U.S. patent number 3,873,232 [Application Number 05/420,201] was granted by the patent office on 1975-03-25 for two-piece channel diffuser.
This patent grant is currently assigned to Avco Corporation. Invention is credited to John T. Exley, Wolfgang J. Stein, Salvatore Straniti.
United States Patent |
3,873,232 |
Stein , et al. |
March 25, 1975 |
TWO-PIECE CHANNEL DIFFUSER
Abstract
A channel diffuser for a centrifugal compressor in which the
diffuser is formed from two annular elements, sandwiched together.
One element is a flangelike portion of the outer housing for an
engine and has a smooth radially extending face. The second element
has a series of tangentially directed channels open toward the
radial face on the first element to form diffuser passages. The
channels in the second element diverge both in width and in height
so that all the divergence in the passages is provided by the
channels.
Inventors: |
Stein; Wolfgang J. (Milford,
CT), Straniti; Salvatore (Orange, CT), Exley; John T.
(Milford, CT) |
Assignee: |
Avco Corporation (Stratford,
CT)
|
Family
ID: |
23665491 |
Appl.
No.: |
05/420,201 |
Filed: |
November 29, 1973 |
Current U.S.
Class: |
415/207;
415/208.3 |
Current CPC
Class: |
F04D
29/441 (20130101) |
Current International
Class: |
F04D
29/44 (20060101); F04d 029/44 (); F01d
009/04 () |
Field of
Search: |
;415/207,211,82,210,181
;60/39.26 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Freeh; William L.
Assistant Examiner: Casaregola; Louis J.
Attorney, Agent or Firm: Hogan; Charles M. Gron; Gary M.
Garfinkle; Irwin P.
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 diffuser for use with a gas turbine engine having a
generally annular housing comprising:
a first annular element having a substantially smooth face defined
by an inner and outer diameter, said face being defined by
straight-lined elements extending radially from said inner to said
outer diameter, said first annular element forming a portion of
said housing;
a second annular element having an inner and outer diameter
substantially equal to the inner and outer diameter of the face on
said first element, said second annular element abutting the face
of said first element, said second element having a plurality of
tangentially directed channels extending from the inner to the
outer diameter of said second element to form a series of diffuser
passages, said passages comprising an inlet throat section having a
constant height and width, a first diffusing section having a
height and width which expand at a first rate and a second
diffusing section having a height and width which expands at a
second faster rate, said widths expanding in the downstream portion
of the channel whereby said diffuser sections provide an increasing
cross-sectional flow area defined by an increasing channel depth
and increasing channel width and whereby all of the divergence in
the diffuser passageways takes place in said second element.
2. Apparatus as in claim 1 wherein said first annular element is in
the form of a flange and said smooth face is in a radial plane.
3. Apparatus as in claim 1 wherein said gas turbine engine
comprises a combustor positioned downstream from said diffuser and
an outer housing surrounding said combustor, said outer housing
being removably secured to the periphery of said first annular
element.
4. Apparatus as in claim 3 wherein the first element has a
periphery extending radially outward beyond the periphery of said
second annular elemennt, said annular outer housing being attached
to the periphery of said first element thereby forming an annular
flow path turning air discharged from said diffuser from a radial
to an axial direction.
5. Apparatus as in claim 4 wherein said second element has an aft
flange and a curved lip positioned inward from said annular outer
housing thereby defining, in part, said annular flow turning
passage.
6. Apparatus as in claim 1 wherein said second annular element is a
unitary piece of material having said passages formed in one face
as a series of tangentially directed channels separated by
generally wedge-shaped segments forming, in combination with the
face on said first element, passages having a generally rectangular
cross section.
7. Apparatus as in claim 6 further comprising means for releasably
holding said first and second annular elements against one
another.
8. Apparatus as in claim 7 wherein said releasable holding means
comprises a plurality of bolts extending through one and threaded
into the other of said elements.
9. Apparatus as in claim 6 wherein said second annular element is
cast and has a plurality of pockets formed in said wedge-shaped
portions, said pockets being opened to the face of said second
element that is opposite the face in contact with the annular face
on said first element.
Description
The present invention relates to compressor diffusers and more
particularly to compressor diffusers for radial-type
compressors.
One of the most important components of a centrifugal compressor is
the fixed diffuser section which receives the high velocity air
discharged from a rotating impeller. This component is designed to
diffuse the high velocity and increase its static pressure to a
level suitable for use in the combustor of a gas turbine. Many
different aerodynamic configurations have been proposed and adopted
in the past to give the most efficient performance possible for a
diffuser of this type.
One type of diffuser that is particularly advantageous is a
so-called channel diffuser in which a series of vanes, extending
between flangelike faces, form a series of tangentially directed
diffuser passages. This type of diffuser gives good performance but
it fails to provide sufficient divergence for the very high
pressure increases desired in an advanced gas turbine engine. In
addition, it is very expensive to manufacture and requires
time-consuming manufacturing techniques. The reason for this is
that each blade must be secured at its ends to both walls of the
diffuser by welding.
The above ends are solved in accordance with the present invention
by a compressor diffuser having a first annular element that has a
substantially smooth face defined by an inner and outer diameter.
The face is defined by straight-lined elements extending radially
from the inner to the outer diameter. A second annular element
abuts the face on the first element and has a plurality of
tangentially directed channels open to the face to form a series of
diffuser passages. The channels have an increasing cross-sectional
flow area defined by an increasing channel height and width so that
all of the divergence in the diffuser passages takes place in the
channels formed in the second element.
The above and other related features of the present invention will
be apparent from a reading of the following description of the
disclosure shown in the accompanying drawing and the novelty
thereof pointed out in the appended claims.
In the drawings:
FIG. 1 is a longitudinal, simplified section view of a gas turbine
engine which has a compressor diffuser embodying the present
invention;
FIG. 2 is an enlarged fragmentary cross-sectional view of the
diffuser of FIG. 1, taken on line 2--2 of FIG. 1; and
FIG. 3 is a fragmentary cross-sectional view of the diffuser of
FIG. 1, taken on line 3--3 of FIG. 2.
Referring to FIG. 1 there is shown a gas turbine engine comprising
an output gearbox 10 which supports an annular inlet housing 12.
Inlet housing 12 forms a bellmouth 14 to provide an annular inlet
for ambient air into a compressor 16. Compressor 16 comprises an
axially bladed hub 18, stator vanes 20 and a centrifugally bladed
impeller 22. Hub 18 and impeller 22 are mounted on a central shaft
24 journaled for rotation at its upstream end by bearing assembly
26. The compressor 16 pressurizes and accelerates air for discharge
radially outward through a compressor diffuser, generally indicated
at 28, whose construction will be described in detail below. Air
leaves the diffuser 28 with a substantially tangential component.
Vanes 29, secured between inner and outer annular duct walls 31,
33, turn air to an axial direction for discharge into a chamber 30.
Chamber 30 is formed by an outer housing 32 which mounts duct wall
33 and an inner cast strut assembly 34. A perforated combustor 36
in chamber 30 receives metered fuel from nozzles 38 for mixture
with air passing inward through the perforations. The mixture is
ignited by a suitable device and the resultant hot gas stream is
turned by a turbine inlet duct 40 for discharge from a turbine
inlet nozzle 42. The hot gas stream then passes across a bladed
turbine rotor 44 also secured to shaft 24. A bearing assembly 46,
supported by strut assembly 34, journals shaft 24 adjacent turbine
rotor 44. From there the hot gas stream passes across a bladed
power turbine rotor 48 which drives a gear set in the output box
through a power turbine shaft 50.
The diffuser 28 forms an extremely important component of the
engine. In accordance with the present invention it is constructed
in such a way that economical mass production is possible without
sacrificing excellent performance. The compressor diffuser 28
comprises a first annular element 52 secured to the annular inlet
housing 12 through an integral structural cone 54, as shown in FIG.
1. The element 52 has an integral outer flange 56 having a shoulder
58 which receives the forward end 60 of housing 32. Housing 32 is
secured to flange section 56 by a series of screws 62. Duct wall 33
is secured to housing 32 so that it is removed with housing 32.
Referring to FIG. 3, annular element 52 has a smooth aft-facing
surface 64 defined by an inner diameter D.sub.1 and an outer
diameter D.sub.2. The surface 64 is defined by straight-lined
elements extending radially between the inner and outer diameters.
Preferably, the surface 64 lies in a single plane at right angles
to the axis of rotation of the compressor. A second annular element
66 abuts the surface 64 and has an integral structural cone 68
forming a structural component of the engine and an integral outer
flange element 70 with a lip 72 defining an annular flow path
between the housing 32 and the lip for passage of air to chamber 30
(see FIG. 1). The element 66 has a section corresponding to surface
64 which has an inner diameter d.sub.1 and outer diameter d.sub.2
generally corresponding to those on surface 64. Inner diameters
D.sub.1 and d.sub.1 are spaced from the periphery of impeller 22 to
form a vaneless annular inlet 69. This inlet may have an area
controlled configuration, as disclosed in copending patent
application entitled "Compressor Diffuser Inlet," Ser. No. 420,203,
filed Nov. 29, 1973, T. Exley and C. Kuintzle inventors of common
assignment with the present application.
As shown particularly in FIG. 2, element 66 has a series of
channels 74 extending tangentially from the inner diameter d.sub.1.
These channels 74 each have a throat 76 at their inlet end, a first
diffusing section 78 and a second diffusing section 80. The throat
sections 76 are formed by a section of constant channel height and
width. The first diffusing section 78 is formed by a channel having
an expanding width and depth. The channel diffusing section 80 is
formed by an expanding channel depth and width which are greater
than that for the intermediate section 78. As is apparent from FIG.
2, section 80 has a channel width C.sub.w which increases toward
the downstream end of the passage. As is apparent from FIG. 3, the
channel depth C.sub.d also increases in the downstream
direction.
The result of forming channels 74 is a series of wedgelike sections
82 in between the channels 74 and having knife edge inlets 84. To
permit securing of element 66 to element 52 a series of threaded
holes 86 are provided in the wedge-shaped sections 82. These are
aligned with suitable holes in the element 52 to permit the
elements to be releasably secured by bolt assemblies 88. Holes 87,
passing through wedges and the corresponding section of annular
housing 52, provide access from one side of the diffuser to the
other. Threaded holes 89 enable additional bolt assemblies 91 to
hold the diffuser section together at that point and provide means
to attach other elements, such as a bleed air conduit.
Element 66 may also be provided with a series of pockets 90 formed
in the downstream section of wedge elements 82 and opening away
from the surface 64, as shown in FIG. 1. These pockets enable the
weight of the element 66 to be substantially reduced without
decreasing its strength.
The diffuser 28 is easily manufactured using mass production
techniques. Element 66 may be formed from a solid piece of material
or cast in rough form. The channels 74 may be formed to very
precise tolerances using standard milling techniques or
electrochemical discharge. Alternatively, the element 66 may be
cast from sintered material to produce the finished dimensions
without further machinery, except for the sharpening of leading
edges 84 on the wedges 82.
Once the passages are formed the forwardly facing surfaces of the
wedge-shaped elements correspond to the plane of surface 64 and a
tight fit is permitted between the two elements. When the diffuser
is assembled by securing sections 52 and 66 together it is
incorporated as part of the engine structure. Element 52, in
addition to forming one portion of the diffuser, conveniently forms
a portion of the exterior of the engine housing. The flange 70 in
cooperation with the housing 32 conveniently forms a passage for
flow of air from the diffuser to the combustor chamber 30. A
diffuser of this type in operation is highly efficient since the
passageway geometry can be controlled to a high degree of
precision. At the same time the diffuser can be made using standard
mass production techniques, thereby significantly decreasing the
cost of an engine.
It should be noted that the degree of divergence for the above
diffuser is significantly greater than that for a prior art channel
diffuser. The reason is that the channels increase both in width
and depth while the conventional diffuser channel increases in
width only. Thus, a new dimension is available for providing
increased divergence.
While a preferred embodiment of the present invention has been
described, it should be apparent to those skilled in the art that
it may be practiced in other forms without departing from its
spirit and scope.
* * * * *