U.S. patent number 3,885,891 [Application Number 05/432,724] was granted by the patent office on 1975-05-27 for compound ejector.
This patent grant is currently assigned to Rockwell International Corporation. Invention is credited to Lester W. Throndson.
United States Patent |
3,885,891 |
Throndson |
May 27, 1975 |
**Please see images for:
( Certificate of Correction ) ** |
Compound ejector
Abstract
Apparatus and methods of operation are disclosed for combining
injected high-energy primary flow fluid (normally a gaseous medium)
and induced or entrained secondary flow fluid (frequently air) at
and in the essentially conventional throat and diffuser sections of
an ejector to significantly increase ejector performance efficient
with limited injection slots or openings of limited size and with
minimum diffuser lengths, to achieve high diffusion rates and
substantially reduced system energy losses attributed to fluid flow
blockage and flow separation, and to obtain other important ejector
operating characteristics.
Inventors: |
Throndson; Lester W.
(Westerville, OH) |
Assignee: |
Rockwell International
Corporation (Pittsburgh, PA)
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Family
ID: |
26977547 |
Appl.
No.: |
05/432,724 |
Filed: |
January 11, 1974 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
Issue Date |
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310723 |
Nov 30, 1972 |
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Current U.S.
Class: |
417/196;
417/197 |
Current CPC
Class: |
F04D
25/08 (20130101); F04F 5/42 (20130101); F04F
5/466 (20130101); F04F 5/16 (20130101) |
Current International
Class: |
F04F
5/00 (20060101); F04F 5/16 (20060101); F04F
5/42 (20060101); F04F 5/46 (20060101); F04f
005/44 () |
Field of
Search: |
;60/264,269
;239/8,265.17 ;417/167,179,180,196,197 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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613,144 |
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Jan 1961 |
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CA |
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1,235,302 |
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May 1960 |
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FR |
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Other References
"Experimental Thrust Augmentation of a Variable Geometry,
Two-dimensional Coanda Wall Jet Ejector" W. J. Scott, January 1964
- National Research Council of Canada Aeronautical Report
LR-394..
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Primary Examiner: Wood, Jr.; M. Henson
Assistant Examiner: Love; John J.
Parent Case Text
CROSS REFERENCES
This is a continuation, of application Ser. No. 310,723, filed Nov.
30, 1972, now abandoned.
Claims
I claim:
1. In ejector apparatus immersed in a body of secondary flow fluid
and producing an augmented thrust vector oriented along an ejector
longitudinal axis, in combination:
perimeter injector means having opposed discharge slots that are
positioned at opposite sides of said longitudinal axis and that are
oriented and sized to each discharge primary fluid flowed
therethrough in a direction toward and substantially at right
angles to said longitudinal axis at a discharge velocity greater
than approximately 0.7 Mach number;
convergent inlet surfaces each extending from immediately adjacent
a respective one of said perimeter injector means opposed discharge
slots and continuing in the direction of fluid flow along said
longitudinal axis through a rotational angle in the range of
approximately 80.degree. to 110.degree. to form an ejector
apparatus throat having a minimum dimension D in a direction normal
to said longitudinal axis;
center injector means having a discharge nozzle that is positioned
intermediate said perimeter injector means discharge slots and
above said ejector apparatus throat minimum dimension D and that is
oriented and sized to discharge primary fluid flowed therethrough
in a direction generally along said longitudinal axis at a
discharge velocity greater than approximately 0.7 Mach number;
divergent diffuser surfaces continuing from said convergent inlet
surfaces in the region of said ejector apparatus throat minimum
dimension D to a termination at an interface with said body of
secondary flow fluid and with an average divergence with respect to
each other of angle 2.alpha.; and
duct means flowing high energy primary flow fluid to said perimeter
injector means discharge slots and to said center injector means
discharge nozzle at pressure ratios greater than approximately 1.3
relative to said body of secondary flow fluid and at flow rates
sufficient for maintaining said discharge velocities,
said perimeter injector means opposed discharge slots and said
divergent diffuser surfaces termination being separated in a
direction along said longitudinal axis by a distance L that is less
than approximately 2.5 times said ejector apparatus throat minimum
dimension D, and said divergent diffuser surfaces average
divergence angle 2.alpha. being at least approximately
15.degree..
2. The invention defined by claim 1 wherein said opposed discharge
slots each have a height H in the direction of said ejector
longitudinal axis and wherein said convergent inlet surfaces each
have a mean radius of curvature R for said rotational angle, said
height H and said radius of curvature R being in a ratio
substantially in the range of from 1:5 to 1:5
3. The invention defined by claim 1 wherein said divergent diffuser
surfaces termination is separated from said perimeter injector
means opposed discharge slots in a direction along said
longitudinal axis by a distance L that is substantially less than
approximately 2.0 times said ejector apparatus throat minimum
dimension D.
4. The invention defined by claim 1 wherein said duct means high
energy primary flow fluid is proportioned with approximately from
30 to 70 percent being flowed to said center injector means and the
balance being flowed to said perimeter injector means.
5. The invention defined by claim 4 wherein said duct means high
energy primary flow fluid is proportioned with approximately 50
percent being flowed to said center injector means and the balance
being flowed to said perimeter injector means.
6. The invention defined by claim 1 wherein said divergent diffuser
surfaces average divergence angle 2.alpha. is at least
approximately 24.degree..
7. A method of augmenting the thrust of a primary fluid flow in
ejector apparatus which is immersed in a body of secondary fluid
and which has joined in succession along a longitudinal axis a
convergent inlet section, a throat section of minimum dimension D
in a direction normal to said longitudinal axis, and a divergent
diffuser section, comprising the steps of:
injecting part of said primary fluid flow into said ejector
apparatus in a direction generally along said longitudinal axis as
a free core jet centrally of a secondary fluid inlet opening in
said convergent inlet section and generally from above and toward
said throat section at a discharge velocity greater than
approximately 0.7 Mach number and entraining and mixing secondary
fluid flowed through said inlet opening into and with primary fluid
from said free core jet;
simultaneously injecting the balance of said primary fluid flow
into said ejector apparatus in a direction generally at right
angles to said longitudinal axis as wall jets and from opposite
sides of said secondary fluid inlet opening in said convergent
inlet section, toward said longitudinal axis, and at discharge
velocities greater than approximately 0.7 Mach number over opposed
curved inlet surfaces in said convergent inlet section adjacent
thereto;
turning said primary fluid flow injected as wall jets over said
curved inlet surfaces in said convergent inlet section and
entraining and mixing additional secondary fluid flowed through
said secondary fluid inlet opening in said convergent inlet section
into and with the primary fluid of said wall jets;
diffusing said free core jet and wall jet primary fluid flow and
entrained and mixed secondary fluid in said ejector apparatus
intermediate opposed wall surfaces extending from said throat
section and defining said divergent diffuser section; and
discharging said diffused free core jet and wall jet primary fluid
flow and entrained and mixed secondary fluid from said ejector
apparatus and into said body of secondary fluid a distance from the
region at which said primary fluid flow is injected into said
ejector apparatus that is in the direction of said longitudinal
axis greater than approximately 1.0 times but less than
approximately 2.5 times said throat section minimum dimension
D,
said primary fluid flow and entrained and mixed seconary fluid
thereby having a thrust at the region of discharge into said body
of secondary fluid at least 50 percent greater in magnitude than
the magnitude of thrust of said primary fluid flow.
8. The method defined by claim 7 wherein said primary fluid flow
injected as a free core jet and as wall jets is injected into said
ejector apparatus at a pressure ratio of approximately 1.3 or
greater with respect to the pressure of said body of secondary
fluid.
9. The method defined by claim 7 wherein said primary fluid flow
injected into said ejector apparatus as wall jets has a height in
the direction of said apparatus longitudinal axis in a ratio to the
mean radius of curvature of said opposed curved inlet surfaces in
said convergent inlet section in the range of approximately from
1:5 to 1:5 initially.
10. The method defined by claim 7 wherein said primary fluid flow
injected into said ejector apparatus is proportioned in a manner
whereby approximately from 30 to 70 percent is injected as said
free core jet and the balance is injected as said wall jets.
11. The method defined by claim 7 wherein said primary fluid flow
injected into said ejector apparatus is proportioned in a manner
whereby approximately 50 percent is injected as said free core jet
and the balance is injected as said wall jets.
12. The method defined by claim 7 wherein said primary fluid flow
injected as wall jets is turned over said opposed curved inlet
surfaces in said convergent inlet section through an angle in the
range of approximately from 30.degree. to 110.degree..
13. The method defined by claim 7 wherein said primary fluid flow
injected as wall jets is turned over said opposed curved inlet
surfaces in said convergent inlet section through an angle in the
range of approximately from 80.degree. to 110.degree..
14. The method defined by claim 7 wherein said free core jet and
wall jet primary fluid flow and entrained and mixed secondary fluid
is diffused intermediate opposed wall surfaces extending from said
throat section that diverge with respect to each other through an
average angle that is at least approximately 15.degree..
15. The method defined by claim 7 wherein said free core jet and
wall jet primary fluid flow and entrained and mixed secondary fluid
is diffused intermediate opposed wall surfaces extending from said
throat section that diverge with respect to each other through an
average angle that is at least approximately 24.degree..
Description
SUMMARY OF THE INVENTION
Ejector apparatus having conventional throat and diffuser sections
in its operating configuration is provided with center injector
means and additionally with Coanda injector means, and is operably
connected to a source of high-energy primary flow fluid. The
injected primary flow fluid from both said injector means is
combined with entrained secondary flow fluid, induced through the
ejector inlet opening, at and in the ejector throat and diffuser
sections to both significantly increase ejector output
force-to-input force performance ratio (thrust augmentation ratio)
and minimize ejector system energy losses in comparison, for
instance, to the performance of comparably sized and configured
conventional multi-tube injector ejector apparatus. The invention
achieves thrust augmentation ratios at least to as great as
approximately 1.55 employing a secondary flow entrance (slot) area
ratio of approximately 12.5, and is especially significant with
respect to short length ejector configurations wherein the desired
ratio of ejector diffuser length to ejector throat diameter is in
the range of approximately 1 to 2.
DESCRIPTION OF THE DRAWINGS
FIG. 1 is a schematic plan view of an embodiment of the compound
ejector of this invention having a throat section with circular
planform;
FIG. 2 is a schematic sectional view taken at line 2--2 of FIG.
1;
FIG. 3 is a schematic plan view of an embodiment of the compound
ejector of this invention having a throat section with a
rectangular planform;
FIG. 4 is a schematic cross-sectional view taken at line 4--4 of
FIG. 3; and
FIG. 5 graphically illustrates thrust augmentation ratio
performance achieved by the instant invention in comparison to
thrust augmentation ratio performance achieved with various
conventional ejector apparatus arrangements.
DETAILED DESCRIPTION
The embodiment of the invention illustrated schematically and in
sectional detail in FIGS. 1 and 2 is distinguished from the other
embodiment illustrated in the drawings primarily by the planform of
the ejector throat configuration. The principal elements comprising
the FIG. 1 arrangement are separately described in the following
subparagraphs, each identified initially by the appropriate
reference numeral in the drawings, and additionally as to element
nomenclature, details of form and construction, and statement of
principal function or functions:
11; ejector high-energy fluid source; normally in the form of a
source of pressurized gaseous medium at a pressure ratio of
approximately 1.3 or greater (e.g. 1.3 to 30 depending on type and
location of source available) at the source discharge face such as
a high-pressure gas supply, a gas compressor, a turbo-fan engine
fan, or a turbo-jet engine turbine section; provides primary flow
fluid to the ejector and such fluid may comprise, in some
applications, products of combustion at an elevated temperature
(e.g. 65.degree.C. to 600.degree.C.) relative to ambient or
atmospheric temperature (nominal 15.degree.C.).
12; supply duct sections; normally of metallic construction or of
fibre-reinforced thermosetting resin construction and in
conventional duct cross-sectional configurations preferably sized
to minimize internal fluid flow pressure or energy losses and to
achieve flow velocities of about 0.25 Mach Number in typical
applications but sometimes to as great as about 0.4 Mach Number;
directs primary flow fluid from source 11 to primary flow
distribution ductwork:
13; distribution duct sections; similar in construction and
cross-sectional configuration to duct sections 12; direct
proportioned primary flow fluid to system injectors;
14; duct fittings; similar in construction to duct sections 12 and
13 and of conventional fitting configuration; join system duct
sections together and to other system fluid distribution
elements;
15; primary flow control valve; essentially of metallic
construction and conventional valve configuration but in some
applications may take form of plug nozzle with cooperable diverter;
regulates/diverts flow of primary flow fluid from source 11 through
supply duct sections 12;
16; proportioning valves; of conventional metallic construction and
configuration; proportioning of primary flow fluid to minimize
system energy losses preferably and normally is accomplished by
varying duct diameters of slot and nozzle opening sizes but if
elements 16 are provided in the ejector arrangement, such function
to further control the primary flow fluid from source 11 for proper
distribution to individual injectors in the apparatus, and in
either case proportioning normally is with from 30 to 70 percent of
total primary fluid flow to the ejector center injector and the
balance to the ejector Coanda injector;
17; center injector; of streamlined duct-like or tube-like
construction using materials comparable to the materials comprising
duct sections 12 and 13 and having a location above the ejector
throat section and an operating orientation downwardly along the
general flow direction of the ejector diffuser section; directs
primary flow fluid to the center of the ejector throat section for
downward projection essentially along the ejector diffuser section
flow axis;
18; nozzle opening; an opening in the center injector sized to
achieve a desired percentage primary fluid and a flow velocity
approaching or in excess of approximately 0.7 Mach Number and
located preferably slightly above or at the plane of the ejector
throat section; provides downward primary air flow at the throat
center and at a proper velocity;
19; coanda injector supply duct; generally similar to injector
means 17 in construction materials but of annular planform
configuration with the toroidal inside diameter essentially
corresponding to the ejector throat section diameter and the
toroidal average diameter corresponding to the diameter of the
ejector circular inlet area; typically directs primary flow fluid
to the perimeter of the ejector inlet for injection into system 10,
for approximately 90.degree. to 110.degree. angular rotation
(15.degree. to 30.degree. minimum), and for mixing and downward
projection essentially in nonseparated relation to the diverging
walls of the ejector diffuser section;
20; Coanda slot opening; ring-like slot opening in the Coanda
injector supply duct substantially coextensive with the perimeter
of the ejector circular inlet area and sized to achieve a primary
fluid flow in the desired 30 to 70 percent total flow range and
with a velocity approaching or in excess of approximately 0.7 Mach
Number; the opening, by virtue of its location and orientation
essentially injects primary flow fluid radially inwardly toward the
inlet area center and approximately at right angles to the lift
ejector operating longitudinal axis whereupon it is rotated by the
Coanda effect typically approximately 90.degree. to 110.degree.
into a downward path generally along the direction of the walls
defining the ejector divergent diffuser section; and
21; diffuser section wall; of metallic composition of
fibre-reinforced thermosetting resin composition in plate-like,
circumferentially continuous form and joined and faired to the wall
of Coanda injector means 19 to provide a smooth transition from the
ejector throat to the divergent ejector diffuser section exit
opening; length essentially accomplishes mixing of ejector primary
and secondary fluid flows and diffusion allows pressures produced
at the inlet to induce ejector secondary fluid flow and develop
improved ejector thrust.
In addition, the drawings are provided with certain of the
following reference symbols identifying features or characteristics
of the ejector construction of the invention useful for analytical
purposes:
L; ejector length (height); extends from the plane of the ejector
exit opening to the plane of ejector inlet opening, the latter
normally being positioned a relatively small distance above the
plane of the ejector throat section;
D; ejector diameter; essentially the diameter of the ejector throat
section except that in cases of non-circular throat section
planforms the dimension may correspond to the average planform
dimension of the throat area affected by the center injector and
the ejector cross-section being analyzed;
A.sub.th ; cross-sectional (planform) area of ejector throat
section;
A.sub.i ; cross-sectional (planform) area of ejector inlet;
A.sub.e ; cross-sectional (planform) area of ejector exit;
A.sub.p ; cross-sectional area of primary fluid flow exits which in
most instances is the sum of the discharge area of the center
injector nozzle opening and the Coanda injector slot opening;
A.sub.s ; cross-sectional area of secondary or entrained fluid flow
which in most instances, because of relative absence of blockage in
the ejector throat section by the center injector means 17,
essentially corresponds to the ejector inlet area A.sub.i ; and
.alpha.; ejector diffuser section wall divergence angle
(half-angle) relative to the lift ejector axis in the general
direction of principal fluid flow.
Heavied arrow showings in the drawings indicate principal air flow
direction for the primary, secondary, and combined fluid flows. The
ejector discharge flow at the exit face is particularly noteworthy
in view of the fact that it is substantially of improved
distribution across the exit face.
FIG. 3 illustrates an ejector apparatus embodiment 30 having the
features of this invention combined with supporting structure
referenced generally as 31. In addition to a different throat
section planform, those FIG. 3 (and FIG. 4) elements of the
embodiment which differ significantly from FIG. 1 and FIG. 2 in
detail are as follows:
32; straight-line center injector; has characteristics, except for
principal planform configuration, of center injector 17; directs
primary flow fluid in the operating position for downward
projection essentially along the ejector diffuser section flow
axis;
33; slot opening; in center injector 32 and similar in all other
characteristics, excepting an elongated planform configuration, to
the nozzle opening 18 described in connection with ejector
embodiment 10;
34 and 35; straight-line Coanda injector; each of construction and
form characteristics similar, except as to planform configuration,
to Coanda injector 19 of the FIGS. 1 and 2 arrangement; comprised
of a slotted, duct-like straight-line Coanda injector; each
projects part of the primary flow fluid (approximately one-half of
the typical 30 to 70 percent proportion of total primary flow) from
source 11 into the ejector inlet and throat section regions for
downward projection essentially along the ejector diffuser section
interior wall surfaces and for mixing;
36 and 37; Coanda slot opening; straight-line openings in injectors
34 and 35 and otherwise similar in characteristics and function to
slot opening 20.
Another embodiment of the instant invention is generally similar to
embodiment 30 but is not shown in the drawings. Such additional
embodiment differs from the FIGS. 3 and 4 arrangement in that it
includes two center injector assemblies 32 positioned intermediate
injectors 34 and 35 and in spaced-apart relation relative to each
other. By this alternate arrangement a proportionately greater
center injection of primary flow fluid can be developed.
FIG. 5 provides quantitative information regarding the performance
capabilities and characteristics of the instant invention. Curves
41 and 42 indicate the magnitude of thrust augmentation obtained
with the instant invention at L/D ratios of 2.5 and 2,
respectively. Although the instant invention is important with
respect to ejectors having a L/D ratio of 2.5 or less, it is
particularly significant with respect to ejector apparatus having a
ratio (L/D) in the range of approximately 1 to 2. In the case of
curve 41, which is in part based on actual test data and in part on
theoretical projection, the test embodiment of the compound ejector
was operated with a divergence half-angle (.alpha.) of 7.5.degree..
Curve 42, on the other hand, involved a divergence half-angle of
12.degree..
The performance of the ejector of this invention, as manifested by
curves 41 and 42, also is compared in FIG. 5 to the performance of
conventional ejectors of comparable design and operating parameters
having only Coanda injection (curves 43 through 45) at 6.degree.
half-angle divergence or only conventional center injection (curve
46) at 7.5.degree.. It is apparent from curves 43 through 46 that
for comparable ratios of ejector throat area to primary slot area,
significantly improved thrust augmentation ratios are obtained with
the present invention. Shorter design lengths (L) are achieved by
practice of the invention as a result of permitting utilization of
high divergence half-angles (.alpha.) with improved diffuser wall
boundary layer control.
In considering the foregoing described invention, careful
distinction must be made between introducing primary flow fluid
into the ejector system by means of a Coanda slot opening in
comparison to introducing such primary flow fluid into the ejector
by tangential injection over the diffuser wall as such is typically
accomplished from a region near the ejector throat. In one test
arrangement involving injection from opposed Coanda slot openings
as in the FIG. 3 arrangement an obtained thrust augmentation ratio
of 1.35 was reduced to a value of 1.2 when one opposed ejector
inlet Coanda slot opening was replaced with a wall-tangent throat
area injector operated at otherwise identical fluid flow
conditions. Studies of flow separation from the ejector diffuser
wall as a function of diffuser divergence angle established that in
a case of distinct wall separation at a 6.degree. half-angle with
center injection only, no separation was observed with the
additional introduction of Coanda slot injection as described in
connection with this invention.
Also, opposed Coanda slot opening injection is considered to
efficiently turn high pressure ratio (e.g. 3.5 to 4) fluid flows
over a relatively small arc. From the standpoint of effecting
Coanda flow turning without separation, the ratio of vane radius or
turn curvature adjacent the slot opening to slot height is
important and fortunately is not considered highly critical. With a
small radius to a slot-height ratio (approximately 5), flow
detachment from the ejector wall becomes apparent at a pressure
ratio of about 1.8 and is based on observed detachment after about
50.degree. of turning. Increasing the ratio of surface turning
radius to slot-height functions to improve the obtained thrust
augmentation ratio particularly when at values in the range of
approximately 10 to 15.
* * * * *