U.S. patent number 3,658,437 [Application Number 05/023,321] was granted by the patent office on 1972-04-25 for diffuser including vaneless and vaned sections.
This patent grant is currently assigned to Caterpillar Tractor Co.. Invention is credited to Shao L. Soo.
United States Patent |
3,658,437 |
Soo |
April 25, 1972 |
DIFFUSER INCLUDING VANELESS AND VANED SECTIONS
Abstract
A diffuser for use in turbomachinery to improve overall
efficiency, the diffuser including a vaneless diffuser section for
reducing supersonic fluid flow to subsonic speed and a
multi-channel diffuser section for achieving maximum pressure
recovery and delivering the fluid to a suitable collector, one of
the diffuser sections providing a flow path of decreasing and then
increasing cross section configured to minimize boundary layer
losses.
Inventors: |
Soo; Shao L. (Urbana, IL) |
Assignee: |
Caterpillar Tractor Co.
(Peoria, IL)
|
Family
ID: |
21814410 |
Appl.
No.: |
05/023,321 |
Filed: |
March 27, 1970 |
Current U.S.
Class: |
415/181; 415/207;
415/214.1; 415/224.5; 415/143; 415/208.3 |
Current CPC
Class: |
F04D
21/00 (20130101); F04D 29/441 (20130101); F04D
29/444 (20130101) |
Current International
Class: |
F04D
29/44 (20060101); F04D 21/00 (20060101); F04d
029/40 (); F04d 017/08 () |
Field of
Search: |
;415/207,209,211,181,219,219A |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
|
|
|
|
|
|
|
724,553 |
|
Aug 1942 |
|
DD |
|
971,229 |
|
Dec 1958 |
|
DT |
|
Primary Examiner: Raduazo; Henry F.
Claims
I claim:
1. In a turbomachine, a diffuser for conditioning fluid flow of at
least transonic speed from a rotor and transmitting it to a
collector means, the diffuser comprising
an annularly open region for receiving fluid flow from the rotor,
the annularly open region being formed by spaced apart walls for
conditioning fluid flow from the rotor,
a diffuser section comprising means forming multiple tangential
channels for delivering fluid flow to the collector means, and
a transition section for delivering fluid flow from the annularly
open region to the multiple channel diffuser section,
the annularly open diffuser region having a convergent-divergent
configuration selected to produce a condition of imminent boundary
layer separation, the transition section being configured for
maintaining the condition of imminent boundary layer separation,
each of the multiple channels also having a convergent-divergent
configuration in a downstream direction selected to establish a
condition of imminent boundary layer separation.
2. In a turbomachine, a diffuser for conditioning fluid flow of at
least transonic speed from a rotor and transmitting it to a
collector means, the diffuser comprising
an annularly open region for receiving fluid flow from the rotor,
the annularly open region being formed by spaced apart walls for
conditioning fluid flow from the rotor,
a diffuser section comprising means forming multiple tangential
channels for delivering fluid flow to the collector means, and
a transition section for delivering fluid flow from the annularly
open region to the multiple channel diffuser section,
at least a portion of the diffuser having a cross section which
converges and then diverges in the direction of flow to establish
and maintain a condition of imminent boundary layer separation in
order to minimize boundary layer losses,
the initial portion of the annularly open diffuser region
converging in the direction of flow for accelerating the velocity
of fluid flow from the rotor,
the rotor being of a type for delivering fluid flow radially
outwardly from its periphery, the spaced apart walls forming the
annularly open region being arranged in substantially radial
relation to the rotor, the multiple channel diffuser section means
being a plurality of elements circumferentially arranged between
walls spaced apart in substantially radial relation to the rotor,
surfaces of the plurality of elements forming opposite sides of
each channel being generally parallel, the spaced apart walls in
the multiple channel diffuser section converging toward each other
and then diverging in a downstream direction for producing a
condition of imminent boundary layer separation.
Description
RELATED U.S. PATENTS
The present invention is described having reference to an earlier
filed Pat. application, now U.S. Pat. No. 3,289,921 issued Dec. 6,
1966, to Shao L. Soo and assigned to the assignee of the present
invention.
The present invention relates to a diffuser for use with a
centrifugal compressor in various turbomachines to decrease
velocity and increase pressure of fluid exiting the compressor
impeller rotor. More particularly, the present diffuser includes an
initial vaneless portion for reducing high Mach number flow
(including transonic and supersonic fluid flow) from the rotor to
lower Mach number flow while minimizing boundary layer losses.
Fluid flow is delivered from the vaneless portion into a vaned
diffuser portion defining multiple channels for achieving maximum
pressure recovery with fluid flow from the vaned diffuser section
being delivered to a suitable collector. Fluid flow through a
diffuser constructed according to the present invention is subject
to more accurate boundary layer control so that overall efficiency
is increased within a given outer diameter diffuser envelope.
Conventional vaned diffusers of a type including a separator and
collector or having multiple tangential channels are well known in
the prior art. However, shock waves and pressure waves are commonly
developed in these diffusers during supersonic and transonic fluid
flow. These shock waves tend to disrupt the flow pattern through
the diffuser and accordingly lower diffuser efficiency.
Accordingly, it is an object of the present invention to provide a
compact diffuser capable of optimum pressure recovery.
It is a further object to accomplish such efficiency through the
use of a first vaneless section within the diffuser followed by a
vaned section.
It is a still further object to provide such a diffuser wherein at
least a portion of the diffuser is characterized by a cross section
which decreases and then increases in a manner suitable for
maintaining fluid flow under a condition of imminent boundary layer
separation.
It is a still further object to provide the decreasing and
increasing cross section by means of opposing walls which converge
toward each other and then diverge in a downstream direction.
It is another object of the invention to provide elements within
the vaned diffuser section for forming multiple tangential channels
to provide for increased pressure recovery within the diffuser.
It is still another object of the invention to form opposing
surfaces of adjacent elements in parallel relation with radially
spaced apart walls converging and then diverging within the vaned
diffused section.
Other objects and advantages of the present invention are made
apparent in the following description having reference to the
accompanying drawings.
In the drawings:
FIG. 1 is a sectioned view of the compressor portion of a gas
turbine engine including a diffuser constructed in accordance with
the present invention;
FIG. 2 is a fragmentary, sectioned view taken from one side of FIG.
1 to illustrate a portion of the compressor impeller or rotor and
the fluid path from the rotor through the diffuser;
FIG. 3 is a view taken along section lines III--III of FIG. 2;
FIG. 4 is a view taken along section lines IV--IV of FIG. 2;
FIG. 5 is an enlarged view of a portion of FIG. 2 to more clearly
illustrate construction of the entry way into one of the multiple
channels of the vaned diffuser sections;
FIG. 6 is a view taken along section lines VI--VI of FIG. 5,
and
FIG. 7 is a view taken along section line VII--VII of FIG. 6.
A turbomachine of the type illustrated in FIG. 1 includes a
compressor rotor 11. Fluid such as air enters the rotor from region
12. Accelerated fluid exits the rotor at its periphery 13 and
enters a diffuser 14 which is constructed according to the present
invention. The diffuser 14 includes a vaneless portion or region
generally indicated at 16 and a vaned region which is indicated at
17. The location and construction of the vaneless and vaned
sections of the diffuser is described in greater detail below.
Fluid from the vaned diffuser section enters an annular collector
18. A portion of the fluid in the collector passes into a single
combustion chamber 19 through a plurality of ports indicated at 21
and then into a chamber 22 from where the fluid passes into turbine
means 23 in a generally conventional manner.
With the rotor 11 operating at its design speed, for example 28,800
rpm, the rotor may have a fluid absolute velocity at its peripheral
exit 13 which is at least transonic and may be supersonic. The
vaneless diffuser portion 16 reduces the fluid flow rate from
supersonic or transonic speeds to a subsonic inlet speed suitable
for the vaned diffuser portion. The diffuser section is an
annularly open region wherein the shock waves do not tend to arise
from the supersonic and transonic speeds of fluid flow. Thus, the
fluid velocity may be reduced without introducing shock waves into
the flow pattern of the diffuser.
Normally, shock waves arise due to interaction of supersonic or
transonic fluid flow with vanes or blades in a vaned diffuser
section. However, in the present diffuser the fluid velocity is
reduced to subsonic speed before entering the vaned diffuser
section. Thus, shock waves do not tend to be created and the vaned
diffuser section is capable of providing maximum pressure recovery
within a given diffuser envelope.
Referring now to FIG. 2 as well as FIG. 1, the vaneless diffuser
section 16 is formed as an annularly open region between radially
spaced apart walls 30 and 31. The vaneless section may be
identified more accurately in FIG. 2 as lying between the periphery
13 of the rotor and a circle defined by the leading edges 32 of
vane islands 33 within the vaned diffuser sections.
As may be seen in FIG. 1 but more clearly shown in FIG. 3, the
radially spaced apart walls 30 and 31 converge together and then
diverge slightly within the vaneless diffuser section.
The vaned diffuser section includes multiple channels 36 which are
arranged in tangential relation to the rotor 11. Each of the
channels 36 has a similar throat such as that indicated at 37 in
FIGS. 2 and 4.
A transition section of the diffuser is formed generally between
the annularly open vaneless region and the multiple channels 36 of
the diffuser. The transition section delivers fluid flow from the
annularly open region 16 into the respective channels 36. The
transition section is formed generally of a plurality of
triangularly shaped areas respectively located at the entry to each
of the channels 36, one of these triangular areas of the transition
section being more clearly shown in FIG. 5. Lines 41, 42 and 43 in
FIG. 5 represent constant spacing between the walls 30 and 31.
Having particular reference to FIGS. 5, 6 and 7, the transition
section is contoured in a manner best illustrated in FIG. 6. As may
be best seen in FIG. 6, the walls 30 and 31 diverge just upstream
from the throat 37 in each of the channels 36. The manner in which
the divergency between the walls 30, 31 extends between the vane
islands or elements 33 may be seen by combined reference to FIGS.
5-7.
Referring again to FIG. 2, opposing walls, for example those
indicated at 51 and 52 on adjacent vane elements 33 to form a
channel 36 are preferably arranged in parallel relation. To form a
cross section which decreases and then increases in a downstream
direction through each channel 36, the radially spaced apart walls
30, and 31 within the vaned diffuser section are contoured in a
manner best illustrated for example in FIG. 4. As seen in that
figure, the walls converge together to form the throat 37 and then
diverge in a downstream direction toward a chamber 53 for each
channel which is in communication with the collector 18 (see FIG.
1). With reference to the vaned diffuser section, it is noted that
the vane islands 33 could also be replaced by generally
conventional blades or foils of a type used in conventional
diffuser designs.
Having further reference to FIG. 2, it may be noted that the
opposite surfaces 51, 52 of each vane island 33 are arranged in
more nearly parallel relation for a portion of each vaned island
which extends beyond one of the adjacent channels 36 into the
diffuser transition section. Thus, the surface 51 of each vane
island 33 is formed with an obtuse angle to allow for the parallel
relation of the walls 51, 52 within the vaned diffuser section.
The converging diverging relation of the walls 30, 31 within the
vaneless and vaned sections of the diffuser are selected to
establish a condition of imminent boundary layer separation within
the diffuser. General considerations and specific examples for
establishing the convergent-divergent contour of opposing walls to
maintain such a condition are set forth in greater detail in U.S.
Pat. No. 3,289,921 referenced above.
Accordingly, the vaneless diffuser region accomplishes the purpose
of reducing supersonic or transonic fluid flow to subsonic speeds
without the introduction of shock waves or pressure waves. The
vaned diffuser section may then operate at optimum efficiency to
pressurize the fluid flow within a compact diffuser envelope.
Maximum pressurization is achieved within the diffuser through the
convergent-divergent contouring of the walls 30, 31 to maintain a
condition of imminent boundary layer separation.
* * * * *