U.S. patent number 3,751,180 [Application Number 05/159,879] was granted by the patent office on 1973-08-07 for vane rings.
This patent grant is currently assigned to United Aircraft of Canada Limited. Invention is credited to James MacDonald Cameron.
United States Patent |
3,751,180 |
Cameron |
August 7, 1973 |
VANE RINGS
Abstract
One piece cast metal vane rings of the same shroud diameter and
number of vanes but of different throat areas are made using a
pattern assembled from several pattern pieces in which the vanes
have different angles to the axis of the vane ring shroud. A set of
pattern pieces of two or three different angles can thus provide
for a number of different throat areas, thus avoiding having to
prepare, in a large number of different sizes, expensive molds for
making pattern pieces for molds of the same diameter but differing
throat areas.
Inventors: |
Cameron; James MacDonald (St.
Lambert, Quebec, CA) |
Assignee: |
United Aircraft of Canada
Limited (Longueuil, Quebec, CA)
|
Family
ID: |
10481339 |
Appl.
No.: |
05/159,879 |
Filed: |
July 6, 1971 |
Foreign Application Priority Data
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Dec 8, 1970 [GB] |
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58,329/70 |
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Current U.S.
Class: |
415/195; 415/915;
415/208.1 |
Current CPC
Class: |
F01D
9/041 (20130101); Y10S 415/915 (20130101) |
Current International
Class: |
F01D
9/04 (20060101); F01d 009/02 () |
Field of
Search: |
;415/119,195,216,217
;416/223,216,217 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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|
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766,812 |
|
Jan 1957 |
|
GB |
|
11,890 |
|
1911 |
|
GB |
|
568,402 |
|
Jan 1933 |
|
DD |
|
Primary Examiner: Raduazo; Henry F.
Claims
I claim:
1. A one-piece cast metal gas-turbine vane ring, comprising,
spaced apart inner and outer annular shrouds having a common axis
extending therebetween,
a plurality of substantially equally spaced apart vanes of the same
size, shape and aerodynamic characteristics,
said vanes being inclined at a generally common angle to said axis
and having respective trailing edges lying close to a plane
perpendicular to said axis with each pair of vanes providing
therebetween a passage having a particular throat area,
at least one of said vanes being inclined at a specific minimum
angle to said axis and at least one other blade being inclined at a
specific maximum angle to said axis such that the difference
between the total throat area of the vane ring if all the blades
were at said minimum angle and the total throat area of the vane
ring if all the blades were at said maximum angle would be not less
than 1 percent and not more than 4-1/2 percent in the total throat
area variation.
2. A metal vane ring, as defined in claim 1, in which there are
vanes having at least three different angles.
3. A metal vane ring, as defined in claim 1, in which said maximum
and minimum angles are such that the difference between the total
throat area of the vane ring if all the blades were at said minimum
angle and the total throat area of the vane ring if all the blades
were at said maximum angle would be not less than 2 percent and not
more than 4-1/2 percent in the total throat area variation.
4. A metal vane ring, as defined in claim 1, in which there is at
least one vane set at an angle intermediate to said maximum and
minimum angles.
Description
BACKGROUND OF THE INVENTION
This invention relates to one-piece cast metal vane rings and their
manufacture.
FIELD OF THE INVENTION
The vane ring is used in the gas turbine engine to direct the
exhaust gases coming from the combustion chamber of the engine onto
the turbine blades. Such a ring is located, as a stator, between
the combustion chamber and the first stage turbine and between each
subsequent turbine stage.
The vane rings are made up of inner and outer cylindrical shrouds
intervened by an annulus containing a number of vanes inclined to
the axis and equally spaced apart circumferentially so that between
each pair there is a converging passage whose minimum
cross-sectional area is called the throat area substantially equal
to the other throat areas. The sum of the throat areas of the vane
rings (called the total throat area) determines the amount of air
the ring is adapted to pass.
DESCRIPTION OF THE PRIOR ART
Different engines of the same model have different total throat
area requirements. So, it is necessary for an engine manufacturer
to provide a number of vane rings of the same circumference, having
different total throat areas.
One-piece cast metal vane rings, of the type to which the invention
applies, are made by casting them in one piece by the lost wax
process. A number of different tools are required to make the wax
or plastic pattern, and each time a change is made in total throat
area, a new set of tools is required. For example, as many as seven
tools have been required to obtain the optimum total throat area
for a particular engine model while under development and in
production.
SUMMARY OF THE INVENTION
The applicatn has now developed a vane ring design which can be
produced with a limited number of tools, while providing a large
variety of total throat areas in a vane ring of the same
circumference. In this design, instead of the respective throat
areas between each pair of blades being equal as in the prior art,
there are at least two different throat areas, but the total throat
area provides the total throat area required of the particular
engine.
This is effected, according to the invention, as follows. Some of
the vanes are at a different angle from the axis of the engine to
other vanes, so that the trailing edges of some of the vanes are
offset from a plane perpendicular to the axis of the engine as
compared with the trailing edges of adjacent vanes. Through this
arrangement throat areas of different dimensions result. The total
throat area is thus changed by a small increment for each vane
arranged at a different angle. This design, as will be seen,
greatly facilitates manufacture of vane rings of the same
circumference, having different total throat areas, which can be
matched with different throat area requirements of the engine model
to which the vane rings are fitted.
In making a vane ring according to prior art, a composite wax
assembly is first made by assembling together, in a holder, a
plurality of separate, but identical, wax or plastic patterns, in a
manner well known. The wax patterns are made by first preparing an
expensive steel mold of the desired size and shape. An assembly
fixture also has to be made. According to this procedure each time
a change in total throat area has to be made, a new set of
identical patterns is required. These have to be prepared by first
making a new steel mold to be used in the procedure described.
In accordance with the present invention at least two different
patterns are made to provide, in turn, at least two different
throat areas such that, when the patterns are assembled together to
form the ring pattern, a predetermined total throat area is
provided. By varying the number of patterns of each angle making up
the composite ring pattern, a number of different total throat
areas are possible by selecting different numbers of each vane
angle pattern. By providing more than two different patterns having
respectively different angles from the axis of the engine, a still
greater number of different total throat areas can be provided to
reduce considerably the number of expensive steel molds needed to
vary the total throat area of a ring of a given circumference, for
various engine throat area requirements. The different air foil
waxes or plastic pieces are arranged so that the same assembly
fixture can be used.
BRIEF DESCRIPTION OF THE DRAWING
Having thus generally described the invention, it will be referred
to, in more detail, by reference to the accompanying drawings,
illustrating preferred embodiments, and in which:
FIG. 1 is a front view of a vane ring showing the leading
edges;
FIG. 2 is a rear view of a vane ring showing the trailing
edges;
FIG. 3 is a cross-section along lines 3--3 of FIG. 1;
FIG. 4 is an elevation showing two wax or plastic pattern pieces,
fitted together in a sub-assembly as they are in a pattern;
FIG. 5 is a front perspective view of the assembly shown in FIG.
4.
DESCRIPTION OF THE PREFERRED EMBODIMENTS
Referring more particularly to the drawings, FIG. 1 shows a special
high temperature resistant alloy cast vane ring A made up of an
outer shroud 15 and an inner shroud 17 forming therebetween an
annulus. Within the annulus, and extending between the shrouds 15
and 17, and integrally connected thereto are a number of spaced
apart vanes 19, 21, 23, 25, etc. having respective leading edges
19a, 21a, etc. and trailing edges 19b, 21b, etc. The trailing edge
of the inner shroud 17 is shown as 17a. The edge 17a is
perpendicular to the axis of the vane ring. Adjacent vanes, for
example, as demonstrated by the vanes 19 and 21 (FIG. 3) enclose a
throat area as indicated by an arrow 22, and the adjacent vanes 21
and 23 enclose a throat area as indicated by arrow 24, while the
throat area between the adjacent vanes 23 and 25 is indicated by
the arrow 26.
In accordance with the invention, the throat areas vary between
certain pairs of vanes. This is accomplished in accordance with the
present invention by varying the inclination or angle of certain of
the vanes as compared with other vanes as indicated
diagrammatically (exaggerated) in FIG. 3 in connection with the
blades 19 and 21 so that the passage between the vanes is of a
different minimum cross-section or throat area from that between
vanes 21 and 23. The inclination of the individual vane is varied
about a pivot point, for example shown at X on a plane parallel to
the trailing edge 17a of the shroud 17. In FIG. 3 the vane 19 is
shown pivoted counterclockwise about the point X as compared to the
vanes 21 and 23 so its trailing edge 19b is slightly out of the
plane of the trailing edges 21b and 23b. It will be noted, from the
drawing, that the trailing edge 19b of the blade 19 is raised
relative to the trailing edge 17a of the inner shroud 17, as
compared with the trailing edges 21b and 23b. Likewise, the leading
edge 19a is lower than the leading edges 21a and 23a. Consequently,
the width of the passage between the blades 19 and 21, as shown by
the arrow 22, is less than the width of either of the passages
between the pairs of vanes 21, 23 and 23, 25 respectively, as
indicated by the arrows 24 and 26. So the throat area between the
vanes 19 and 21 is smaller than that between the vanes 21 and
23.
The vane ring A is made by assembling wax or plastic pieces 28, 30,
etc. and fitting them together in a fixture to produce the ring
pattern which is invested with a skin of a material which becomes
the mold, as is well known in the investment casting art. Two
pattern pieces are shown fitted together in a sub-assembly B. The
fully assembled pattern is of the same shape as the vane ring to be
cast. According to the invention, a plurality of different shaped
pattern pieces are made, that is to say pieces in which the
inclination of certain of the vanes differs from that of other
vanes. A preferred number of patterns is three, one having a
maximum vane inclination, a second, a minimum inclination and the
third an intermediate inclination. What is meant by different
shaped composite patterns is patterns which have at least two
different vane angles and consequently provide different throat
areas between vanes.
A typical example of a vane ring A is as follows. The inner shroud
17 is 9 inches and the outer shroud 15 12 inches in outside
diameter. The vanes are approximately 1 and 1/2 inches in radial
height. The required total throat area is 13.333 square inches. The
ring A has 15 vanes. Vanes 19 and 21 of different angles are used.
The angles of vanes 19 and 21 are such that 15 vanes would provide
a total throat area of 13.035 square inches using vane 19 alonge
and 13.630 square inches for using vane 21 alone. One assembly,
using eight of vane 19 and seven of vane 21 generated a total
throat area of 13.31 square inches. Another assembly also made up
of eight vanes 19 and seven vanes 21 generated a total throat area
of 13.35 square inches. This variation is within an acceptable
tolerance for total throat areas, since even when making one piece
cast metal vane rings by the conventional method, there is always a
certain difference in total throat area, resulting from unavoidable
slight variations in the assembly technique. This variation in
total throat area is normally acceptable when within a .+-. 1
percent tolerance. The percentage throat area difference between a
ring made up entirely of vanes having the maximum angle of the vane
19 to the axis of the ring and a ring made up entirely of vanes 21
having a minimum angle to the axis of the ring is between about 4
percent and about 4-1/2 percent total throat area variation. In
other words, the mixing of wax or plastic pieces with vanes at
different angles permits this relatively wide range of variation in
total throat area.
According to the invention, then, the intentional or built-in
variation between the two or more different vane angles is
considerably greater than any difference which may occur
accidentally, even though the variation is quite small. But, the
built-in variation is great enough that a plurality of patterns,
having different vane angles, can be assembled to provide for a
number of different total throat areas, ranging from the total
provided by using all patterns of the same angle which would
provide the minimum total throat area to the total which provided
using all patterns which would provide the maximum throat area. A
great number of inbetween variations are possible by different
combinations of the respective patterns.
The materials employed in making the vane rings of the invention
are well known in the art. For example, the vane ring itself is
preferably of a special high temperature resistant alloy. The
materials used in the investment casting process are also well
known in the investment casting art as are the techniques used. One
technique has been used to illustrate the invention and is
preferred, but other techniques can equally be used.
The principle of the invention then is to "classify" each
individual vane in its pre-investment form (wax or plastic model),
select an appropriate vane class, mix and distribution, assemble,
invest, etc. and cast. This effectively duplicates the procedure
used with individual vane segments prior to the introduction of the
integral vane ring. By selecting at least two vane angles,
preferably at least three vane angles, a wide selection of total
throat areas can be produced. By stocking wax or plastic pieces of
different vane angles, the time required to obtain a new vane ring
class can be greatly reduced, as it is only necessary to assemble,
cast and machine.
* * * * *