U.S. patent number 3,867,068 [Application Number 05/346,422] was granted by the patent office on 1975-02-18 for turbomachinery blade cooling insert retainers.
This patent grant is currently assigned to General Electric Company. Invention is credited to Charles E. Corrigan, Robert J. Corsmeier, Ronald E. Dennis.
United States Patent |
3,867,068 |
Corsmeier , et al. |
February 18, 1975 |
Turbomachinery blade cooling insert retainers
Abstract
An improved turbomachinery blade includes impingement inserts
adapted to direct a coolant toward surfaces defining an internal
cavity within the blade. The inserts are provided with means which
mechanically secure the inserts in place within the cavity. The
securing means include a bushing having flanges of approximately
the same thickness as that of the side walls of the insert, which
flanges are secured within openings provided in such side walls
near the bottom end of the inserts. A pin is inserted within holes
provided in the root portion of the blade and a hole extending
through the bushing, which is aligned with the holes in the root
portion of the blade, and a collar of braze alloy is positioned
around each end of the pin, thereby fluidically sealing each end of
the pin and the insert and securing the pin to the blade and the
insert in place within the cavity.
Inventors: |
Corsmeier; Robert J.
(Cincinnati, OH), Corrigan; Charles E. (Cincinnati, OH),
Dennis; Ronald E. (Cincinnati, OH) |
Assignee: |
General Electric Company
(Cincinnati, OH)
|
Family
ID: |
23359308 |
Appl.
No.: |
05/346,422 |
Filed: |
March 30, 1973 |
Current U.S.
Class: |
416/97R;
416/96A |
Current CPC
Class: |
F01D
5/147 (20130101); F01D 5/189 (20130101); F05D
2260/201 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); F01D 5/14 (20060101); F01d
005/18 () |
Field of
Search: |
;416/92,95,96,97 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Powell, Jr.; Everette A.
Attorney, Agent or Firm: Lawrence; Derek P. Sachs; Lee
H.
Claims
1. In a turbomachinery blade of the type including a root portion,
a blade platform, a hollow body portion defining an internal
cavity, at least one thin-walled, hollow insert adapted to be
positioned within said hollow body portion, and means for
delivering a coolant to the interior of said insert, the
improvement comprising:
means for mechanically securing said insert to said hollow body
portion, said securing means including a bushing adapted to be
secured to said insert, and pin means adapted to be secured to both
said bushing and to
2. The improved blade of claim 1 wherein said insert comprises an
impingement insert having an inlet at one end thereof and a
multiplicity of relatively small holes therethrough which are
directed toward surfaces defining said cavity and are adapted to
impinge cooling air thereagainst.
3. The improved blade of claim 2 wherein said bushing is adapted to
be positioned within said inlet, and said bushing includes at least
one flange of approximately the same thickness as that of said
insert wall,
4. The improved blade of claim 3 wherein said bushing includes a
second flange of approximately the same thickness as that of said
insert wall, said wall includes a second opening for receiving said
second flange and said first and second flanges are adapted to be
secured to said insert
5. The improved blade of claim 3 wherein said insert includes a
base end which defines said inlet, and said base end is sized so as
to provide a slight gap between side walls of said internal cavity
and said base end,
6. The improved blade of claim 2 wherein said bushing comprises a
sleeve adapted to be positioned within said inlet, and said sleeve
is adapted to
7. A turbomachinery blade comprising a root portion, an
airfoil-shaped, hollow body portion defining an internal cavity
therein, a blade platform separating said root portion and said
hollow body portion and defining the inner bounds of said airfoil,
at least one thin-walled, hollow insert positioned within said
hollow body portion, passage means adapted to deliver a coolant to
the interior of said insert, and means for mechanically securing
said insert in a position within said internal cavity, said
securing means including a bushing adapted to be secured to said
insert and pin means adapted to be secured to both said bushing
and
8. The turbomachinery blade recited in claim 7 wherein said insert
comprises an impingement insert having an inlet at one end thereof
and a multiplicity of relatively small holes therethrough which are
directed toward surfaces defining said cavity and are adapted to
impinge cooling
9. The turbomachinery blade recited in claim 8 wherein said bushing
includes at least one flange of approximately the same thickness as
that of said insert wall, said wall includes an opening for
receiving said flange, and said blade further includes means for
securing said flange in
10. The turbomachinery blade recited in claim 9 wherein said
bushing includes a second flange of approximately the same
thickness as that of said insert wall, said wall includes a second
opening for receiving said second flange, and means for securing
said second flange in said second
11. The turbomachinery blade recited in claim 9 wherein said
bushing includes an inner spool, and said spool is adapted to
extend across said
12. The turbomachinery blade recited in claim 11 wherein said
spool
13. The turbomachinery blade recited in claim 8 further including
means for dividing said internal cavity into at least two separate
cavities, each of said cavities is provided with one of said
impingement inserts, and each of said cavities includes means for
mechanically securing said insert to
14. The turbomachinery blade recited in claim 9 wherein said root
portion of said blade includes at least one hole, said bushing
includes at least one hole adapted to align with said hole in said
root portion, and said pin means comprise a pin adapted to be
positioned within each of said
15. The improved turbomachinery blade recited in claim 14 wherein
said hole in said root portion is slightly larger than the outer
diameter of said pin and a braze collar is positioned within the
gap between said pin and said hole.
Description
BACKGROUND OF THE INVENTION
This invention relates generally to gas turbine engines and, more
particularly, to an improved fluid cooled turbomachinery blade
structure for use in high temperature gas turbines.
The invention herein described was made in the course of or under a
contract, or a subcontract thereunder, with the United States
Department of the Air Force.
It is well known that significant increases in gas turbine engine
performance, in terms of thrust or work output per unit of fluid
input, can be obtained by increasing the turbine inlet temperature
of the motive fluid or hot gas stream. It is also recognized that
one major limitation on turbine inlet temperature is that which is
imposed by the turbine blade temperature capability. In an effort
to extend turbine blade capabilities, numerous complex
turbomachinery blade structures have been proposed which employ one
or more modes of cooling using fluid extracted from the
compressor.
One such mode of cooling which is becoming increasingly popular is
the provision of impingement inserts within an internal cavity
defined by a hollow body portion of the turbomachinery blade.
Coolant is delivered to the interior of such an insert and is
expelled through a multiplicity of small holes against an internal
wall of the turbomachinery blade, thereby cooling the portion of
the turbomachinery blade which is exposed to the hot gas
stream.
As is further known to those skilled in the art, the overall weight
of a gas turbine engine, and in particular the thrust-to-weight
ratio of the engine, is one of the engine's most critical
characteristics. The weight of the turbine rotor assembly, like
that of any other turbomachinery component, must therefore be
maintained at the minimum practical levels obtainable. Not only
must the wall thickness of the hollow body portion of the blade
itself be maintained at a minimum thickness, but the wall thickness
of the impingement insert also must be maintained at minimum
practical levels. Wall thicknesses for such inserts on the order of
0.010 inch are becoming more and more prevalent. When one attempts
to secure such a thin insert to the turbomachinery blade, however,
problems arise due to the high centrifugal force asserted on such
an insert.
Prior attempts at securing such a blade insert in place have
included the provision of an enlarged flange formed integrally with
the insert at the bottom thereof and the further provision of a
load-bearing surface upon which such flange would rest. Such a
design is shown in U.S. Pat. No. 3,715,170 - Savage et al., which
patent is assigned to the same assignee as the present application.
Inserts provided with such a load-bearing flange have proven
extremely successful, but in many applications such a flange is not
practical. For example, as briefly mentioned above, due to the
increase in tip speed of newer turbine rotors, the blade must be
made as lightweight as possible to keep the disc size and weight at
a minimum. One method of keeping the blade weight low is to make
the airfoil walls as thin as possible. In designing such a blade, a
minimum practical wall thickness is chosen for the tip portion of
the blade, but the airfoil wall thickness must increase as it nears
the blade platform in order to carry the increasing load of the
airfoil. This centrifugal loading and the radial temperature
gradient of the airfoil combine to produce blades having walls that
are constant in thickness from the tip to a point above the pitch
line, thereafter increase in thickness to a short distance below
the pitch line, and then become essentially constant in thickness
to the airfoil root portion. With these changes in wall thickness,
the internal cavity formed by the hollow body portion of the blade
also changes in size, with a blade as described above providing a
bottle-shaped cavity with the largest opening being near the tip of
the blade.
As is well known to those skilled in the art, it is highly
desirable to provide a constant clearance between the impingement
inserts and the inner wall of the blade. To install a baffle from
the root end of the blade would be virtually impossible if such a
specified clearance must be maintained between the baffle and this
bottle-shaped cavity. Support embossments located on the exterior
of the inserts further hinder the assembly. To further complicate
matters, many airfoil portions are twisted. Since the impingement
inserts cannot be installed from the root end of the airfoil, they
must necessarily be installed from the blade tip end; and, this
makes it virtually impossible to utilize an insert having an
enlarged load-bearing flange at its inner end.
Attempts have also been made in the past to pin the bottle-shaped
inserts in place, but the base wall thickness of 0.010-0.020 inch
provides insufficient strength to withstand the loads imposed by
the pins due to the centrifugal force exerted on the blade and
insert during normal operation of the gas turbine. Another
alternative is to braze the insert directly to the blade member,
but the location of the braze joint in an area of only limited
access makes it difficult to properly place the braze and to
inspect the joint.
SUMMARY OF THE INVENTION
It is an object of this invention, therefore, to provide a means
for mechanically securing a cooling insert in a turbine blade which
means overcomes the above-described problems associated with prior
art designs. It is a further object to provide such a positive
mechanical securing means which does not substantially interfere
with the coolant flow, is easy to assemble, and substantially
eliminates leakage of coolant.
Briefly stated, the above objects are attained in the present
instance by providing an insert which includes an opening which is
drilled or punched through both sides thereof near the bottom end
thereof. A grommettype bushing is placed in the openings and
secured to both sides of the insert. A hole is then drilled through
the bushing and the insert is pushed into the blade internal cavity
until the hole in the bushing lines up with suitable holes in the
shank portion of the blade. A pin is then inserted into the aligned
holes and braze alloy is placed around each end of the pin and the
insert base in order to seal the ends of the pin and the insert
base and retain the pin in place. The bushing is provided with
flanges of approximately the same thickness as that of the walls of
the insert so as to lend itself to an optimum weldment.
DESCRIPTION OF THE DRAWINGS
While the specification concludes with a series of claims which
distinctly claim and particularly point out the subject matter
which Applicants consider to be their invention, a complete
understanding of such invention will be obtained from the following
detailed description, which is given in connection with the
accompanying drawings, in which:
FIG. 1 is a partial, cross-sectional view diagrammatically showing
one installation of the inventive insert retaining means of the
present invention;
FIG. 2 is a cross-sectional view taken along line 2--2 of FIG.
1;
FIG. 3 is a cross-sectional view taken along line 3--3 of FIG.
1;
FIG. 4 is an enlarged, partial, cross-sectional view showing the
details of a portion of FIG. 1;
FIG. 5 is a partial, sectional view of an alternative retaining
means;
FIG. 6 is a cross-sectional view taken generally along line 6--6 of
FIG. 5;
FIG. 7 is an axial cross-sectional view of a second alternative
retaining means;
FIG. 8 is a cross-sectional view, with portion deleted, taken
generally along line 8--8 of FIG. 7;
FIG. 9 is a partial sectional view, similar to FIG. 5, of another
alternative embodiment; and
FIG. 10 is a cross-sectional view, with portions deleted, taken
generally along line 10--10 of FIG. 9.
DESCRIPTION OF A PREFERRED EMBODIMENT
Referring to the drawings wherein like numerals correspond to like
elements throughout, attention is directed initially to FIGS. 1
through 4 wherein a turbomachinery blade incorporating the present
inventive insert retaining means is generally designated by the
numeral 10. The blade 10 includes a root portion 12 which provides
a pair of tangs 14 adapted to mount within a dovetail slot (not
shown) associated with a gas turbine rotor disc (not shown). The
blade 10 further includes an airfoil-shaped, hollow body portion 16
which is separated from the root portion 12 by means of a blade
platform 18.
The airfoil-shaped, hollow body portion 16 includes a leading edge
20 and a trailing edge 22 and a pair of airfoil-shaped side walls
24 and 26 extending therebetween which are suitably formed and
adapted to extract energy from a motive fluid flowing thereacross.
The side walls 24 and 26 cooperate to define an internal cavity 28
which, in the present instance, is divided into two separate
sections, leading edge cavity 30 and trailing edge cavity 32 by
means of a rib member 34, which is formed integrally with hollow
body portion 16 and extends between the side walls 24 and 26.
As most clearly shown in FIG. 2, the side walls 24 and 26 vary in
thickness from a relatively thin cross section near the tip of the
hollow body portion 16 to a thicker cross section near the blade
platform 18. As a result of this varying thickness, the leading
edge cavity 30 and the trailing edge cavity 32 are bottle-shaped
cavities which are wider near the tip end of the hollow body
portion 16 than near the blade platform 18.
As further shown in FIGS. 1 and 2, a thin sheet metal impingement
insert 36 is positioned within the leading edge cavity 30, while a
similar impingement insert 38 is located within the trailing edge
cavity 32. Each of the inserts 36 and 38 is shown as being a
thin-walled shell having side walls 40 and 42 generally conforming
to the blade side walls 24 and 26. The side walls 40 and 42 are
formed with a plurality of nozzles or apertures 44 which are
disposed in spaced relationship to the inner surfaces of the
cavities 30 and 32 by suitable spacing means 46. As best shown in
FIG. 2, the inserts 36 and 38 are closed at one end 48 and define a
chamber 50 therein which is open at end 52 to receive coolant
fluid.
In order to direct the coolant fluid into the chambers 50, suitable
passage means 54 are provided in the root portion 12 of the blade
10. Furthermore, the open or base end 52 of the inserts 36 and 38
are sized so as to sealingly engage side walls 56 located near the
top of the passage means 54. As described in greater detail
hereafter, the joint between the base end 52 and the side walls 56
can be filled with a braze alloy to further seal this joint. In
this manner, coolant delivered through the passage means 54 is
directed to the chamber 50 and thus to the plurality of apertures
or nozzles 44 and is not permitted to pass around the open ends 52
of the inserts 36 and 38 directly into the cavities 30 and 32. The
coolant fluid, in passing through the apertures 44, impinges
directly on the inner sides of the leading edge 20 and the side
walls 24 and 26 of the blade 10, thereby cooling such walls in a
known manner. The coolant fluid in the leading edge cavity 30 then
exits through openings 60 (one of which is shown in FIG. 1)
provided in a tip cap 62, which defines the outer end of the
cavities 30 and 32, and through film openings (not shown) in the
hollow body portion 16, while the coolant fluid in the trailing
edge cavity 32 exits through openings in the tip cap and through
trailing edge slots 64 located in the trailing edge 22 of the blade
10.
Referring still to FIGS. 1 through 4, means are provided for
mechanically securing the inserts 36 and 38 into the position shown
in FIG. 1. The means for mechanically securing the inserts in place
are generally designated by the numeral 66 and include a
grommet-type bushing 68 which is positioned within openings 70 and
72 located in the side walls 40 and 42 of the inserts 36 and 38.
Since the means for mechanically securing the inserts 36 and 38 in
place are substantially identical, only the structure associated
with the insert 36 will be described.
As best shown in FIGS. 3 and 4, the bushing 68 includes a pair of
thin flanges 74 and 76 which are interconnected by means of an
inner spool 78. The flanges 74 and 76 are sized so as to correspond
in shape to that of the openings 70 and 72 associated with the side
walls 40 and 42. In the embodiment shown in FIGS. 1 through 4, the
openings 70 and 72 are made to an approximately circular
configuration, although other configurations would also be
suitable. Furthermore, as clearly shown in FIG. 3, the flanges 74
and 76 are made of approximately the same thickness as that of the
side walls 40 and 42 so as to provide a configuration which lends
itself to an optimum weldment. In addition, the openings 70 and 72
provide a much larger perimeter than that of the inner spool 78 so
as to provide a large weld area which further enhances the strength
of the weldment.
As best shown in FIGS. 3 and 4, the inner spool 78 is provided with
a pair of flats 80 and 82 which extend parallel to the side walls
56 of the passage means 54 when the flanges 74 and 76 are
positioned within the openings 70 and 72. In this manner, the flats
80 and 82 permit the correct volume of air to pass through the open
end 52 and into the chamber 50 of the insert 36.
Prior to assembling the insert 36 into the blade 10, the bushing 68
is positioned within the insert and is welded in place. A hole 84
is then drilled through the center of the bushing 68, and the
insert 36 is positioned within the hollow body portion 16 of the
blade 10 through the open end thereof. The hole 84 is aligned with
a pair of holes 86 and 88 located within the root portion 12 of the
blade 10. A pin 90 is then inserted through the holes 84, 86 and
88, as shown in FIG. 3.
The holes 86 and 88 in the root portion of the blade 10 are made
oversized with respect to the diameter of the pin 90 so as to allow
for the tolerance build-up of the various parts and also the
placement of a braze collar around the ends of the pin 90. The hole
84 is sized so as to fit relatively securely around the pin 90 so
as to provide accurate placement of the insert 36 within the hollow
body portion 16. The braze alloy collar which is placed around both
ends of the pin 90 not only secures the pin 90 to the root portion
12 of the blade but also acts as a seal which precludes the flow of
coolant around the pin 90 before it enters the chamber 50
associated with the insert 36. Furthermore, if desired, the base
end 52 of the insert can be sized so as to provide a slight gap
between the outer wall of the insert 36 and the side walls 56 of
the blade. In such a case, the braze not only seals the pins 90 but
also flows into the gap between the insert and the wall 56 and
effectively seals this gap. In this manner, all coolant which flows
through the passage means 54 must flow into the chamber 50
associated with one of the inserts 36 or 38.
In assembling the inserts into the blade, once the inserts 36 and
38 are positioned within the hollow body portion 16 and the pins 90
are located within the holes 84, 86 and 88, the braze alloy is
placed around each of the pins 90. The tip cap 62 is then located
in place, a suitable braze alloy is applied to the tip cap 62, and
the entire blade is then heated which causes the braze alloy to
melt, thereby sealing each end of the pins 90 and the base ends of
the inserts in addition to securing the pins 90 and the tip cap 62
in their respective positions.
Referring now to FIGS. 5 through 10, a number of alternative
embodiments of the mechanical securing means for cooling inserts
are shown. As shown in FIGS. 5 and 6, a bushing 94 having a pair of
relatively elongated flanges 96 and 98 could be utilized in place
of the bushing 68. In such a case, the flanges could extend down to
the open end of the insert. An inner spool 100 interconnects the
flanges 96 and 98, and, if desired, flats 102 and 104 can be
provided on either side of the spool 100. As was the case of the
bushing 68, once the bushing 94 is welded to the insert 36, a hole
106 is drilled therethrough and a pin 108 is positioned therein in
such a manner as to secure insert 36' to the blade 10.
As shown in FIGS. 7 and 8, in certain applications a bushing 110 is
designed to fit within the open end 52 of the insert 36. In such a
case, the bushing 110 would have an outer contour shaped in the
form of an airfoil and sized so as to fit within an insert 36". The
bushing 110 would be hollow and would provide a passageway 112 for
the flow of coolant into a chamber 50" of the insert 36".
In assembling the insert 36 into the blade, the bushing 110 could
be initially brazed in place within the insert 36", and the insert
36" thereafter positioned within the blade 10. Holes 114 and 116
could then be drilled through the root portion 12 and each side of
the insert 36. Pins 118 and 120 would then be positioned within the
holes 114 and 116 and would act to secure the bushing 110 and,
thus, the insert 36" in place.
While the bushing 68 described in connection with FIGS. 1 through 4
provides an extremely secure assembly, in certain applications a
simple cylindrical collar or a tear-shaped bushing such as that
shown at 130 in FIGS. 9 and 10 may be all that is required to
secure the insert in place. In such a case, the bushing 130 would
be welded or brazed to the inner sides of the insert 36'" and a
hole 132 would be drilled through the insert 36'" and bushing 130.
Once the insert 36'" is positioned within the blade 10 a pin 134
would be inserted within the hole 132 and brazed in place as
described above.
While a number of suitable embodiments of Applicants' inventive
means for securing cooling inserts to the interior of gas turbine
blades have been described, it should be readily apparent to those
skilled in the art that slight modifications could be made in these
embodiments without departing from the broader inventive concepts
described herein. For example, while each of the above embodiments
is described in connection with an open-ended blade and a removable
tip cap, the inventive securing means could be readily adapted for
use in applications wherein the inserts are inserted through the
dovetail portion of the blade. Similarly, the shape of the flanges
74 and 76 can be readily changed without departing from the broad
inventive concepts. For this reason, the appended claims are
intended to cover these and all similar modifications which fall
within the scope of the invention.
* * * * *