U.S. patent number 3,768,919 [Application Number 05/190,199] was granted by the patent office on 1973-10-30 for pipe diffuser with aerodynamically variable throat area.
This patent grant is currently assigned to Avco Corporation. Invention is credited to John A. O'Connor.
United States Patent |
3,768,919 |
O'Connor |
October 30, 1973 |
PIPE DIFFUSER WITH AERODYNAMICALLY VARIABLE THROAT AREA
Abstract
A "pipe" diffuser comprises an annular housing surrounding a
centrifugal impeller and has primary diffuser passages intersecting
with one another to form scallop-shaped entrance edges. A series of
ports are provided in the throat region of the diffuser passages to
momentarily inject pressurized diffuser exit air to aerodynamically
vary the throat flow characteristics and prevent surge during
operation of the stage above its normal surge line.
Inventors: |
O'Connor; John A. (Orange,
CT) |
Assignee: |
Avco Corporation (Stratford,
CT)
|
Family
ID: |
22700394 |
Appl.
No.: |
05/190,199 |
Filed: |
October 18, 1971 |
Current U.S.
Class: |
415/116; 415/914;
415/151 |
Current CPC
Class: |
F04D
29/441 (20130101); Y10S 415/914 (20130101) |
Current International
Class: |
F04D
29/44 (20060101); F04d 029/44 (); F04d
027/02 () |
Field of
Search: |
;415/DIG.1,207,98,151,116 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
|
|
|
|
|
|
|
659,211 |
|
Aug 1936 |
|
DD |
|
209,026 |
|
Apr 1924 |
|
GB |
|
Primary Examiner: Raduazo; Henry F.
Claims
Having thus described the invention, what is claimed as novel and
desired to be secured by Letters Patent of the United States
is:
1. A compressor assembly comprising:
a rotatable bladed impeller having an annular discharge region;
an annular diffuser housing surrounding the discharge of said
impeller, said diffuser having a plurality of generally conically
diverging tangentially directed diffuser passages having throats
which intersect adjacent the discharge of said impeller to form a
series of generally scalloped inlet edges to said diffuser passage
throats, said diffuser passages having an angle of incidence with
respect to the air leaving the discharge region of said impeller
that directs the air more radially outward than a free vortex flow,
thereby creating high and low pressure regions on opposite sides of
said scalloped inlet edges; and
means for injecting air into the throats of said diffuser passages
and means for supplying a source of air adjacent said throats at a
static pressure level higher than that of the air in the throats of
said passages, and means for forming ports from said source of
pressurized air for injection into the throats of said diffuser
passages to aerodynamically alter the flow characteristics of said
throats and means including ports for injecting air to the low
pressure side of said scalloped inlet edges thereby aerodynamically
reducing the effective incidence of the passages relative to the
flow from the impeller.
2. A compressor assembly as in claim 1 wherein said port is a slot
for injecting a sheet of air generally over the low pressure side
of said scalloped inlet edge.
3. A compressor assembly as in claim 1 wherein said
injection port means includes ports directing air generally
tangentially with respect to the longitudinal axis of said throats
to aerodynamically reduce the cross-sectional flow area
thereof.
4. A compressor assembly as in claim 1 wherein said
injection port means includes ports positioned to direct air
radially inward toward the longitudinal axis of said throats to
aerodynamically reduce the cross-sectional flow area thereof.
5. A compressor assembly as in claim 1 wherein said air supply
means comprises:
means for extracting pressurized air from the discharge of said
diffuser passages; and
means for distributing said air to a point adjacent the throats of
said passages.
6. A compressor assembly as in claim 5 wherein said distributing
means comprises a series of chambers formed in said diffuser
housing in between adjacent diffuser passages and conduit means
connecting the discharge from said diffuser passages to said
chambers.
7. A compressor assembly as in claim 5 wherein said injection port
means additionally define ports directed tangentially with respect
to the longitudinal axis of said throats to aerodynamically reduce
the cross-sectional flow area thereof.
8. A compressor assembly as in claim 5 wherein said injection port
means additionally define directing air radially inward with
respect to the longitudinal axis of said throats to aerodynamically
reduce the cross-sectional flow area thereof.
Description
This invention was made under a contract with the U. S.
Government.
The present invention relates to compressor assemblies and more
particularly to compressor assemblies utilizing the "pipe"
diffuser.
The so-called "pipe" diffuser has been used in centrifugal
compressors to achieve high pressure ratios. This type of diffuser
is illustrated in U. S. Pat. No. 3,333,762 in the name of J. C.
Vrana. This diffuser generally comprises a series of tangentially
extending conical passages in a housing which surrounds the
periphery of a centrifugal impeller. The passages intersect
adjacent the periphery of the impeller in such a fashion that they
produce scallop-shaped inlet edges for the diffuser passages. The
scalloped edges conform more closely to the velocity distribution
of the air leaving the impeller to produce a highly efficient
handling of both subsonic and supersonic flows discharged from the
impeller.
Normally in a compressor of the above type as utilized in a gas
turbine engine, it is designed to operate as closely as possible to
the compressor surge line in order to provide the most efficient
compressor performance. This operating line is a steady state
operating line, however, and when the engine is accelerated to a
higher rotational speed the operating point of the compressor stage
tends to move toward and across the surge line. The resultant
instability and back flow produces a great loss in efficiency and
performance. For prior art vane-type diffusers surge during
acceleration has been avoided by mechanically altering the
configuration of the diffuser. In the pipe diffuser, however, a
mechanical alteration is difficult, if not impossible due to the
complex sealing and component displacing problems. At present the
only alternative for a pipe diffuser is to provide an operating
line sufficiently removed from the surge line so that acceleration
will not cause the compressor to go into surge.
Therefore it is an object of the present invention to provide a
compressor with a pipe diffuser of the above general type that
operates at a high level of efficiency closely adjacent the surge
line for both steady state and transient conditions without going
into surge.
This end is accomplished by incorporating in a pipe diffuser means
for injecting air into the throats of the pipe diffuser passages to
aerodynamically alter the flow characteristics of the diffuser.
This change in the diffuser characteristic allows a controlled
surge line shift for the stage which can be utilized to prevent
surging during transient operation when the surge line would
normally be exceeded.
The above and other related objects and features of the present
invention will be apparent from a reading of the description of the
disclosure shown in the accompanying drawing and the novelty
thereof pointed out in the appended claims.
In the drawing:
FIG. 1 is a sectional view of a centrifugal compressor
incorporating a diffuser which embodies the present invention;
FIGS. 2 and 3 are fragmentary sectional views of the diffuser of
FIG. 1 taken on lines 2--2 and 3--3, respectively, of FIG. 1;
FIG. 4 is an alternate embodiment of the diffuser shown in FIG. 1;
and
FIG. 5 is a graph of pressure ratio versus corrected weight air
flow for the compressor assembly of FIG. 1.
Referring to FIG. 1 there is shown a rotatable centrifugal impeller
10 having blades 12 which pressurize and accelerate air for
discharge through an annular region defined generally by the
periphery 14 of the impeller 10. The air thus discharged enters
into a series of diffuser passages, generally indicated by
reference character 18, formed in an annular diffuser housing 20.
Housing 20 has an inner diameter 21 surrounding the periphery 14 of
impeller 10. As herein shown, each of the passages 18 comprise a
generally constant cross-sectional area throat portion 22 and a
conical outlet portion 24. The longitudinal axes 26 of each passage
18 are positioned so that the throat portions 22 intersect with
adjacent throats to produce a series of scallop-shaped inlet edges
28, as seen particularly in FIG. 2.
As shown in FIG. 3, the diffuser housing 20 has a series of
chambers 30 in between adjacent diffuser passages 18 around the
periphery of housing 20. Each chamber 30 is connected to a suitable
air distribution system comprising a manifold conduit 34 and
connecting conduits 36 (only one of which is shown) leading from
the manifold conduit 34 to the chambers 30. Manifold conduit 34 is
connected to the outlet of the diffuser passages 18 by means of a
suitable connection system illustrated in simplified form as a
conduit 38 by way of a control valve 40. It should be apparent to
those skilled in the art that other forms of air distribution
systems may be used to supply pressurized diffuser exit air to the
regions adjacent each throat 22 of the diffuser passages 18.
A series of ports 42 connect chambers 30 with the throat 22 of the
passages 18. As illustrated in FIG. 3 ports 42 extend tangentially
relative to the longitudinal axis 26 of the passages 18. An
additional passageway 44 connects the chamber 30 with the low
pressure side of scalloped leading edges 28, as will be described
below in detail. The passage 44 is in the form of an elongated
slot. As is apparent, passage 44 may be supplied with air from a
different distribution system at different pressure levels if
desired.
During steady state operation the compressor operates along the
operating line SS shown in FIG. 5. This line SS generally conforms
to and is closely adjacent to surge line S.sub.1. During
acceleration or certain other transient operation of the engine,
the operating line temporarily follows the line ACL which would
place the diffuser above the surge line S.sub.1. However, during
this transient condition the valve 40 is opened to permit the flow
of air from the diffuser outlet to the throats 22 which are at a
lower static pressure level. The ports 42 inject the air into the
stream which aerodynamically reduces the flow area of the throat,
thus moving the surge line to line S.sub.2 which is well away from
the transient operating line ACL. When the steady state condition
has again been reached the valve 40 is closed, thus terminating the
flow. The pressure in chambers 30 and throats 22 are now equalized
and there is no net flow into the chambers.
The use of the slotlike passage 44 may be used in addition to or
separately from the ports 42 to aerodynamically change the flow
characteristics of the scalloped leading edges 28. Injection of air
through passage 44 changes the flow characteristics in the
following manner. In the absence of flow passages, air discharged
from the periphery of impeller 10 tends to follow along a free
vortex flow path. The diffuser passages 18 tend to divert the air
more radially outward than a path following the laws of free vortex
motion. As a result, the radially outboard side of scalloped edge
28 tends to have a pressure higher than the radially inboard side
of edge 28. The injection of air through slot 44 to the low
pressure side tends to make a blunter leading edge and
aerodynamically produces an optimum angle of incidence for the
scalloped edge 28 that is more tangential. The injection of air
from slot 44 injects air into the separation region which forms
under the high positive incidence conditions existing and delays
stalling around the scalloped leading edge 28.
FIG. 4 shows a different embodiment for injecting air into the
throats of the diffusers. In this figure there are shown ports 46
extending from chambers 30' into the throats 22' of the diffuser
passages 18'. It will be noted that ports 46 are directed radially
inward with respect to the longitudinal axis 26' of the diffuser
passages 18'. Injection of air through these ports aerodynamically
reduces the throat area in a fashion similar to that for ports 42
shown in FIGS. 1, 2 and 3. By varying the injection angle we are
able to produce a variation in blockage for a fixed flow rate. It
should be apparent that the ports 46 may even be angled forward or
aft or varied in size to produce a variation in blockage for a
given injected air flow.
The diffuser systems described allow a compressor assembly to be
matched as close as desired to the surge line for steady state
operation to attain a maximum efficiency, yet have a sufficient
surge margin for transient operation. A momentary decrease in
efficiency occurs during acceleration due to the pressure losses of
recirculating the compressor discharge air and deterioration of
diffuser performance due to blockage. However, because of the short
time these conditions are incurred they will not significantly
effect the overall engine mission performance.
In each of the arrangements described above the precise degree of
flow blockage may be adjusted to given compressor performance
criteria by selecting the size and number of the holes, as is
apparent to those skilled in the art. These arrangements permit a
diffuser with a high degree of efficiency in addition to a
substantial surge margin for both steady state and transient
operating conditions.
While the preferred embodiment of the present invention has been
described, it should be apparent to those skilled in the art that
further modifications may be performed without departing from the
spirit and scope .
* * * * *