U.S. patent number 3,574,924 [Application Number 04/771,220] was granted by the patent office on 1971-04-13 for solid state repair method and means.
This patent grant is currently assigned to North American Rockwell Corporation. Invention is credited to Gordon L. Dibble.
United States Patent |
3,574,924 |
Dibble |
April 13, 1971 |
SOLID STATE REPAIR METHOD AND MEANS
Abstract
A method of rebuilding a jet engine compressor, fan, or turbine
blade containing a worn or damaged area by trimming off the portion
of such blade surrounding the area and replacing such portion with
another of precisely corresponding size and metallurgical
composition. Standardized templates define the size of the trimmed
off portion. The replaced portion is integrally joined to the blade
by solid state molecular diffusion bonding in a mold exactly
duplicating the contour of the original blade when new.
Inventors: |
Dibble; Gordon L. (Fontana,
CA) |
Assignee: |
North American Rockwell
Corporation (N/A)
|
Family
ID: |
25091105 |
Appl.
No.: |
04/771,220 |
Filed: |
October 28, 1968 |
Current U.S.
Class: |
228/119;
228/173.2; 228/193; 416/213R; 416/224; 228/262.71; 29/402.13 |
Current CPC
Class: |
B22D
19/10 (20130101); F01D 5/005 (20130101); Y02T
50/673 (20130101); Y02T 50/671 (20130101); Y10T
29/49737 (20150115); Y02T 50/60 (20130101) |
Current International
Class: |
F01D
5/00 (20060101); B22D 19/10 (20060101); B22d
019/10 (); B23p 007/00 () |
Field of
Search: |
;29/401,475,156.8 (B)/
;29/493,498,402,198,504 ;52/514 |
References Cited
[Referenced By]
U.S. Patent Documents
Primary Examiner: Campbell; John F.
Assistant Examiner: DiPalma; Victor A.
Claims
I claim:
1. A method of repairing a worn or damaged metallic article,
comprising the steps of:
providing a pair of mating dies, the workfaces of which are adapted
to define a cavity having the precise size and shape of said
article in the new and undamaged condition when said dies are in
mating relationship;
removing a portion of said article to create a vacant area thereon,
said portion including the worn or damaged area of said
article;
placing said article in said dies with at least one separate
incremental mass positioned in said vacant area, said mass being of
the same material as said article, the volumetric content of said
mass being at least equal to the volume of the void formed by said
vacant area in said cavity when said dies are in mating
relationship; and
applying sufficient heat and pressure to said dies to cause said
mass both to deform into conformity with said void and to join said
article by solid-state molecular diffusion bonding
therebetween.
2. The method set forth in claim 1 above, further including, prior
to said removing step:
providing at least one template for mass production use on a
plurality of damaged articles corresponding generally with said
damaged article;
placing said template in close proximity to said damaged article
over said damaged area; and
tracing said template on said article to define said vacant area
whereby said removed portion corresponds in plan view with said
template.
3. The method set forth in claim 1 above wherein:
said mass has a volumetric content from 0.01 to 10.0 percent larger
than said volume of said void.
4. The method set forth in claim 1 above wherein:
said metallic article is made of Ti-6A1-4V titanium alloy; and
said heat and pressure are from about 1600.degree. to 1725.degree.
F. and from 2000 to 5000 p.s.i., respectively.
5. The method set forth in claim 4 above, wherein:
said dies containing said article and said mass are positioned
within an airtight retort; and
a vacuum is maintained in said retort continuously during
application of said heat and pressure.
6. A mass-production method for repairing a multitude of worn or
damaged metallic articles having identical design but a variety of
different types and locations of wear or damage, comprising the
steps of:
forming a plurality of standardized templates having predetermined
area dimensions;
prefabricating a plurality of incremental masses corresponding in
area with said area dimensions of said templates;
removing portions of said articles, said removed portions
containing said worn or damaged areas and corresponding in area
with said templates;
placing said masses in the voids resulting in said articles from
removal of said portions; and
joining said masses to said articles by solid-state molecular
diffusion bonding therebetween.
7. The method set forth in claim 6 above, wherein:
said bonding is accomplished by the steps of placing said
individual articles together with said masses between a pair of
mating dies defining a cavity having the contour of said articles
in the undamaged condition;
heating said dies and said articles to a temperature sufficient for
said bonding to occur at a coordinated pressure; and
applying said pressure to said dies to compress said articles
therebetween until said bonding occurs.
8. The method set forth in claim 6 above, wherein:
said masses have a total volumetric content from 0.01 to 10.0
percent larger than the total volumetric content of said removed
portions.
9. The method of mass production rebuilding a plurality of worn or
damaged metallic articles of identical design, comprising the steps
of:
forming a plurality of standardized templates having predetermined
plan area dimensions;
prefabricating a plurality of incremental masses corresponding in
plan view with said templates;
trimming said articles to remove portions therefrom, said removed
portions containing said worn or damaged locations and
corresponding in plan area with said templates;
providing a pair of mating dies, the workfaces of which are adapted
to define a cavity having the precise size and shape of said
articles in the new or undamaged condition when said dies are in
fully mated relationship;
successively placing each of said trimmed articles between said
dies with a plurality of said masses positioned in the vacant areas
resulting in said articles from removal of said portions therefrom,
said masses being of the same material as said articles, the
volumetric content of said masses in combination being at least
equal to the volume of the voids formed in said cavity due to
removal of said portions when said dies contain said trimmed
articles and are in fully mated relationship;
surrounding said dies with an airtight retort;
maintaining a vacuum within said retort;
heating said retort and its contents to a temperature sufficient
for solid-state molecular diffusion bonding between said
incremental masses and said trimmed articles;
applying sufficient pressure to said dies to compress said articles
and masses therebetween in an amount sufficient to deform said
masses into conformity with said cavity and to achieve said
diffusion bonding; and
said masses having an initial combined volumetric content from 0.01
to 10.0 percent larger than said volume of said voids in said
cavity resulting from said removal of said portions.
Description
BACKGROUND OF THE INVENTION
Engines of turbojet or turbofan-type such as used in modern
military and commercial aircraft contain many compressor and
turbine blades, each of which is precision formed. Engine
performance and reliability depend directly upon the detailed
design contour and structural integrity of these blades. In axial
flow compressors of some jet engines, as many as 20 stages of
compression are accomplished by a corresponding number of blade
rows, each containing from 50 to 150 individual blades. The moving
rows are separated by stationary alternate rows in close proximity,
whereby dimensional accuracy of the blades is crucially important.
Similarly, in turbofan engines, each individual blade is contoured
for maximum efficiency at the design rotation speed, whereby the
angle of attack at each radial location along the blade length
decreases as the tangential velocity increases. Accuracy of such
contour is crucially important in achieving proper aerodynamic
performance of the blade. In addition, structural integrity of the
blades is absolutely essential due to the high centrifugal stresses
and elevated temperatures to which they are exposed during high
speed rotation under normal operating conditions.
When a blade becomes damaged due to entrance of a foreign object,
erosion, temperature or load stress, such as to produce local
distortion or microscopic cracking, it is unsafe for aircraft use.
Accordingly, compressor and turbofan blades which are found to
contain any abnormal deviation or defect in shape, dimension,
structural integrity, or surface smoothness are completely
discarded and replaced by new blades. Due to the extreme care and
expense involved in fabrication of such blades and the costly
materials used therein, replacement of such blades is the
outstanding major item of expense in jet and turbofan engine
maintenance.
SUMMARY OF THE INVENTION
The invention in this case provides a method for repairing metallic
articles which are found to contain localized defects such as
cracks, pits, dents, surface erosion, worn areas, or other
dimensional deficiencies from any cause. As illustratively applied
to turbofan blades, the novel method begins with a machining step
to cut away that portion of the blade surrounding the defect. The
foregoing step is carefully controlled to produce a cutout portion
of predetermined size and shape according to a set of standardized
template patterns. For economy and mass-production convenience, a
large number of incremental elements of standard size and shape
conforming to the mentioned templates are prefabricated for use in
rebuilding damaged blades. After the mentioned machining or cutting
step, the blade is placed into a two-piece mold having workfaces
which define a cavity oppositely corresponding to the precise
contour of a complete undamaged blade. One or more of the mentioned
prefabricated incremental elements is positioned in the cutout area
of the damaged blade. Heat and pressure are applied to the
two-piece mold as required to effect gradual deformation of the
incremental element into conformance with the stated workface
contour, and to unite the incremental mass to the adjoining blade
material integrally by a solid-state molecular diffusion bond.
DESCRIPTION OF DRAWINGS
FIG. 1 shows a damaged turbofan engine blade which may be rebuilt
by the novel process disclosed herein;
FIG. 2 shows the article from FIG. 1 in an intermediate state of
the repair process;
FIG. 3 shows an article similar to FIG. 1 but with a different type
of damage;
FIG. 4 shows a pattern of templates useful for trimming damaged
portions off a turbofan blade, together with a trimmed blade;
FIG. 5 shows a finished rebuilt blade following completion of the
novel process;
FIG. 6 shows a general perspective view of a retort useful in the
bonding step of the novel process; and
FIGS. 7 and 8 are cross-sectional views taken along line 7-7 of
FIGS. 4 and 6 showing the tooling and workpiece elements in two
stages of the bonding operation used to produce the rebuilt blade
of FIG. 5.
DETAILED DESCRIPTION
Referring to the drawings described above, use of the novel process
disclosed herein may be seen in connection with repairing or
rebuilding turbofan blades such as blade 10 in FIG. 1. In a typical
case, blade 10 is provided with a strong base portion 12 with
flanges or similar means to key the same securely in a rotating hub
or the like (not shown). Blade 10 is an airfoil with a
progressively changing angle of attack between base 12 and distal
end or tip 14 in the familiar manner of propeller blades. The
leading and trailing edges of blade 10 are designated 16 and 18,
respectively. Intermediate blade portions 12 and 14, blade 10 is
provided with stabilizing means in the form of platform projections
extending in opposite directions from both sides of the blade, only
one of which is visible in FIG. 1 and denoted by reference numeral
20. When many blades identical to blade 10 are mounted in a
complete circle around a hub, the mentioned intermediate platforms
20 contact each other between each pair of adjoining blades to form
a circular segmented flange, the segments of which comprise
platforms 20. Thus, each of the platforms is designed to bear
firmly against the next adjacent platform and thereby stabilize the
same against shock or vibration effects in the individual blades
during high speed rotation of the turbofan.
In turbofans of conventional type, blade 10 may have an overall
length on the order of 12 to 15 inches or more. The airfoil
contours of blade 10 are precision engineered and fabricated to
produce maximum efficiency of engine performance at the particular
speed and pressure conditions at which the engine incorporating
such blades is designed to operate. Any dents, punctures or other
localized deformations in the contours of blade 10 seriously
compromise the aerodynamic properties of the blade and are
completely intolerable. In the illustrative case of FIG. 1, blade
10 contains damaged portion 22 such as frequently experienced in
aircraft due to entrance of a foreign object in the inlet airflow
of a turbofan engine during operation thereof. Under present
commercial airline engine overhaul procedures, such damage would
require blade 10 to be discarded and replaced by a new blade in the
absence of the inventive process disclosed herein.
Referring to FIG. 2, the process for repairing blade 10 begins by
cutting or other suitable operations whereby the portion of blade
10 containing damaged area 22 is removed from the blade. The
portion thus removed has a predetermined size and shape conforming
to a template 24. In the illustrative case of blade 30 shown in
FIG. 3, erosion damage along substantially the entire length of
leading edge 16 such as may be encountered in a typical case is
shown. Blade 30 may be seen to contain other damaged portions 32
and 34 in addition to leading edge erosion area 36. Any change in
normal dimensions, such as due to wear of a blade from any cause
during service use thereof may be overcome by the repair method
disclosed herein. In addition to template 24, it may be seen
particularly from FIG. 4 that additional templates 25, 26, 27, and
28 are adapted to define those portions of blade 30 requiring
removal from the blade in order to insure that no damaged areas
remain on blade 30 after the cutting operation is completed. The
portions of blade 30 to be thus removed are determined by placing
templates 24--28 in the locations identified by reference numerals
44--48, respectively, and scribing or otherwise marking blade 30 to
trace the outline of the templates thereon.
It will be understood by those skilled in the art that templates
24--28 represent standardized areas of predetermined size and
location which define those portions of blades 10 and 30 which most
frequently sustain damage during service use of the same, and that
the templates are adapted for repair of blades 10 and 30 on a mass
production basis. Thus, those portions of blades 10 and 30 which
are removed during the stated cutting operations will be replaced
by incremental masses of the same material used in the mentioned
blades, such masses having essentially the same shape and surface
area as templates 24--28, but not necessarily the same thickness.
Viewing FIG. 4, for example, the incremental mass required to
replace the material removed from blade 30 and defined by area 46
will have the same shape and location as area 46, and is designated
by reference numeral 60 in FIG. 7.
Referring to FIGS. 7 and 8, the novel method in this case involves
use of restraining die or mold means such as illustratively shown
by mating dies 50 and 52. Dies 50 and 52 may be fabricated by any
suitable process known to the prior art, such as by casting from
plaster patterns or cutting operations on metallic blocks. Dies 50
and 52 when in completely mated relationship enclose a cavity 54
therebetween defined by the workfaces 56 and 58 of dies 50 and 52,
respectively. Cavity 54 has a contour oppositely and precisely
corresponding to the surfaces of a complete new blade identical to
blade 10 or 30 but without any damage or defects. Following the
cutting operations described in connection with FIG. 4, for
example, blade 30 is positioned in lower die 52 with incremental
masses corresponding in size and location to areas 44--48 shown in
FIG. 4 preplaced in the manner thus suggested. Incremental mass 60,
for example, seen in FIG. 7 occupies the area of the void produced
by removal of material defined by area 46 in FIG. 4. However, while
mass 60 has substantially the same peripheral dimensions as area
46, the thickness t of mass 60 is uniform throughout the mass and
is of particular significance in practicing the method disclosed
herein.
In FIG. 7, blade 30 with the damaged portions removed therefrom is
positioned between mating dies 50 and 52 within a surrounding
retort 62. Mass 60 is positioned within cavity 54 in the void
resulting from removal of area 46 from blade 30, other incremental
masses being similarly preplaced in the same pattern suggested by
area 44--48 in FIG. 4. Each of the stated incremental masses has
substantially uniform thickness, as suggested by thickness t of
mass 60, but not necessarily the same thickness as between
different masses. Thus, the thickness of mass 60, for example, is
predetermined to result in a total volumetric content of the mass
which will coincide almost exactly with the volume of the void
within cavity 54 resulting from removal of area 46 of blade 30 when
the blade is positioned between dies 50 and 52, and the dies are
fully mated together in the relationship shown by FIG. 8. Ideally,
the volumetric content of mass 60 should equal that of the
mentioned void. In no case should mass 60 ever be sized to result
in less volume than such void. Therefore, any tolerance allowed for
dimensional inconsistencies in the manufacture of masses 60 must be
limited to oversizing thereof rather than undersizing, with respect
to the mentioned ideal volumetric content. As a practical matter,
very slight oversizing of mass 60, as well as all the other
incremental masses discussed above, on the order of 0.01 percent to
10 percent in excess of the stated ideal volumetric content, is
preferable in order to compensate for any inconsistencies in the
cutting operations necessary to prepare blade 30 for repair. It is,
of course, the purpose of templates 24--28 to standardize the
cutting patterns and minimize such inconsistencies, but some slight
variations during lengthy mass production runs will inevitably
occur.
With the workpiece and tooling elements arranged within retort 62
as shown by FIG. 7 and discusses above, a vacuum source (not shown)
is preferably connected to the retort through conduit 64 provided
for this purpose. The retort and its contents are heated to a
suitable temperature for diffusion bonding to occur between the
material in blade 30 and the incremental masses adjacent thereto
such as mass 60. The amount of such heating will depend upon the
amount of pressure to which retort 62 and its contents will be
subjected and the duration of its exposure to the conditions
identified with solid-state molecular diffusion bonding of the
workpiece materials. Of the various materials suitable for use in
turbofan blades, titanium or an alloy thereof is widely used
because of its high strength and light weight, although other and
different materials may be used in various other types of article
repaired by the novel process disclosed herein. Where the workpiece
material is titanium, complete bonding together with the necessary
creep deformation required to reshape mass 60 into conformity with
the contours of die cavity 54, may be accomplished at 1600.degree.
F. and 1000 p.s.i. compressive force continuously maintained for 24
hours in the direction suggested by arrows 66 and 68. in FIG. 7,
for example.
It will be understood that the inventive concept in this case may
be practiced with a wide variation of metals and alloys and with
articles of different size and shape, and that the parameters for
achieving solid-state diffusion bonding will necessarily vary for
each particular choice of workpiece material. Among the metals or
alloys which may be joined by solid-state diffusion bonding are
aluminum, stainless steel, titanium, nickel, tantalum, molybdenum,
zirconium, and columbium. Diffusion bonding is characterized by
intermolecular exchange between contacting surfaces of the
workpiece at suitable pressures and at temperatures below the
melting point of the workpiece material. In some cases, a thin
interleaf material, or eutectic former, is provided while in other
forms of solid-state bonding no interleaf material is necessary.
The prior art involving solid-state or intermolecular diffusion
bonding includes issued U.S. Pat. Nos. 3,145,466; 3,180,022;
3,044,160; 2,850,798; and 3,170,234. The precise values of
time-temperature and pressure utilized in connection with bonding
workpiece materials is not a critical or limiting feature of the
broad concept disclosed herein, but specific materials and
parameters are stated for illustration only. Similarly, many
different metals or alloys for dies 50 and 52 could be used to
practice the inventive principles taught herein, although hard tool
steel such as those high in nickel and cobalt content are
preferable due to the relatively severe temperatures and load
conditions to which the dies are subjected. Illustratively, 4130
steel widely used commercially is suitable for the dies.
When deformation of mass 60 is complete, dies 50 and 52 will be in
the completely mated position suggested by FIG. 8 wherein cavity 54
is fully occupied by the rebuilt blade 70. In the foregoing
relationship, a slight gap between the dies may be seen to exist as
indicated by reference numeral 72. Compressive force denoted by
arrows 66 and 68 is transmitted through the dies and directly to
the workpiece elements contained within cavity 54. It is this
compressive force which produces deformation of incremental masses
such as mass 60 as required to conform the same into the final
desired shape of the rebuilt blade 70. Moreover, application of
compressive force vertically through mass 60, for example, will be
understood to cause lateral or horizontal force to be exerted by
mass 60 against the contacting portions of blade 30 and die cavity
54. Thus, in the absence of lateral restraint offered by blade 30
and cavity 54, the compressive force applied to mass 60 would
produce considerable increase in the length and width thereof
simultaneous with reduction in its thickness t. Since lateral
deformation is restrained, a considerable reaction force
transversely through mass 60 occurs due to vertical pressure
applied to retort 62. It is this lateral component of force which
is essential for solid-state molecular diffusion bonding to occur
between the contacting surfaces of blade 30 and mass 60. If the
volumetric content of mass 60 were insufficient to occupy
completely the void produced by removal of material from blade 30,
complete deformation of mass 60 would occur without creation of the
necessary lateral force. It is the foregoing consideration which
makes the dimensions of the incremental masses such as mass 60 so
critical in practicing the process disclosed herein.
Following completion of the bonding steps discussed above, retort
62 is opened and dies 50 and 52 are separated from each other to
permit removal of blade 70. It will be understood that blade 70 is
a single solid unitary mass of material completely homogenous
throughout with regard to metallurgical properties and composition.
The shape of blade 70 oppositely corresponds in every detail with
the contours of cavity 54 when dies 50 and 52 are fully mated as
seen in FIG. 8. The foregoing feature completely avoids any
necessity for machining operations on blade 70, resulting in a very
significant savings of time, money, and material, the importance of
which increases with use of costly materials such as titanium. In
practicing the process thus disclosed, manual deburring of edges is
occasionally required to finish rebuilt blades, but every such
blade is identical to all others formed within the same set of
matched dies 50 and 52.
In further connection with the illustrative case of turbofan blade
repair using the method disclosed herein, use of the alloy known as
Ti-6A1-4V in such blades is common. This alloy has the following
approximate composition by weight:
Aluminum 51/2 to 61/2 percent
Vanadium 31/2 to 41/2 percent
Carbon 0.08 to 0.1 percent
Hydrogen 0.010 to 0.012 percent
Titanium balance
When the foregoing material is used in both blade 30 and mass 60 as
well as all other incremental masses required to occupy cavity 54
completely in FIG. 7, for example, retort 62 and its contents are
heated to a temperature of from 1650.degree. to 1725.degree. F.
with a vacuum of 1 .times. 10.sup..sup.-4 millimeters of Mercury or
less maintained in the retort. The stated temperature is continued
for a period of from about 8 to about 16 hours, while a pressure of
from about 2000 to about 5000 p.s.i. is applied in the direction of
arrows 66 and 68 for the stated period. Where only slight
deformation of mass 60 and the other incremental masses is
involved, such as by preshaping the same to the approximate
aerodynamic curvature of the final part before the bonding step,
the lower end of the forementioned pressure and time period ranges
are applicable.
* * * * *