U.S. patent number 3,574,482 [Application Number 04/793,434] was granted by the patent office on 1971-04-13 for turbomachinery blades.
This patent grant is currently assigned to General Electric Company. Invention is credited to Henry J. Brands, Joseph W. Savage.
United States Patent |
3,574,482 |
Savage , et al. |
April 13, 1971 |
TURBOMACHINERY BLADES
Abstract
A cast, hollow, turbine blade has an opening in its tip end wall
formed by a core pin which positioned the core in a mold as the
blade was cast. A plate is brazed to the inner surface of this end
wall and seals this opening in a manner such that the structural
integrity of the blade is not dependent on a bonded joint.
Inventors: |
Savage; Joseph W. (Cincinnati,
OH), Brands; Henry J. (Cincinnati, OH) |
Assignee: |
General Electric Company
(N/A)
|
Family
ID: |
25159913 |
Appl.
No.: |
04/793,434 |
Filed: |
January 23, 1969 |
Current U.S.
Class: |
416/90R; 416/232;
416/96R |
Current CPC
Class: |
F01D
9/041 (20130101); F01D 5/187 (20130101); F01D
5/18 (20130101); Y02T 50/673 (20130101); Y02T
50/671 (20130101); Y02T 50/676 (20130101); Y02T
50/60 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); F01D 9/04 (20060101); F01d
005/18 () |
Field of
Search: |
;253/77 (H)/ ;253/77
(I)/ ;253/39.15 (B)/ ;170/159 (M)/ ;416/90,95,224,233,232
(Foreign)/ ;416/248,96,213 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
|
|
|
|
|
|
|
212,964 |
|
Mar 1957 |
|
AU |
|
742,477 |
|
Dec 1955 |
|
GB |
|
129,576 |
|
Sep 1950 |
|
SW |
|
269,598 |
|
Oct 1950 |
|
CH |
|
Primary Examiner: Powell, Jr.; Everette A.
Claims
We claim:
1. A cast, hollow, turbomachinery blade:
having an internal chamber defined in part by an integrally cast
end wall at the tip end thereof;
said end wall having an opening therethrough formed by a supporting
core pin during casting of the blade; and
a plate bonded to the inner surface of said end wall and overlying
said opening to seal said opening.
2. A turbomachinery blade as in claim 1 wherein:
the blade further comprises an integrally cast tang at the inner
end of the blade;
the tang has at least one opening in the form of a port for
admitting cooling fluid into said chamber; and
the plate is insertable through one of said openings to permit its
introduction into said chamber and positioning on said end wall for
bonding thereto.
3. A turbomachinery blade as in claim 2 wherein:
a recess is formed on the inner surface of said end wall around the
opening therein and the insert is registered therein, said recess
facilitating positioning of said plate on said end wall.
4. A method of sealing the internal chamber of a hollow, cast,
turbomachinery blade having an end wall defining the outer bounds
of the chamber, where said end wall has an opening therethrough,
formed by a supporting core pin during casting of the blade,
comprising the steps of:
introducing a plate into said chamber;
positioning said plate on the inner surface to said end wall,
overlying said opening; and
bonding said plate to said end wall.
5. A method as in claim 4 comprising the further steps of:
introducing a plate having brazing material thereon;
subjecting the blade to heat after the plate has been so positioned
to melt said braze; and
removing said heat to complete the bonding of the plate to the end
wall.
Description
The present invention relates to improvements in gas turbine
engines and more particularly to improved hollow blades employed in
such engines.
Turbine blades are formed as hollow shells, not only to reduce
their weight, but to provide a plenum chamber from which cooling
air is discharged, through openings in the shell, into the hot gas
stream. The arrangement of the openings and the flow of the cooling
air through the interior of the blade can take many different forms
to maintain the actual metal temperature of the blade substantially
cooler than the extremely high temperature of the hot gas stream
which passes through the blades to drive the turbine.
The most advanced alloys are employed in fabricating these blades
in order to permit operation in the severe environment of high
temperatures and high stresses that is inherent in high-performance
engines intended for the propulsion of aircraft. The most effective
and practical fabrication technique for forming hollow blades of
such alloys is casting. A core is positioned within a mold to
define the hollow shell of the blade which is integrally cast with
a tang employed in securing it to a turbine rotor disc.
The opposite ends of this core must be supported to accurately
position it within the mold. One end of the core may be supported
by extensions through the attaching tang which define, in the cast
blade, entrance ports for cooling air. Conventionally the other end
of the core has been supported by having the core extend beyond the
tip end of the blade mold. The resultant cast blade is then open at
its tip end. This has necessitated attachment of an end cap, by
brazing, welding or the like, in order to seal the tip end of the
blade. Alternatively, such cores have been provided with one or
more extensions to enable support of tip end of the core. The
resultant cast blade then has openings which have been sealed by
"plugs" which are brazed or welded in these openings.
In either case the structural integrity of the blade is dependent
on joints between the blade and either the end caps or the "plugs."
While such approaches have been adequate in the past, bonded joints
formed by welding, or the like, are not wholly reliable in the
severe environment of high-performance gas turbine engines.
While the motivating environment for the present invention is in
the turbine section, similar problems can also be encountered in
forming and sealing the tip ends of hollow compressor blades used
in a gas turbine engine.
Accordingly, the object of the invention is to provide improved
sealing mechanism for the tip ends of turbomachinery blades and, in
so doing, to eliminate bonded joints as structural elements of the
blades.
These ends are attained in an integrally cast blade having a wall
defining the tip end of the blade. This wall has an opening,
through which a core pin projected to support the tip end of the
core, in the mold, as the blade was cast. A plate overlies this
opening and is secured to the inner surface of the tip wall. The
tip end of the blade is thus an integral cast structure, and the
core opening is sealed by the plate without reliance on any bonded
joint which would be subjected to substantial stresses.
Preferably, the opening is disposed centrally of the tip end wall
and ribs project inwardly to define a recess. The plate has an
outline registerable with this recess to facilitate its being
positioned in sealing relation. The plate is bonded, as by brazing,
in its sealing position to insure that it will remain in place,
particularly while the rotor is at rest.
The above and other related objects and features of the invention
will be apparent from a reading of the following description of the
disclosure found in the accompanying drawing and the novelty
thereof pointed out in the appended claims.
In the drawing:
FIG. 1 illustrates a blade, with portions in section, embodying the
present invention;
FIG. 2 is a section, taken on line II-II in FIG. 1;
FIG. 3 is a view taken on line IV-IV in FIG. 1; and
FIG. 4 is a section, along the chord, of the tip end portion of
this blade, illustrating the core employed during casting of the
blade.
The blade seen in FIG. 1 is an integral casting comprising a tang
12, a platform 14 and a cambered airfoil blade portion 16. The
blade portion is formed as a thin-walled shell defining an interior
plenum chamber 18.
The blade would be mounted on the periphery of a rotor disc by
inserting the tang in a correspondingly shaped dovetail slot.
Cooling air, or other cooling fluid, in known fashion, would be
directed to the base of the tang. Entrance ports 20 direct the
cooling air into the plenum chamber 18. Small openings, selectively
placed in the airfoil wall, discharge the cooling air along the
outer surface of the blade to provide a cooling mechanism for the
blade portion which projects into a hot gas stream.
The tip end of the cavity 18 is defined by an integrally cast end
wall 22. An opening 24, in the end wall 22, is sealed by a plate
26. The plate 26 overlies the opening 24 and is secured, or bonded,
to the inner surface of the wall 24 by brazing or the like. The use
of brazing assures a tight seal and further keeps the plate 26 in
sealing position when the turbine blade is in operation.
FIG. 3 illustrates the relationship of the core to the blade during
the casting operation. The exterior of the blade is defined by
surfaces of a conventional mold. The interior chamber 18 and ports
20 are defined by a core 28. The portions of the core defining the
ports 20 are extended into the mold to position the tang end of the
core. A core pin 30, seen in FIG. 3, extends into the mold to
position the tip end of the core. When the core is removed, after
casting, the opening 24 exists where the core pin 30 projected into
the mold.
The plate 26 may be first coated with brazing material and then
inserted through one of the ports 20, or through the opening 24,
into the chamber 18. Internal ribs 32, on opposite sides of the
opening 24 define a recess with which the plate 26 is registerable.
After insertion in the chamber 18, it is a simple matter to
position the plate in this recess, overlying the opening 24. After
being so positioned, heat may be applied to melt the braze which
coats the plate 26, and, upon removal of the heat, the plate will
be permanently secured in its sealing position.
It will be apparent that the structural integrity of the tip end of
the blade is in no way dependent on the bonded joint between the
plate 26 and end wall 22 when the blade is subjected to its major
force loading in a direction toward its tip end, due to centrifugal
forces in operation. This is due to the fact that the plate 26
bears against the inner surface of the tip end wall 22.
Various modifications of the described embodiment will occur to
those skilled in the art within the spirit and scope of the present
inventive concepts which are to be circumscribed solely by the
following claims.
* * * * *