U.S. patent number 3,883,264 [Application Number 05/132,336] was granted by the patent office on 1975-05-13 for quiet fan with non-radial elements.
Invention is credited to Gadicherla V. R. Rao.
United States Patent |
3,883,264 |
Rao |
May 13, 1975 |
Quiet fan with non-radial elements
Abstract
In an air blower or axial compressor, such as employed in
airplane power plants, ventilating systems, etc., a series of
rotating vanes, stationary vanes, or supporting structure of
streamline struts is oriented in circumferentially leaning relation
to another series of blades in the machine so as to effect a
reduction in noise.
Inventors: |
Rao; Gadicherla V. R. (Woodland
Hills, CA) |
Family
ID: |
22453545 |
Appl.
No.: |
05/132,336 |
Filed: |
April 8, 1971 |
Current U.S.
Class: |
415/119;
415/209.1; 416/195; 416/189; 416/203 |
Current CPC
Class: |
F04D
29/544 (20130101); F02C 7/045 (20130101); F01D
5/142 (20130101); F01D 1/04 (20130101); Y02T
50/60 (20130101) |
Current International
Class: |
F01D
1/04 (20060101); F01D 1/00 (20060101); F01D
5/14 (20060101); F02C 7/04 (20060101); F02C
7/045 (20060101); F01d 005/16 (); F01d
009/02 () |
Field of
Search: |
;415/119,182,501,210,216,209 ;417/423R |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
|
|
|
|
|
|
|
637,672 |
|
Feb 1928 |
|
FR |
|
60,157 |
|
Jan 1926 |
|
SW |
|
441,269 |
|
Jan 1936 |
|
GB |
|
712,589 |
|
Jan 1954 |
|
GB |
|
631,231 |
|
Oct 1949 |
|
GB |
|
2,030,695 |
|
Jan 1971 |
|
DT |
|
Primary Examiner: Raduazo; Henry F.
Claims
I claim:
1. In an axial flow apparatus of the type described, in
combination:
a rotor unit and a stator unit each comprising a circumferential
array of vanes;
said rotor unit being rotatable in axial adjacency to said stator
unit for imparting energy to an axial flow through the
apparatus;
one of said units having a frame comprising inner and outer
supports;
said vanes of one unit including a plurality of non-radial vanes of
airfoil cross-section which are similarly oriented in non-radial
positions leaning circumferentially away from the radial in a
common direction throughout their radial extent; said vanes being
secured between said supports;
the vanes of the other unit being oriented in positions angularly
related to the positions of said non-radial vanes;
said non-radial vanes comprising a first circumferential array of
vanes all similarly oriented in positions leaning circumferentially
away from the radial in one direction and a second circumferential
array of vanes leaning away from the radial in an opposite
direction;
whereby the pulsations created by the vanes of said rotor unit
passing the vanes of said stator unit will be attenuated by the
radial progressions of the crossings of the relatively moving
vanes, thereby reducing noise.
2. An axial flow apparatus as defined in claim 1;
said first and second circumferential arrays being disposed in
respective axially adjacent planes and all secured between the same
inner and outer support members.
3. An axial flow apparatus as defined in claim 1;
said first and second circumferential arrays being disposed in
respective planes which are separated by an axial space in which
the other unit is received.
Description
BACKGROUND OF THE INVENTION
An axial compressor, air blower or a fan can be described as a
machine in which energy is imparted to the air flowing through it
in a direction essentially along the axis of the machine. The
essential components of such machines are rows of rotating blades
which impart energy to the airstream and rows of stationary vanes
which serve a dual purpose of turning the airflow in the desired
direction as well as providing structural support. The row of
rotating blades is usually called a rotor and the frame containing
the stationary vanes is usually called a stator. The combination of
a rotor and stator is usually called a stage. In some instances the
combination of a rotor situated between two stators is called a
one-and-a-half stage. In axial compressors used in jet engines one
would find a plurality of stages. In a fan employed for propelling
or providing lift for an airplane one would find only a few number
of stages. For such applications one may also use a 11/2 or a
single stage. In air blowers used in ventilating systems one may
find only a rotor supported by framework of a few streamlined
struts either in front or behind the rotor. In such cases these
supporting struts do not serve the purpose of turning the flow as
in the case of vanes in a stator. However, there is a similarity in
the manner in which noise is generated in all of these various
types of machines, so that the term stator will be employed in this
specification to include the frame containing the supporting
struts. Similarly the term vanes will be employed to include the
supporting struts even though they do not perform any flow
turning.
The primary source of noise generated in fans, air blowers, and
axial compressors is the pulsations in airflow caused by the
rotating blades moving past the stationary vanes or struts. The
fundamental frequency of the noise thus generated is the product of
the number of blades in the rotor and its speed as revolutions per
second. In present day designs, actually in use, the rotor blades
as well as the stator vanes are radially oriented in the manner of
spokes of a wheel, causing strong pulsations in the airflow passing
through them. Furthermore, such fluctuations or pulsations in the
flow reach their peak values all along the length of blade or vane
at the same instant.
In the prior patented art, the patent to Kappus, U.S. Pat. No.
3,216,654 illustrates a turbofan engine as one class of axial-flow
assemblies including a compressor unit, involving the noise problem
to which the invention is directed. Erwin U.S. Pat. No. 3,373,928
discloses a propulsion fan adaptable for a similar use which
proposes to reduce noise by multiplying the number of fan blades to
an extent such that the number of blades multiplied by the
rotational speed, gives a frequency which is above the audible
limit.
SUMMARY OF THE INVENTION
The present invention pertains to configurating the stationary
vanes in a stator and/or the rotating blades of the rotor in a
manner such as to achieve noise reduction without requiring the use
of an unusually large number of fan blades or airfoils. The details
of the rest of the engine, compressor, fan or blower will not be
discussed here, since such omission does not detract from the
usefulness or application of this invention. In this present
invention the blades and/or vanes are oriented in non-radial
configurations so as to provide vane-blade inter-actions in a
manner similar to that in a pair of scissors. Specifically, a vane
or blade interacts with the wake from an upstream vane or blade at
an oblique angle and also such interaction proceeds gradually from
hub to tip as the rotor blade moves past the stator vane. Of more
importance is that for every vane leaning in one direction there is
a corresponding vane leaning in the opposite direction. As the
above referred to wake-interaction travels radially inwardly along
one leaning vane, it will travel radially inwardly along another
corresponding vane leaning in the opposite direction. The obliquity
of the wake interactions, in conjunction with the phase differences
in the occurrence of such interactions on the plurality of vanes
provides the noise reduction.
OBJECTS OF THE INVENTION
The main object of the present invention is to provide a stator or
rotor with non-radial vanes leading in alternate directions so as
to reduce noise in fans, air blowers, and axial compressors.
Another object applicable to a stator is to provide for annular
adjustment of the set of vanes leaning in one direction relative to
the set of vanes leaning in the opposite direction.
Another object is to provide circumferentially leaning vanes in the
stator located upstream of a rotor and vanes leaning in the
opposite direction in the stator located downstream of the rotor,
and to provide angular adjustment of either one of the stators
relative to the other.
Another object is to provide a structural support frame of
non-radial streamlined struts, adjacent struts leaning
circumferentially in opposite directions, for supporting the
rotating shaft of a fan consisting of rotating vanes.
The usefulness of the invention and the claims made are not limited
to any specific application but includes all rotating machinery
where rotors and stators are employed for imparting energy to the
airstream. The term stator includes a frame containing streamlined
supporting struts, which do not turn the flow passing through
them.
DESCRIPTION OF THE INVENTION
Whereas the specification concludes with claims particularly
delineated and distinctly claiming the subject matter of the
invention, it is believed that the invention will be better
understood from the following description along with the
accompanying drawings in which:
FIG. 1 is a partial cross-sectional view showing one stage
comprising rotor and stator configurations.
FIG. 2 is an exploded perspective view of a portion of the rotor
and stator of FIG. 1 showing the orientation of the blades and
vanes in the planes of the rotor and the stator respectively.
FIG. 3 is an exploded perspective view of portions of tandem frames
in a stator.
FIG. 4 is a partial cross-sectional view of a rotor located between
two stators.
FIG. 5 is a partial cross-sectional view of a frame containing
non-radial streamlined struts, and
FIG. 6 is a perspective view showing portions of the non-radial
streamlined struts.
FIGS. 1, 2, and 3 disclose a stator downstream of a rotor in a
single stage of a multistage compressor, in the way of an example
only, and in no manner do they limit the scope of the application
of the invention. FIGS. 5 and 6 disclose a structural frame of
streamlined struts supporting a rotor employed in a ventilating
fan. The scope of the invention is not limited to any particular
axial position of this supporting frame in relation to the location
of the rotor.
Referring to FIG. 1, there is shown a partial cross section of a
single stage in a multistage compressor. The rotor, consisting of
suitably pitched radial blades 11 of airfoil cross section attached
to the hub 12, rotates and imparts velocity to the airstream
flowing between the hub and outer casing 13. Downstream of the
rotor is located a stator 14 consisting of a plurality of
stationary vanes 15 and 16 with pitch, attached to the hub and the
outer casing. The air flow leaving the rotor is turned into a
direction suitable for the following stage, not included in the
figure, by employing suitable airfoil cross sections for the
stationary vanes in the stator. In addition to performing the
required flow turning, these stationary vanes also provide
structural support between the hub and the outer casing. In
specific applications where no flow turning is required, the stator
may consist of few supporting streamlined struts without pitch. The
direction of flow is indicated by arrows in the figure.
Referring next to FIG. 2, there is shown a perspective view of
portions of rotor and stator of FIG. 1. For the sake of clarity,
the rotor and stator are shown in an exploded view in this figure,
but in any practical application they will be close to each other.
The rotor contains radially oriented blades 11 having suitable
airfoil sections and pitch as in conventional axial compressor
rotors. The means of securing the rotor blades to the rotating hub
12 and the means of providing torque to the rotor are not shown in
the figure, as such omission does not detract from the usefulness
of the invention. The perspective view of the stator 14 depicts the
arrangement of the stationary vanes. There is one set of vanes 15
all located in one cross-sectional plane followed by another set of
vanes 16 all of which are located in an adjacent cross-sectional
plane. These stationary vanes 15 and 16 are of suitable airfoil
shapes with pitch such as to provide the required turning angle to
the flow passing through the duct formed by the hub and the outer
casing. With respect to radial direction, the vanes 15 lean
circumferentially in one direction, whereas the vanes 16 lean in an
opposite direction. The details of securing the vanes 15 and 16 to
the inner rim 17 or to the outer rim 18 are not shown in the
figure, as they do not affect the use of and advantages provided by
the present invention.
In FIG. 3 is shown a partial view of the tandem frames of a stator.
All the stationary vanes 19 leaning in one direction are secured to
an inner rim 20 and outer rim 21. All the stationary vanes 22
leaning in the other direction are secured to an inner rim 23 and
outer rim 24. Only for the sake of clarity these tandem frames are
shown far apart from each other, but in any practical application
they are close to each other, e.g. as in FIG. 1. On the outer rim
24 is arranged a worm-gear 25 to provide a means for rotatably
adjusting the position of vanes 22 with respect to the vanes 19.
The drive for the worm-gear and its control are not shown in the
figure as they are not an essential feature of the invention. Other
means for providing a similar relative motion can be employed
without affecting the use and claims of this invention. The means
for securing the rims 23 and 24 to the hub and outer casing of the
compressor are not shown in the figure. To provide structural
rigidity and prevent vibration of the vanes 19, a circular ring 26
is attached to all the vanes at a suitable radial location between
the hub and tip. This ring 26 is secured to a portion or all of the
airfoil cross section employed for the vanes. Similarly a ring 27
is attached to all the vanes 22 to provide the structural support
referred to above. In FIG. 4 is shown an alternate use of the
stator frames comprising the non-radial vanes. This is a partial
view of the tandem frames shown in FIG. 3, axially spaced with a
rotor between. The rotor 28 containing rotating blades is located
between stators 29 and 30 containing stationary vanes. The
stationary vanes in stator 29 are made to lean in a direction
opposite to those in the stator 30 as described in FIG. 3. The
rotor vanes 11 are radial and pitched as in FIG. 2. Furthermore, a
worm-gear such as shown at 25 in FIG. 3 is attached to either of
the stators 29 and 30 to provide a means of altering their angular
disposition as discussed in FIG. 3.
In FIG. 5 is shown a partial cross-sectional view of a stationary
frame which serves the purpose of a supporting structure for the
rotating shaft connected to a suitable rotor. The rotor containing
the rotating blades is not shown in the figure and can be upstream
or downstream of the supporting struts 31 shown in the figure. All
of the streamlined struts 31 extending non-radially outward, are
attached to an inner hub 32 and outer rim 33, and are contained in
the same cross-sectional plane. A suitable bearing, not shown in
the figure, is utilized within the hub to carry the rotating shaft
of a compressor, fan or air blower.
In FIG. 6 is shown a view of the structural frame of FIG. 5
depicting the non-radial and alternately leaning configuration of
the streamlined struts. Half of the streamlined struts 34 are all
similarly oriented and lean in one direction. The remaining struts
35 are all similarly oriented and lean in a direction opposite to
that of the struts 34. All the struts are secured to an inner hub
32 and an outer rim 33 to form a rigid supporting structure. The
details of means of securing the struts to the inner and outer rims
are not shown in the figure. One or more circular rings 36 can be
attached to part or the entire cross sections of the struts at
suitable radial locations to provide additional rigidity to the
streamlined struts.
Having described the orientation and structural arrangements of the
plurality of non-radial vanes in a stator, some of the definite
characteristics can be observed. Since all the vanes such as 15 or
16 shown in FIG. 2, lying in one cross-sectional plane are oriented
in the same direction, the distance between any two adjacent vanes
measured along the circumference at any specific radius remains
constant. Consequently, presently available design methods can be
employed to choose the airfoil cross sections and pitch for the
vanes. The vanes 15 and vanes 16 will have suitably designed
airfoil sections so that the required flow turning is partially
accomplished in the row of vanes 15 and the remainder in the row of
vanes 16.
Any structural vibrations of the vanes 15 or 16 shown in FIG. 2 can
be damped by securing the trailing edges of each forward vane 15 to
the leading edges of rear vane 16 at the points of
intersection.
In another form of application of the invention, the vane
configuration shown for the stator in FIG. 2 can be employed for a
rotor. In such application the stationary vanes of the adjacent
stator are radially configured in a manner similar to the rotor
blades shown in rotor of FIG. 2. Each rotating leaning blade
together with a corresponding rotating blade leaning in the
opposite direction and portions of the inner and outer rims
connecting them form a rigid structure. Consequently, the rotating
blades in spite of their non-radial configuration are not subjected
to excessive bending stresses under the effect of centrifugal
force.
The vanes 19 and 22 shown in FIG. 3 may have a short chord in
comparison to their length. Any structural vibrations of the vanes
are damped by one or more suitable circumferential rings located
between the inner and outer rims and connected to all or part of
the airfoil sections of the vanes.
The specific purpose of providing means for angular displacement
between tandem frames as shown in FIG. 3 is to optimize the noise
reduction with changes in the rotor speed. The worm-gear 25,
schematically shown in FIG. 3, can be driven by a mechanism
controlled by the rotor speed. In an application where optimum
noise reduction is desired at a specific speed or where the speed
does not appreciably change, a fixed position of the vanes, as in
FIG. 2, can be chosen to simplify the structural design of the
inner and outer rims of the stator.
The invention as described here in terms of stationary vanes lends
itself easily for modifications to existing machinery to reduce
their noise. For example, whatever aerodynamic or structural duties
an existing stator is required to perform can be easily done by the
two rows of stationary vanes 15 and 16 together as shown in FIG.
2.
While certain preferred forms of the invention are described,
modifications and variations are obviously possible. It is
therefore to be understood that within the scope of the claims, the
invention may be practiced otherwise than specifically
described.
The effectiveness of the invention in reducing noise as intended
has been established by me through tests on an experimental
fan.
In the appended claims, the term "vane" is used in a generic sense
to designate both the stator vanes and the rotor blades of the
foregoing description.
* * * * *