19 | 2010-05-20 | Rolls-Royce Deutschland Ltd & Co Kg | Multi-vane variable stator unit of a fluid flow machine |
| US20130034425A1 (en) * | 2010-04-14 | 2013-02-07 | Turbomeca | Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same |
| EP2397652A3 (en) * | 2010-06-20 | 2014-12-17 | Honeywell International Inc. | Multiple airfoil vane for a turbocharger |
| CN102261344B (en) * | 2011-08-31 | 2013-12-04 | 无锡杰尔压缩机有限公司 | Synchronous regulating device of high-speed centrifugal fan outlet guide vane |
| CN102261344A (en) * | 2011-08-31 | 2011-11-30 | 无锡杰尔压缩机有限公司 | Synchronous regulating device of high-speed centrifugal fan outlet guide vane |
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