US1931692A - Centrifugal blowing apparatus - Google Patents

Centrifugal blowing apparatus Download PDF

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US1931692A
US1931692A US428698A US42869830A US1931692A US 1931692 A US1931692 A US 1931692A US 428698 A US428698 A US 428698A US 42869830 A US42869830 A US 42869830A US 1931692 A US1931692 A US 1931692A
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impeller
air
vanes
vane
blades
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US428698A
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Paul E Good
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Elliott Co
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Elliott Co
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/42Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/02Selection of particular materials
    • F04D29/023Selection of particular materials especially adapted for elastic fluid pumps
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/26Rotors specially for elastic fluids
    • F04D29/28Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F04D29/285Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors the compressor wheel comprising a pair of rotatable bladed hub portions axially aligned and clamped together
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/42Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44Fluid-guiding means, e.g. diffusers
    • F04D29/441Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F04D29/444Bladed diffusers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/60Mounting; Assembling; Disassembling
    • F04D29/62Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
    • F04D29/624Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00Geometry
    • F05D2250/50Inlet or outlet
    • F05D2250/51Inlet
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00Geometry
    • F05D2250/70Shape

Description

Oct. 24, 1933. P. E. GOOD 1,931,692
cnu'mwum. BLdwme APPARATUS Filed Feb. 15. 1930 e Sheets-Shee t 1 Oct. 24,1933. I I P. E. GOOD 1,931,692
I CENTRIFUGAL BLOWING APPARATUS Fil ed Feb 15. 1930 6 Sheets-Sheet 2 I INVENTOR g I w 9st. 24 1933. P. E. GOOD 2 CENTRIFUGAL BLOWING APPARATUS I F iled Feb. 15. 19 30 e She ets-Sheet 3 Oct. 24, 1933. I P. a. GOOD 1,931,692
' .cENTRIF GAL BLOWING APPARATUS Filed Feb. 15, 1930 6 Sheets-Sheet 4 I 58 1mm: 5/2.
INVENTOR Md? f A m;
ct. 1933. 5 D 1,931,692
CENTRIIEUGA L BLOWING APPARATUS I Filed Feb. 15, 19 30 6 ShGGtS-ShGQt 5 flasmur: PAT/4 0/ EA! TERI/VG All? 'REL/VTVE T0 IMPELlER BLADE.
Z49 /MPEL L ER.
INVENTOR Oct. 2-4, 1933. P. EGOOD 1,931,692 I I-CENTRIFUGAL BLOWING APPARATUS Filed Fb. 15', 1930 e Sheets-Sheet 6 INVENTOR Patented Oct. 24, 1933 PATENT OFFICE 1,931,692 CENTRIFUGAL BLOWING APPARATUS Paul E. Good, River-ton, N. 1., assignor to Elliott Company, Pittsburgh, 11's., a corporation of Pennsylvania Application February 15, mo. Serial No. asses 15 Claims.
The present invention relates broadly to the art of fluid pressure apparatus and more particularly to a compressor of the type commonly referred to sea centrifugal blower, and utilized for compressing air and gases. In addition to improvements in the. constructional characteristics of such apparatus, the present invention contemplates The invention is embodied in a novel coordination of these various elements, and more particularly the impeller and vanes as well as in certain novel features of construction of the respective parts and the method of determining their proper contour or configuration.
The vane structure is so positioned as to produce a more or less axially directed flow of the fluid to be compressed into the impeller, the characteristics of the impeller and vanes'being such as to produce the desired engaging action with a minimum shock, as between the entering air and the impeller. 39 In the accompanying drawings, I have shown for purposes of illustration only, certain preferred embodiments of the present invention.
In the drawings:
Figure l is an exploded perspective view illustrating the snail housing with an inlet casin and vane structure on one side and a portion of the impeller shaft housing on the opposite side, the impeller being removed for sake of cleamess;
Figure .2 is a front elevational view of the impeller;
Figure 3 is a transverse sectional view on the line 111-411 of Figure 2;
Figure 4 is a view similarto Figure 3 illustrating the relationship of the varies and impeller;
Figures 5, 6, '7, 8 and 9' are transverse sectional views on the lines V-V, VI- VI, VII-VII, VIiL-VIII, and IX-IX of Figure 4, these views being more or less diagrammatic and having vector diagrams superimposed thereon;
Figure 10 is a transverse sectional view on the line X-X of Figure 4;
Figure 11 is an end elevational view of one of the blades; a
Figure 12 is a view similar to Figure 4 illustrating a modified embodiment of the invention;
particularly in Figures 4 and 14 of the drawings.
Figure'iiiisaviewsimilartoFigumEbut taken on the lin'eXIII-XIII of Figure12;
Figure 14 is a perspective view of the vane structure; and v Figure 15 is a 0 detail view illusv trating the manner of forming the individual Having reference more particularly to Figure 1 of the drawings, a blowing apparatus constructed in accordance with the present invention includes 5" a snail housing 2 with one side of which cooperates an inlet casing 3, within which is carried a vane assembly 4. Cooperating with the opposite side of the housing 2 is a-bearlng 5 for an impeller shaft 6 adapted to receive an impeller 7, as illustrated in detail in Figures 2 and 3. Usually the bearing end 5 of the houslng2 will be the housing which contain the turbine or motor utilized for driving the impeller, andthe bearings thereof will support the impeller shaft 6.
with the parts in led position, the ends 'I' of the impeller blades 8 will rotate substantially in the plane of the inwardly directed opening 9, which opening in turn communicates with the dischargeoutlet 10.
Upon rotation of the impeller in the direction indicated in the drawings, air or other fluid being compressed will be drawn axially thereinto, as represented by the arrows A in Figure 4, these arrows being intended to illustrate direction of fluid flow and not relative distribution thereof.
As an actual matter of fact, the velocity of air over the entire area of the inlet casing 3 will not be constant. Since the lowest absolute pressure will exist nearest the hub of the impeller and the highest absolute pressure nearest the point of discharge of the impeller blades, there will be a varying pressure difierential effective over the entrance to the inlet casing, which diflerential will be such as to produce the highest velocity of entering air adjacent the center of the casin8..with a gradually decreasing velocity outwardly therefrom. The fluid received by the impeller will first have been caused to pass axially through the inlet casing 3 wherein it will have been acted upon by the vanes 11 .carried thereby. These vanes at their inner ends may cooperate with an inner ring 12 and at their outer ends with a similar ring 13 of larger diameter, the outer diameter of the ring 13 being substantially equal to the inner diameter of the casing 3 whereby the vane assembly may be axially inserted into or removed from the inlet casing. This construction is illustrated more no In Figure 15 there is illustrated more or less diagrammatically, one manner in which the individual vanes 11 may be considered as having been formed. In this figure, there is illustrated a substantially cylindrical section 11 of any metal having the desired thickness for the construction therefrom of individual vanes. This cylinder, having a substantially uniform radius of curvature as to all of its wall parts, is subject to comparatively easy manufacture. In actual practice it may be formed either as a complete cylinder, such as illustrated in Figure 15, or as the are of a cylinder, as will be apparent.
Having provided the desired parent body of stock curved in the manner referred to, it may be considered as having been intersected by a plane P parallel to and including the axis of the cylinder. This plane P will obviously be substantially normal to a plane tangent to the cylindrical envelope 11 at the point of intersection between the plane and the envelope. This line of intersection is indicated by the line p-p in Figure 15, which line determines one edge of the entrance vane. This being a straight line, all points in this edge of the vane will provide a constant entrance angle. Thereafter, points p, p and 12 will be laid ofi along the surface of the cylinder, which points are sufficient for the determination of a second oblique plane P. This plane will intersect the surface of the envelope along the line p, p and p and will define the opposite edge of the vane 11. Since all points in the edge defined by the oblique plane P are at a varying distance from the edge determined by the plane P, the side of the vane 11 determined by the oblique plane will provide discharge angles which constantly vary throughout the length of the vane.
After the desired number of vanes has been formed in this manner, they may be secured'in positionintermediate rings 12 and 13in any desired manner, such as by welding the respective ends of the vanes to the respective rings. 1
From an inspection more particularly of Figur'es 5 to 9, both inclusive, the relationship of the vanes 11 to the inner and outer rings 12 and 13 will be more clearlyapparent, Figures 5 to 9 rep resenting respectively successive sections from the central portion of the apparatus outwardly along the section lines of Figure 4 correspondingly designed. Not only do these figures illustrate the angular relationship of the vanes, but they disclose the relative relationships of the vanes and the impeller at different positions.
Due to the general construction before referred to, the vanes will povide constant entrance angles to the air passing through the vane assembly. These entrance angles E E E, E and E are designated in Figures 5 to 9, respectively. Each of these angles is approximately 90.
While the vane assembly presents entrance angles of constant characteristics, they present discharge angles of varying characteristics, these angles being designated respectively D D, D", D and D in the figures under consideration. It will be noted that thesedischarge angles become progressively more and more acute from the inner to the outer ends of the vanes. By way of illustration only, and in order to afford a better understanding of the invention, without in any wise limiting the same to any specific dimensions, applicant has applied to each of the discharge angles the corresponding value in degrees.
With theapparatus in operation, air is caused to enter the vane assembly in a direction which may be diagrammatically represented by the arrows B in Figures 5 to 9. This air, acted upon by the vanes and under characteristic conditions which will be hereinafter more fully referred to, may be considered as discharged from the vanes in the direction indicated by the arrows C C, C", C and C in Figures 5 to 9, both inclusive, thedirection of these arrows varying with the variation in the corresponding discharge angles of the vanes.
. As is also illustrated by the figures under consideration, the vane assembly and the impeller blades are relatively so disposed as to provide an axial space S between the same, the characteristics of which will be hereinafter more fully set forth. In operation, it will be apparent that all portions of the impeller rotate in the same direction, but at speeds increasing in accordance with ,the distance of any given part from the axis of "rotation; If the speed of rotation is known, it is possible to. determine the actual velocity of any portion of the impeller structure.
In order to provide an eflicient operating construction, it is desirable that the air enter the impeller in a direction substantially parallel to the blades in such manner that the air may be received by the blades without any substantial shock. Such a construction is obtained in accordance with the present invention by utilizing an impeller blade of novel characteristics, deter mined to a large extent by the characteristics of the'vanes 11. This may be best explained by the use of vector diagrams, which for purposes of a better understanding of the invention, have been incorporated in Figures 5 to 9. In all of these figures, the direction of rotation of the impeller being the same, but the velocity of different portions varying in accordance with the radial distance of such portions from the axis of rotation, the lines designated impeller velocity all extend in the same direction but are of different lengths, the lengths being indicative of the diameter at which the section is taken and therefore of the actual velocity. .Each of the impeller velocity vectors has applied thereto a numerical value, actually determined for a particular installation and applied by way of illustration only.
Cooperating with the impeller velocity vectors and extending at an angle thereto in the respective figures corresponding to the discharge angles, are air inlet velocity vectors which have heretofore been designated C to C both inclusive. The direction of these vectors is determined by the discharge angle of the corresponding portion of the vane 11, while the length is a matter of experience. With an impeller having radial blades of the properly curved section to eliminate shock at the inlet, the velocity of the entering air becomes substantially uniform over the entire inlet area of the wheel itself. Experience dictates the possibility of utilizing a constant value of the absolute inlet velocity at all radii. This is herein illustrated as being 180.feet per second, this figure being utilized for purposes of illustration only, and represents the velocity intermediate the vanes and the impeller.
From the impeller velocity vector and the air inlet velocity vector, there is obtained a third line, designated, respectively, P P, P", P and P in the respective figures, and representing the absolute path of entering air relative to the impeller blade. sive, which principally determine the contour characteristics of any given portion of an impeller blade. This is true for the reason, as be It is the lines P to P both inclufore stated, that it is desirable to have the air enter the impeller in a direction substantially parallel thereto.
By way of concrete illustration, reference will be had to Figure 9, in which the impeller velocity vector has a length corresponding to 340, and in which the air inlet velocity vector has a length corresponding to 180, the included angle between these vectors being 35 degrees, which corresponds to the discharge angle D". From these two vectors there is determined the line P hereinbefore designated as the absolute path of the entering air relative to the impeller blade. This line, cooperating with the impeller velocity vector, includes an angle of 29 degrees, as indicated. The contour of the blade section is thus determined, and this section is illustrated in full lines in Figure 9. For more clearly illustrating the relationship, a portion of the blade contour is applied in dotted lines to the vector diagram.
This same procedure is followed in connection with each section of the vane and impeller, and provides a definite basis for a determination of .the impeller blade contour. Inasmuch as the respective vector diagrams of Figures 5 to 9 provide absolute paths of entering air, P to P, both inclusive, which swing from a position on one side of a perpendicular through the perpendicular into position on the opposite side, the impeller blades have edge portions which correspondingly extend from a position rearwardly of a plane including the axis of rotation to a position forwardly of such plane, as will be apparent from the drawings.
There is thus provided an impeller blade construction every portion of which effectively cooperates with the air as received from the vane and gives to this air the rotational or centrifugal velocity desired for expelling it through the outlet 10 of the snail housing 2.
For stiffening purposes, each of the impeller blades is preferably provided with a back .rib 14, extending from the hub of the impeller to the ou er end of the blade. For more effectively receiving the air from the vane assembly and holding it within the path ofthe impeller, the baldes are of curved contour beyond thesection lines 1X1X of Figure 4, as apparent more particularly from Figures 10 and 11. This curvature is preferably constant or substantiallyv constant from the plane of the section IX-IX outwardly inasmuch as the primary function of these portions is to impart the desired centrifugal velocity to the air which has previously been received from the vane assembly.
It will be apparent from the foregoing descrip tion that the impeller is of the open or unshrouded type, and that the blades extend primarily in a substantially truly radial direction,
the cross sectional contour given to the blades varied in different sections in accordance with the absolute paths of the entering air, as before described. It will therefore be apparent that the cross sectional contour given to the blades is for the purpose of bettering the entrance conditions of the air into the impeller.
From the standpoint of rotation of the air as imparted to it by the rotating impeller, the effect, therefore, is substantially the same as if the impeller were composed of plain radial surfaces. Inasmuch as the actual cross sectional contour of the impeller blades at any" given point compared to other points, does not depart uniformly or progressively from corresponding sections radially displaced therefrom, it is obvious that the actual contour is not a function of geometry determined from the impeller alone, but is a function of the conditions before referred to as established in large part at least by the vane assembly construction, and therefore constitutes an improved method of determining impeller blade characteristics.
While reference has heretofore not been made to the fact, it will be apparent to those skilled in the art that the vane construction described provides within the inner ring 12, an eye 15, which is unobstructed.
From the standpoint of ablowing apparatus, the present application embodies desirable features; first, in the combination of a stationary vane structure to direct air into an impeller in which there is axial flow into the impeller and radial flow outwardly therefrom. It likewise presents a novel advance in the art with respect to the characteristics of the vane structure, as well as with respect to the characteristics of the impeller, and more especially in the use of an im- .peller having a, blade section such that the air enters the same substantially parallel thereto and without any appreciable shock.
From a manufacturing consideration, advantages arise from the use of a vane structure in which all portions have a given radius of curvature. inasmuch as the production of such a vane is facilitated.
Further advantages arise from the combination of vanes 'which may be considered as composed of sections of the surface of a cylinder formed between a plane parallel to and including the axis of the cylinder and an oblique plane intersecting the cylindrical surface, the plane of obliquity being so determined that air will be received and delivered to the rotating impeller in a coordinated functional relationship to the blade angles of the impeller.
Reference has heretofore been made to the space S intermediate the vane structure and the runner or impeller. In view of the importance of this space in actual practice, reference will be made to it, and more particularly to its cooperating characteristics to the open eye 15 in the vane structure. At the outset it may be stated that the open hole 15 is desirable from the standpoint of its ability to handle comparatively large volumes of airwithout the friction lossesm incident to the use of vanes. It may be considered that there is an annulus of air flow through the vanes 11 of the vane structure upon which the vanes confer a directed, rotative velocity proceeding through the eye of the impeller in the form of a spiral; i. e., rotation and definite progression. All portions of this have been considered as travelling at the same definite velocity, namely, 180 feet per second. In addition to this annulus, there is also an inner core of air through the eye 15 travelling at high velocity.
The velocity is different for the reason that the vanes have not reacted upon it. This being true, the velocity in the space S may be considered as a mixed or resolved velocity determined by the air through the annulus and the air through the hole. It is, of course, a fact that a zone of air travelling into a space under velocity will penetrate further without disintegration if the swirl is lower. In other words, if there were no swirl through the hole 15, the jet or none of air produced thereby would penetrate further into the space S without losing its identity.
The resolved or mixed velocity in the space S, as before referred to, is progressive radially out- 'pendicular, benefit is gained.
ward from the shaft. This being true, it is possible both from experience and theory to modi= fy the exit angles D to D on the vane structure to take account of this modification of velocity and to arrive at a resultant direction and modifled magnitude of velocity in the vector diagram so that the rotor will pick up the air with less shock. In other words, the cooperation between the hole and stationary vanes produces a result in direction and magnitude of entering velocity so that'the rotor shape may be simplified and the entrance angles of the blades become more nearly straight lines, as will be apparent more particularly from Figure 13, in which the vector diagram corresponding to Figure 5 is illustrated in dotted lines and the vector diagram for the construction of Figure 13 illustrated in full lines.
It will be apparent to those skilled in the art that if the vectors if to P both inclusive, could be perpendicular to the vector indicating impeller velocity, there would be no need of curving the blades of the impeller. Obviously, therefore, as the direction and magnitude of the air inlet velocity is modified in direction and magnitude to make the absolute velocity vector per- It is to be observed, however, as will be apparent by reference to Figures 5 to 9, both inclusive, that the vector indicating absolute path of entering air without any modifying influenceswings through.
the perpendicular. Therefore, an attempt to modify vector relationship if continued far enough would actually become objectionable and constitute a correction in a wrong direction.
Having this thought in mind, there is incorporated in the space S of Figure 12, which space obviously corresponds to the space S of Figure 4., a dividing partition 16 in the form of a cylindrical body concentrically disposed with respect to the axis of rotation of the impeller. This partition has for its object to limit the effect of the combination of velocities referred to, to a useful zone whereby an objectionablecorrection of the character referred to will not be necessary. Such a partition obviously divides the space S into two more or concentrically disposed spanes such that the modifying influence of one of these spaces on the other is substantially eliminated.
With a construction embodying such a partition, there may be obtained a situation such as illustrated diagrammatically in Figure 13. in this figure, the vector indicating impeller velocity is of the same extent and direction as that shown in Figure 5. The location of the vane 11', however, has been changed so that instead of providing a discharge angle of 53 degrees, as shown in Figure 5, there is provided a discharge angle of substantially 57 /2 degrees. This, in turn, determines a vector p, which more nearly approaches the perpendicular than the vector]? by an amount represented by.the difference between the dotted vector line for absolute path of entering air and'the solid vector line indicating the same value. This makes it possible for the blade 8' of the impeller to have its impact or air receiving 0 more nearly appro hing a straight line. In this figure, the dotted lines indicate the positions of the parts as indicated in Fie 5 for a structure in which thepartition 16 is not utilized, while the full lines indicate the changed position of the parts where advantage is taken of such a partition. This vchange in the direction of the entering air is made possible by reason of the fact that the influence of the outer envelope of air on the inner memos Instead of utilizing an impeller as before dev scribed, the impeller may be modified as illustrated in Figure 12, by applying thereto a sepa rate nose piece 1'? or by extending the impeller in an axial direction so as to provide a modified contour similar to that which is provided by the addition of the nose piece. This modification is made in order to take advantage of the tendency of air having a lesser swirl to travel more nearly intact through a given space. The nose piece or addition to the impeller constitutes in effect a flow directing device in almost'identical or similar manner that the stationary vanes are flow directing devices,. and its function is to definitely control the outward flow of the central core or zone of air coming through the hole or eye 15. In other words, if the air coming through this hole does not dissipate outward into the wheel and mix with the air coming through the stationary vanes, the function of the nose piece continuation thereof.
From a manufacturing standpoint, the use of a separate nose piece is desirable, although from an operating standpoint the characteristics of a separate and integral structure are substantially the same. It will hereinafter be referred to, regardless of whether separable or integral, a a flow directing addition to the impeller.
,It will thus be found that the structure of Figure 12 provides the combination with a rotating impeller having a curved blade adapted to'receive air without shock in an axial direction, the absence of shock resulting from the cooperation of a stationary structure adapted to receive in a curved vane, an outer annulus of air and to give it a velocitydirection modification and having an open central hole, together with the space between the rotor and the stationary vane structure adapted to receive an annulus and core of air, and to so combine them as to secure a favorable resultant velocity relative to the impeller prior to its entering the blades thereof.
The present invention embodies advantages in the respects referred to both from the standpoint of structure involved, and from the method of determining the structural relationship of the parts.
While I have herein illustrated and described certain preferred embodiments of the present invention,'it will be understood from such description that changes in the construction and relationship of the parts may be made without departing either from the spirit of the invention or the scope of my broader claims.
I claim:--
1. A bio apparatus, comprising in combination a casing, an impeller'rotatable therein, and a vane structure comprising vanes of uniform curvature but gradually increasing in width outrality or blades having-a contour determined by I the. characteristics of the vane structure for receiving entering air therefrom substantially parallel to the blade faces. 7
2. The combination in a blowing apparatus, of
a vane structure and impeller, having an axial space therebetween and in which the vane structure includes an open substantially centrally located eye, of means in said space for dividing it into inner and outer zones.
3. A blowing apparatus having an axial inlet and a radial outlet, comprising a casing, an open impeller rotatable therein, and a vane structure cooperating with said impeller for directing air into the impeller, said vane structure comprising vanes providing a discharge angle progressively increasing relative to the impeller axis in a direction radially of the impeller, and the blades of said impeller having air receiving portions of progressively increasing angularity from the center of the impeller toward the periphery thereof throughout the air receiving portion of the impeller.
4. A blowing apparatus having an axial inlet and a radial outlet, comprising a casing, an open impeller rotatable therein, and a vane structure cooperating with said impeller for directing air into the impeller, said vane structure comprising vanes providing a discharge angle progressively increasing relative to the impeller axis in a direction radiallyof the impeller, and the blades of said impeller having air receiving portions of progressively increasing angularity from the center of the impeller toward the periphery thereof throughout the airreceiving portion of the impeller, said vanes being of uniform curvature but gradually increasing width from the inner toward the outer ends thereof.
5. A blowing apparatus having an axial inlet and a radial outlet,-comprising a casing, an open impeller rotatable therein, and a vane structure cooperating with said impeller for directing air into the impeller, said vane structure comprising vanes providing a discharge angle progressively increasing relative to the impeller axis in a direction radially of the impeller, and the blades of said impeller having air receiving portions of progressively increasing angularity from the center of the impeller toward the periphery thereof throughout the air receiving portion of the impeller, said vanes having outer substantially straight air receiving edges and outwardly diverging air discharge edges and having a substantially uniform radius of curvature from one end to the other. a
6. A blowing apparatus having an axial inlet and a radial outlet, comprising a casing, an open impeller rotatable therein, and a vane structure.
cooperating with said impeller for directing air into the impeller, said vane structure comprising vanes providing a discharge angle progressively increasing relative to the impeller axis in a direction radially of the impeller, and the blades of said impeller having air receiving portions of progressively increasing angularity from the center of the impeller toward the periphery thereof throughout the air receiving portion of the impeller, said vanes being shaped to provide a substantially constant angle for the entering air throughout the length of the vanes with a discharge angle of progressively increasing acuteness from the inner toward the outer ends of the blades.
7. Allowing apparatus having an axial inlet and a radial outlet, comprising, in combination, an impeller having blades of changing cross section throughout a portion of the length thereof, and a guide vane structure for directing air into said impeller, said guide vane structure including vanes providing a varying air discharge angle a radial outlet, comprising, in combination, an
blades having curved air receiving portions.
from the inner to the outer ends thereof, the variation in the cross section of said blades being proportionate to the variation in the air discharge angle of said vanes.
8. Blowing apparatus, having an axial inlet and a radial outlet, comprising, in combination, an impeller having a plurality of blades of gradually increasing curvature in cross section from their inner portions to their outer portions throughout a substantial part of their length, and a vane structure including a plurality of vanes for directing air to said impeller, said vanes being of substantially uniformly curved cross section throughout substantially the entire length thereof and so disposed as to provide discharge angles varying throughout the length of each vane in accordance with the varying cross sec- ,tion of the impeller blades.
9. Blowing apparatus, having an axial inlet and 96 open impeller having a plurality of blades providing curved air receiving portions, and a vane structure including a plurality of vanes, said vanes and blades being of such contour as to direct the entering air from the vanes into the 100 impeller substantially parallel to the curved air receiving portions of the impeller blades.
10. Blowing apparatus, having an axial inlet and a radial outlet, comprising, in combination, an open impeller having a plurality of blades 5 providing curved air receiving portions, and a vane structure including a plurality of vanes, said vanes and blades being of such contour as to direct the entering air from the vanes into the impeller substantially parallel to the curved air receiving portions of the impeller blades, said vanes being substantially radially disposed and of increasing width from their inner toward their outer ends.
11. Blowing apparatus, having an axial inlet and a radial outlet, comprising, in combination, an openimpeller having a plurality of blades providing curved air receiving. portions, and a vane structure including a plurality'of vanes,
said vanes and blades being of suchcontour as to direct the entering air from the vanes into the impeller substantially parallel to the curved air receiving portions of the impeller blades, 'said vanes being substantially radially disposed and of increasing width from their inner toward their 25 outer ends, and having a substantially uniform curvature throughout their length. i
12. In a blowing apparatus having an axial inlet and a radial outlet, a vane structure, and an open impeller, said vane structure including a plurality of vanes effective for directing air into the impeller, and having a continuously curved cross sectional contour providing entrance angles for the entering air substantially constant from the outer periphery of the vane structure toward the center thereof, and discharge angles for the air of gradually increasing acuteness from the center of the vane structure toward the periphery thereof, said impeller including a plurality of 13. Blowing apparatus having an axial inlet and a radial outlet, comprising a casing, an open impeller including a plurality of blades rotatable in said casing, and means cooperating with said impeller for directing air into said impeller sub-.145 stantially parallel to the front faces of said. blades, said blades having front faces of varying curved cross sectional contour throughout at least a portion of their length.
14. In a blowing apparatus having an axial inlet and a radial outlet, the combination with the curvature increasing in a direction outwardly an impeller having blades providing variously from the center of the impeller, of flow directing curved portions in a direction transversely theremeans cooperating therewith and including vanes of at different distances along their lengths, of substantially uniformly curved transversely there- 5 flow directing means cooperating therewith and of throughout their length, said blades having a 80 including vanes providing a substantially conwidth increasing from their inner toward their stant entrance angle with a discharge angle beouter ends providing air discharge angles of incoming more and more acute toward the outer creasing acuteness from the center of the flow ends thereof. directing means toward the periphery thereof 10 15. In a blowing apparatus having an axial for directing air into the impeller substantially as inlet and a radial outlet, the combination with an parallel to the curved faces of the impeller blades. open impeller having blades providing portions curved in a direction transversely thereof with PAUL E. GOOD.
7 Chhtititlh'ih or cortecrtott. I hateht hie. i,%i,o92. I @ctoher 24, R933.
their e. oooo.
, it it; herehy certified that er'rorappears in the printed speciiicatioh oi the ahove hhereti patent requiring -'correetion as ioilowsz; Page 5, time oh, tor "given to the hiodeefi read however, having; and that the said Letters Patent should he read with this correction therein that the same may comic to the record oi the case it the Patent hiiice.
Sigheo and coated this 5th day at December, A. It). 31933.
t. M, tiophixie (Seat) Acting tieiseioher ct Potehto.
htttrtrietr'e oh cotic tiott,
Patent No. t,%i, ii2. @ctoher 2%, i933.
thtlt. a. (soon it it hereby eertiiieti that the Qertiticete oi @orreetion issued @ecemher: 5, i933, was erroheoosiy drawn as to the were "having" and that this tlert t eate should have readies iottows: page 3, time tor "given to the Modes 7 read ,hovvever, wt and that the chit lLettere harem choroid he read with this correction therein-that the come mey'eohiorm to the record at the case iii the Patent tbitice,
Sighed and coated this 23rd day oi ,Bahoary, A 9. WM.
it, ht heirte (heat) Acting tloieeioner oi hoteote.
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Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2422615A (en) * 1941-11-21 1947-06-17 Havillard Aircraft Company Ltd Rotary compressor
US2438426A (en) * 1939-12-19 1948-03-23 Power Jets Res & Dev Ltd Centrifugal compressor
US2469458A (en) * 1945-09-24 1949-05-10 United Aircraft Corp Blade form for supercharger impellers
US2602683A (en) * 1945-03-03 1952-07-08 Sulzer Ag Rotor for turbomachines
US2778563A (en) * 1953-03-16 1957-01-22 Doyle Vacuum Cleaner Co Vacuum and blower producer
US2780174A (en) * 1951-03-19 1957-02-05 Solar Aircraft Co Pump and power plant assembly
US2814433A (en) * 1954-02-19 1957-11-26 Young Radiator Co Propeller fan nozzle
DE1033840B (en) * 1952-09-02 1958-07-10 Maschf Augsburg Nuernberg Ag Radial fan
US2884769A (en) * 1959-05-05 Air conditioner
US2941780A (en) * 1954-06-17 1960-06-21 Garrett Corp Elastic fluid turbine and compressor wheels
US2965287A (en) * 1955-11-11 1960-12-20 Maschf Augsburg Nuernberg Ag Radial flow compressor
US4695225A (en) * 1983-08-30 1987-09-22 Bbc Brown, Boveri & Company, Limited Axial swirl body for generating rotary flows
EP0902237A2 (en) * 1997-09-10 1999-03-17 Mitsubishi Heavy Industries, Ltd. Combustor swirler with twisted vanes
US6502399B2 (en) 1997-09-10 2003-01-07 Mitsubishi Heavy Industries, Ltd. Three-dimensional swirler in a gas turbine combustor
US20050217624A1 (en) * 2004-03-31 2005-10-06 Valeo Klimasysteme Gmbh Air intake
US20050260068A1 (en) * 2004-05-18 2005-11-24 C.R.F. Societa Consortile Per Azioni Automotive compressor
FR2880078A1 (en) * 2004-12-23 2006-06-30 Renault Sas Intake duct for turbocharger of internal combustion engine, has blades of two different types, where one blade has flat shape and another blade has shape appropriated to pre-rotate gas flow at inlet of compressor impeller
US20070286717A1 (en) * 2006-06-12 2007-12-13 Simple Tech Co., Ltd. Fan apparatus
EP2063129A1 (en) 2007-11-20 2009-05-27 Napier Turbochargers Limited Impeller and turbocharger
US20110223029A1 (en) * 2008-09-11 2011-09-15 Hunter Pacific International Pty Ltd Extraction fan and rotor
US20130189094A1 (en) * 2007-09-27 2013-07-25 Cummins Turbo Technologies Limited Multistage compressor with improved map width performance
US20140003927A1 (en) * 2012-06-29 2014-01-02 Visteon Global Technologies, Inc. Blower assembly
CN104428539A (en) * 2012-08-24 2015-03-18 三菱重工业株式会社 Centrifugal compressor
US20160177973A1 (en) * 2014-12-17 2016-06-23 Mahle International Gmbh Fan
WO2016184970A1 (en) * 2015-05-20 2016-11-24 Ebm-Papst Mulfingen Gmbh & Co. Kg Flat flow-conducting grille

Cited By (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2884769A (en) * 1959-05-05 Air conditioner
US2438426A (en) * 1939-12-19 1948-03-23 Power Jets Res & Dev Ltd Centrifugal compressor
US2422615A (en) * 1941-11-21 1947-06-17 Havillard Aircraft Company Ltd Rotary compressor
US2602683A (en) * 1945-03-03 1952-07-08 Sulzer Ag Rotor for turbomachines
US2469458A (en) * 1945-09-24 1949-05-10 United Aircraft Corp Blade form for supercharger impellers
US2780174A (en) * 1951-03-19 1957-02-05 Solar Aircraft Co Pump and power plant assembly
DE1033840B (en) * 1952-09-02 1958-07-10 Maschf Augsburg Nuernberg Ag Radial fan
US2778563A (en) * 1953-03-16 1957-01-22 Doyle Vacuum Cleaner Co Vacuum and blower producer
US2814433A (en) * 1954-02-19 1957-11-26 Young Radiator Co Propeller fan nozzle
US2941780A (en) * 1954-06-17 1960-06-21 Garrett Corp Elastic fluid turbine and compressor wheels
US2965287A (en) * 1955-11-11 1960-12-20 Maschf Augsburg Nuernberg Ag Radial flow compressor
US4695225A (en) * 1983-08-30 1987-09-22 Bbc Brown, Boveri & Company, Limited Axial swirl body for generating rotary flows
EP0902237A2 (en) * 1997-09-10 1999-03-17 Mitsubishi Heavy Industries, Ltd. Combustor swirler with twisted vanes
EP0902237A3 (en) * 1997-09-10 2000-09-20 Mitsubishi Heavy Industries, Ltd. Combustor swirler with twisted vanes
US6502399B2 (en) 1997-09-10 2003-01-07 Mitsubishi Heavy Industries, Ltd. Three-dimensional swirler in a gas turbine combustor
US7431558B2 (en) * 2004-03-31 2008-10-07 Valeo Klimasysteme Gmbh Air intake
US20050217624A1 (en) * 2004-03-31 2005-10-06 Valeo Klimasysteme Gmbh Air intake
US20050260068A1 (en) * 2004-05-18 2005-11-24 C.R.F. Societa Consortile Per Azioni Automotive compressor
US7374398B2 (en) * 2004-05-18 2008-05-20 C.R.F. SOCIETá CONSORTILE PER AZIONI Automotive compressor
FR2880078A1 (en) * 2004-12-23 2006-06-30 Renault Sas Intake duct for turbocharger of internal combustion engine, has blades of two different types, where one blade has flat shape and another blade has shape appropriated to pre-rotate gas flow at inlet of compressor impeller
US20070286717A1 (en) * 2006-06-12 2007-12-13 Simple Tech Co., Ltd. Fan apparatus
US20130189094A1 (en) * 2007-09-27 2013-07-25 Cummins Turbo Technologies Limited Multistage compressor with improved map width performance
US8845268B2 (en) * 2007-09-27 2014-09-30 Cummins Turbo Technologies Limited Multistage compressor with improved map width performance
EP2063129A1 (en) 2007-11-20 2009-05-27 Napier Turbochargers Limited Impeller and turbocharger
US20110223029A1 (en) * 2008-09-11 2011-09-15 Hunter Pacific International Pty Ltd Extraction fan and rotor
US9618007B2 (en) * 2012-06-29 2017-04-11 Hanon Systems Blower assembly
US20140003927A1 (en) * 2012-06-29 2014-01-02 Visteon Global Technologies, Inc. Blower assembly
CN104428539A (en) * 2012-08-24 2015-03-18 三菱重工业株式会社 Centrifugal compressor
US9850913B2 (en) 2012-08-24 2017-12-26 Mitsubishi Heavy Industries, Ltd. Centrifugal compressor
EP2863064A4 (en) * 2012-08-24 2015-08-26 Mitsubishi Heavy Ind Ltd Centrifugal compressor
US20160177973A1 (en) * 2014-12-17 2016-06-23 Mahle International Gmbh Fan
US10138902B2 (en) * 2014-12-17 2018-11-27 Mahle International Gmbh Fan including at least one cover element
WO2016184970A1 (en) * 2015-05-20 2016-11-24 Ebm-Papst Mulfingen Gmbh & Co. Kg Flat flow-conducting grille
US20180298916A1 (en) * 2015-05-20 2018-10-18 Ebm-Papst Mulfingen Gmbh & Co. Kg Flat flow-conducting grille
US10590954B2 (en) * 2015-05-20 2020-03-17 Ebm-Papst Mulfingen Gmbh & Co. Kg Flat flow-conducting grille

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