AU8070891A - Gaseous fluid aspirator or pump - Google Patents
Gaseous fluid aspirator or pumpInfo
- Publication number
- AU8070891A AU8070891A AU80708/91A AU8070891A AU8070891A AU 8070891 A AU8070891 A AU 8070891A AU 80708/91 A AU80708/91 A AU 80708/91A AU 8070891 A AU8070891 A AU 8070891A AU 8070891 A AU8070891 A AU 8070891A
- Authority
- AU
- Australia
- Prior art keywords
- impeller
- inlet
- gaseous fluid
- blade
- flow
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Description
GASEOUS FLUID ASPIRATOR OR PUMP
The present invention relates to improvements relating to a gaseous fluid aspirator or pump particularly but not exclusively to an aspirator for an optical air pollution apparatus particularly a very early warning smoke detector apparatus adapted to summon human intervention before smoke levels become dangerous to life or delicate equipment. It can cause early or orderly shut down of power supplies and it can operate automatic fire suppression systems.
The present invention will be described with reference to an aspirator for use with very early warning smoke detection apparatus. Smoke detection apparatus of the type described in applicants U.S. Patent No. 4,608,556 directed to a heat-sensitive/ gas- sampling device in a smoke detector system including sampling pipes and an apertured housing in association with a smoke detection device of the type described in U.S. Patent No. 4,665,311 which has a sampling chamber as illustrated in Figure 1 of the drawings therein. With reference to Figure 7 of the U.S. Patent No. 4,608,556 there is shown schematically a reticulation fluid/smoke mixture transport system of sampling pipes leading to various sampling areas to continuously sample air from those various areas. The transport system leads back to a sampling chamber of the type for example that is described in U.S. Patent No. 4,665,311. However, it will be equally applicable to other apparatus requiring efficient long-lived operation of an aspirator at low power consumptions.
The smoke detector utilises an airtight chamber through which a representative sample of air within the zone to be monitored, is drawn continuously by an aspirator. The air sample is stimulated by an intense, wide band light pulse. A minuscule proportion of the incident light is scattered off airborne particles towards a very sensitive receiver, producing a signal which is processed to represent the level of pollution in this instance of smoke. The instrument is extremely sensitive, so much so that light scattered off air molecules alone may be detected. Therefore, minor pollution is readily detectable as an increased signal. Therefore, the detector which is utilisable in commercial situations, is extremely sensitive and yet has a low incidence of false alarms. It is extremely important that the means for obtaining a continuous sample of the air to be monitored is reliable, efficient, consumes only a small amount of power and has a long life. It is also important that the aspirator develops a relatively high pressure and pressure and draws a relatively large volume of air given its low power rating in order that there is little or no delay in the detection of smoke or like pollution in a dangerous situation.
Existing aspirator systems as currently used, utilise an axial flow fan providing relatively low cost and long life coupled with ready availability. However, known equipment has a very low efficiency of less than 2% at flow rates of 40 litres per minute.
Such low efficiency is considered unsatisfactory particularly if increased flow rates with reduced power input is to be attainable.
Thus it is an objective of the present invention to provide a gaseous fluid aspirator/pump having relatively high pressure output with increased efficiency and decreased power requirements.
A more specific objective is to provide an efficient aspirator of the order of 20% efficiency, having a capacity of the order of 60 litres per minute at a pressure of the order of 300 Pascals with an input of about 2 watts and having a long reliable life.
There is provided according to the present invention a gaseous fluid aspirator/pump apparatus including a curved blade impeller with radially extending blades, the impeller being mounted in a housing having a gaseous fluid inlet and outlet wherein gaseous fluid moving from the inlet to the outlet is turned from axial flow into the impeller to radial flow from the impeller, said impeller and an associated portion of the housing being shaped to prevent flow separation and turbulence in the gaseous fluid stream whilst under the influence of the impeller.
Specifically the impeller inlet includes an inlet configuration of curvate form in which the cross-sectional area is maintained constant by projecting a truncated conical section around the inlet throat until the blade passage is reached.
Thus flow separation is prevented whilst turning the fluid flow through 90° and acceleration and deceleration of the fluid flow is substantially prevented, minimising loses. Turbulent eddies are minimised and uniform velocity distribution is achieved. The impeller blade inlet angle can be set by conventional velocity-triangle means and the number of blades is optionally set at 12.
The invention will be described in greater detail having reference to the accompanying drawings in which Figure 1 is a cross-sectional view of the aspirator showing the configuration of the impeller and housing inlet. Figure 2 is a frontal view of the impeller blades.
Figure 3 shows a measured comparison of performance curves between a conventional aspirator and the aspirator of the invention.
Figure 4 shows comparative response times for a given length of pipe. Figures 5 and 6 show schematically the derivation of impeller throat dimensions and composition of inlet boss profile.
Figure 7 shows impeller inlet area calculation according to Eck.
Figure 8 shows impeller blade leading-edge profiles.
Figure 9 shows inlet area reduction caused by rounded leading-edge.
Figure 10 shows modification of blade leading-edge. The aspirator shown in Figure 1 includes an impeller 10 and inlets throughout 11 forming a curvate inlet cavity with surfaces 15, 16 presenting a constant cross- sectioned area to the fluid stream for receiving incoming air and turning it through 90° into impeller blades to travel to the peripheral chamber 14, forming a rounded trapezoidal volute. The impeller includes a cavity 17 for housing a small DC brushless motor (not shown). To minimise temperature rise, and therefore improve bearing life, a cooling fan is preferably incorporated for the motor. To minimise friction losses labyrinth seals 18, 19 are provided.
With reference to Figure 2 of the drawings the blades 20 of the impeller are of minimum thickness (1 mm) to reduce energy losses. The leading edges 21 of the blades are rounded parabolically to avoid a narrowing of the channel width to minimise acceleration of the air stream.
No detailed information can be found regarding the design of the impeller inlet throat geometry (including the boss profile), its importance being all-too-readily dismissed by others. However, this can hold the key to high efficiency so a method was derived from first principles, to minimise energy loss by :
* preventing flow separation while turning the airflow through 90°,
* preventing acceleration or deceleration of the airflow, and by preparing the airstream for presentation to the blade channel entrance in such a manner that, within the blade channels:
* flow separation and eddies would be minimised, and
* a uniform velocity distribution would be achieved.
This method resulted in a parabolic boss profile in which it was possible to emulate this shape to a high accuracy by specifying a short circular arc. The blade inlet angle was set by conventional velocity-triangle means, and the number of blades was set at 12.
To minimise energy loss caused by the blade leading-edges, the blades are designed with minimum thickness (1 mm). However, when set at the required angle, their effective thickness is 2.7 mm. With 12 blades their combined thickness would constitute a significant reduction in the inlet cross-sectional area, so the channel depth is increased
(with a smooth transition) at the leading-edge to maintain a constant mean air velocity.
Moreover, the blade leading-edges are rounded parabolically (see Figure 10) (rather than a conventional wedge-shape) to remove a narrowing of the channel width which would also accelerate the airstream, thus incurring loss.
The blade channel is preferably maintained at a constant depth of 3.3 mm by parallel shrouds. The blades are preferably curved to achieve radially extending tips thereby producing a maximum static head matched by a dynamic head component that must be converted to static head in the outlet diffuser attached to the spiral volute. The spiral volute geometry has an expanding rounded-trapezoidal design modified to fit within the available space, complete with an 8° diffuser nozzle for which a trapezoidal to circular transition was required. It is possible to match the inlet and outlet couplings exactly to mate with the standard 25 mm pipe work carrying the gaseous fluid for sampling. This enables the staging of multiple aspirators where higher pressures may be needed and facilitates the attachment of an exhaust pipe to overcome room pressure differentials that sometimes occur, for example in computer rooms. With reference to Figures 1 , 5 and 6, details of the formation of the inlet throat
15,16 will be described.
For minimum loss the airstream should be directed to flow parallel to the walls of the throat. Accordingly, the cross-sectional area should be measured perpendicular to that flow, i.e. perpendicular to the throat walls. In practise however, the throat walls themselves (turning through 90°) cannot be parallel if a uniform cross-sectional area is to be achieved. Moreover, in computing the throat area, only one wall shape was defined in the first instance, so the extent to which the second (boss) wall might not be parallel, was not yet known. To obtain a cross-sectional area measured at an angle which averaged perpendicularity to both walls (i.e. perpendicular to a centreline), would require an iterative process.
However, this extra effort could be counter-productive because it is possible that the airstream would flow partially in shear, due to incomplete turning. Moreover, at the pipe-throat interface, the bulk of the mass flow is biased towards the first wall (simply because the cross-sectional area of any annular ring of given width is proportional to the annular radius squared). Therefore it would seem most appropriate to calculate the cross- sectional area perpendicular to this first wall.
In visualising this area three-dimensionally, it was discovered that the cross- section at any point along the throat is described by the surface of a truncated cone (see Figure 5). Available literature provided differing formulae for the sloping-surface area
(excluding the base) of a regular cone, e.g.: S = pi r (r+h). However, this formula was
found incorrect, failing the simple test of mathematically comparing (say) the area of a known semicircle, pulled into the shape of a cone or "Indian teepee").
An alternative formula was derived from first principles and was subjected to rigorous testing. Accordingly, the surface area As of a cone of base radius r and height h is given by:
As = pi r h (1 + (r/h)2).5
And for a truncated cone the surface area becomes :
As = pi (r2 2 - n h (1 + (r2/h2)2).5
By application of this formula to the impeller configuration as illustrated in Figure 5, it has been possible to derive the following equation which has also been rigorously tested by "longhand" calculations : rb = ((rι - x)2 - r02 x /(n - r0 ))- 5 This general solution may be simplified by substitution of r0 = 10.5 and = 20 which have been determined for this particular impeller design: rb = ((20 - x)2 - 11.6 x)-5 which may be solved for various values of x. However, the resulting values for rb may be more easily handled by converting to x', where: x' = r-, - rb = 20 - rb - 20 - ((20 - x)2 - 11.6 x)-5
The vertical coordinates, y and y' are determined by the value of x, because of the circular curvature of the first throat wall and congruency of the triangles: y = (f2 . X2).5 = (90 - X2).5 y' = y x'/x By plotting the coordinates (x',y') obtained for several values of x, it is possible to determine the curve of best fit, as illustrated in Fig. 6. Fortunately, a satisfactory fit to this parabola was achieved using a circular curve.
In the case of this impeller, the best-fit radius of curvature was found to be 22 mm, drawn tangentially to the blade channel. Conveniently this approach requires that the part-circle is constructed with its centre at the set distance r-i = 20 mm from the impeller centreline. Whereas the curve of best fit requires a very sharp central tip for the boss, to assist with die fabrication and to allow the extraction of each molded part without breakage, and to provide a more-conventionally aerodynamic leading edge, it is proposed that the central point should be rounded 24 as indicated in Fig. 6. It is expected that in practise, this minor rounding would have a negligible effect upon any aspect of the
impeller performance. Indeed, this type of rounding (though with a much greater radius) is reminiscent of the round-headed impeller-retaining nuts commonly used in larger cast metal centrifugal pumps.
Bl APE PASSAGE ENTRY Now, at the leading edge of the blades there exists the potential for a sudden change in area which would introduce losses. This change in area arises from the thickness of the blades. If the throat width immediately ahead of the blades was made equal to the blade width, there would be a reduction in area upon entering the blade passage. Alternatively, if the throat width were reduced so that the throat area equalled the blade passage area, there could be an equally lossy discontinuity because of the necessary difference in widths.
The solution lies with shaping the blade passage entry according to the shape of the leading-edge of the blades. As the airflow encounters the blade leading-edge, the passage width should expand smoothly from the required throat width to the required blade width, maintaining a uniform cross-sectional area. This expansion taper should be completed within the length of the blade shaping.
It would seem ideal to ensure that the shaping and the taper were made complementary throughout the transition, but this would suggest wedge shapes and in practise it is expected that the simple provision of smooth curves in both dimensions would minimise loss.
As illustrated in Fig. 6, it is desirable to provide the expansion taper 22 on one shroud only, i.e. the motor side. This simplifies the design, by leaving the inlet-side shroud unaltered. More importantly, a tapered expansion of the inlet shroud would tend to promote flow separation within the blade passage. With reference to Figures 7 to 10 detailed description of the blade entry design will be made.
According to Eck the effective thickness (f) of each blade is larger than the actual thickness (t), depending upon the acuteness of the inlet angle (B-i). This is illustrated in
Fig. 7, where for simplicity the inlet circle has been straightened-out (Eck uses different symbols, namely s = t, sigma = t'). The effective thickness is easily obtained by geometry: f = t/sin(B1) = 1/sin(25) = 2.4 mm
Fig. 8 compares the effects of using the chisel-shaped leading-edge of Eck, with a rounded shape which is preferred. This rounded shape is more practicable to mold and should reduce the entry shock losses including flow separation behind the blade, particularly at
flow rates significantly below the rated capacity of the impeller (where a rounded shape would adapt more readily to differing velocity angles).
It can be shown (with reference to Fig. 8) that in the case of a rounded shape, the effective thickness is obtained by a modified equation: V = t (1+1/sin(Bi ))/2 = 1 *(1 +1/sin(25))/2 = 1.7 mm
Unfortunately, it can be seen from Fig. 9 that Eck's concept of straightening-out the inlet circle disguises another effect. In practice the blades cannot be regarded as parallel and there is a degree of narrowing of the blade passage as the airstream passes the rounded leading-edge. Any such narrowing would cause a momentary increase in air velocity (acceleration), resulting in loss. This narrowing is caused by the acute angle of the back of the next blade. In the case of a 12-blade impeller, the next blade is advanced by 360/12 = 30°.
Therefore the leading-edge should be "sharpened" as indicated in Fig. 10, to avoid the momentary narrowing of the blade passage area. This is achieved by constructing a line parallel to the next blade (30° advanced), intersecting with the inlet tangent (at 20 mm radius), as shown at point "a". This line is inclined to the inlet tangent at the required rake angle of (B1 + 360/z) = 55°, intersecting with the edge of the blade at point "b". The other side of the blade is similarly treated to achieve symmetry.
Ideally the sudden transitions (sharp edges) produced by this sharpening should be smoothed by using appropriate curves as shown (dashed). The resulting shape more closely resembles a classical aerodynamic profile.
Although it was initially regarded as important to utilize a semicircular leading- edge for simplicity in mold fabrication, such a narrow (1.0 mm) blade thickness would require spark-erosion milling in any case, so the aerodynamic profile would be only slightly more expensive to mill.
It is interesting to note that for the range of possible values of Bi (0 to 90°), for an impeller with 12 blades there is no sharpening required if B-| exceeds 60°. The maximum sharpening (30° rake) occurs for Bι = 0.
According to the leading-edge profile of Fig. 10 it is possible to retain the previously-calculated effective blade thickness, namely 1.7 mm. Utilizing this figure, the useable inlet circumference reduces to:
C1' = C1 - z f = 126 - 12*1.7 = 106 mm
To produce an inlet area equal to the pipe area, the blade width at the impeller inlet should be: W-i = Ao/Cι ' = 346/106 = 3.3 mm
Additional constructional features provided in the pump housing incorporates isolation of the aspirated air from the ambient air to enable operation in hazardous areas. To achieve this, the motor labyrinth is designed as a flame trap to comply with Australian standards. 5 Figures 3 and 4 give graphical representations of the performance of the aspirator as described herein as compared with the conventional aspirator currently utilised in the early warning smoke detection apparatus.
With reference to Figure 3, the increased pressure possible with the new aspirator is shown and in one example with a 100 metre pipe a pressure rise in excess of 1 0 300 Pascals at a speed of 3,800 φm was achieved at a power drain of only 2 watts which is less than half that of the original aspirator. The sustained good performance at relatively high flow rates provides a distinct advantage for use with large numbers of pipes and sampling holes without compromising the operation of single pipe systems.
With reference to Figure 4, this shows the drastically improved response times of
1 5 the aspirator according to the invention as against the length of pipe whereby in a 100 metre pipe the smoke transport time is reduced by a factor of 4. With shorter less restrictive pipes the improvement is less dramatic but nevertheless the time is halved for a 50 metre pipe.
Calculations have shown that the peak total efficiency of the aspirator was in fact
20 21%. Therefore, taking into account the known motor efficiency, the peak impeller efficiency proved to be 49% which for an impeller pump of such low specific speed as in the present example, such results are well in advance of normal expectations. Moreover it has been found that the impeller achieves an internal efficiency of 81% given the special attention made to the inlet throat geometry and blade design. 25 The parts of the aspirator can be injection moulded thereby allowing automatic production and assurance of repeatable quality. These factors significantly increase factory capacity committing a rapid response to increasing market demand whilst assisting to maintain an internationally competitive cost structure. The invention provides an improved system performance for early fire detection, however, the scope of
30 application for the aspirator is considerably widened where low power input and fast response are required such as in battery-powered or solar-powered air pollution monitoring applications.
Claims (4)
1 . A gaseous fluid aspirator/pump apparatus including a curved blade impeller with radially extending blades, the impeller being mounted in a housing having a gaseous fluid inlet and outlet wherein gaseous fluid moving from the inlet to the outlet is turned from axial flow into the impeller to radial flow from the impeller, said impeller and an associated portion of the housing being shaped to prevent flow separation and turbulence in the gaseous fluid stream whilst under the influence of the impeller.
2. Apparatus as claimed in claim 1 wherein the impeller inlet and associated housing portion are configured in matching curvate conical form in the area of the inlet opening acting to prevent or restrict flow separation in fluid flowing therein whilst turning the fluid flow through a substantial angle such as 90° and also to substantially prevent or restrict acceleration and deceleration of said fluid flow in the apparatus.
3. Apparatus as claimed in claim 1 or 2 wherein the impeller blades are rounded along a parabolic curve to maintain constant cross-sectional area at the leading-edge of the blade passages thereby avoiding narrowing of the width between said blades and to minimise acceleration or deceleration of the air stream.
4. In a smoke detection system a gaseous fluid aspirator/pump apparatus as claimed in any one of claims 1 to 3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| AU80708/91A AU653735B2 (en) | 1990-06-19 | 1991-06-19 | Gaseous fluid aspirator or pump |
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| AUPK070990 | 1990-06-19 | ||
| AUPK0709 | 1990-06-19 | ||
| AU80708/91A AU653735B2 (en) | 1990-06-19 | 1991-06-19 | Gaseous fluid aspirator or pump |
| PCT/AU1991/000261 WO1991019906A1 (en) | 1990-06-19 | 1991-06-19 | Gaseous fluid aspirator or pump |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| AU8070891A true AU8070891A (en) | 1992-01-07 |
| AU653735B2 AU653735B2 (en) | 1994-10-13 |
Family
ID=25639563
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| AU80708/91A Ceased AU653735B2 (en) | 1990-06-19 | 1991-06-19 | Gaseous fluid aspirator or pump |
Country Status (1)
| Country | Link |
|---|---|
| AU (1) | AU653735B2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7075646B2 (en) | 2000-02-10 | 2006-07-11 | Martin Terence Cole | Smoke detectors particularly ducted smoke detectors |
| US7551277B2 (en) | 2003-10-23 | 2009-06-23 | Siemens Schweiz Ag | Particle monitors and method(s) therefor |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2827266A (en) * | 1956-10-31 | 1958-03-18 | V C Patterson & Associates Inc | Vestibule for cold storage warehouses |
| CH404069A (en) * | 1962-06-29 | 1965-12-15 | Licentia Gmbh | Flow channel, in particular working medium flow channel of a turbo compressor |
-
1991
- 1991-06-19 AU AU80708/91A patent/AU653735B2/en not_active Ceased
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7075646B2 (en) | 2000-02-10 | 2006-07-11 | Martin Terence Cole | Smoke detectors particularly ducted smoke detectors |
| US7508313B2 (en) | 2000-02-10 | 2009-03-24 | Siemens Aktiengesellschaft | Smoke detectors particularly ducted smoke detectors |
| US7551277B2 (en) | 2003-10-23 | 2009-06-23 | Siemens Schweiz Ag | Particle monitors and method(s) therefor |
| US7724367B2 (en) | 2003-10-23 | 2010-05-25 | Siemens Schweiz Ag | Particle monitors and method(s) therefor |
| US7738098B2 (en) | 2003-10-23 | 2010-06-15 | Siemens Schweiz Ag | Particle monitors and method(s) therefor |
Also Published As
| Publication number | Publication date |
|---|---|
| AU653735B2 (en) | 1994-10-13 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MK14 | Patent ceased section 143(a) (annual fees not paid) or expired |