U.S. patent number 3,778,188 [Application Number 05/287,888] was granted by the patent office on 1973-12-11 for cooled turbine rotor and its manufacture.
This patent grant is currently assigned to General Motors Corporation. Invention is credited to Robert H. Aspinwall.
United States Patent |
3,778,188 |
Aspinwall |
December 11, 1973 |
COOLED TURBINE ROTOR AND ITS MANUFACTURE
Abstract
An integral cast turbine rotor wheel includes a disk and porous
blades extending from the disk and into the rim of the disk, the
disk defining cooling air entrance ports communicating with the
porous blades so that cooling air may be circulated through them.
The method of manufacture of the wheel includes providing cores
defining air ports and blades, the blade portion of each core being
porous, placing the cores in a mold shaped to conform to the wheel
and pouring metal to define the cast body. The cores are then
removed and any necessary machining of the wheel is performed.
Inventors: |
Aspinwall; Robert H.
(Zionsville, IN) |
Assignee: |
General Motors Corporation
(Detroit, MI)
|
Family
ID: |
23104807 |
Appl.
No.: |
05/287,888 |
Filed: |
September 11, 1972 |
Current U.S.
Class: |
416/97R;
416/244A; 416/231R; 416/241R; 416/244R |
Current CPC
Class: |
F01D
5/34 (20130101); F01D 5/183 (20130101); F05D
2230/21 (20130101); F05D 2300/514 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); F01d 005/18 () |
Field of
Search: |
;416/97,231,244
;415/115 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
|
|
|
|
|
|
|
722,514 |
|
Jan 1955 |
|
GB |
|
760,734 |
|
Nov 1956 |
|
GB |
|
Primary Examiner: Powell; Everette A.
Claims
I claim:
1. A bladed turbine rotor element comprising, in combination, a
solid disk having a rim portion and an annular row of porous blades
integral with the disk, each blade including a porous airfoil
portion projecting from the rim and a porous base portion extending
into the rim; the rim defining circumferentially spaced air
entrance ports each coummunicating with the exterior of the disk
and with the base portion of a blade; the said rotor element being
unitarily cast as an integral piece.
2. A bladed turbine rotor element comprising, in combination, a
solid disk having a rim portion and an annular row of porous blades
integral with the disk, each blade including a porous airfoil
portion projecting from the rim and a porous base portion extending
into the rim; the rim surrounding the base portion and defining
circumferentially spaced air entrance ports each communicating with
the exterior of the disk and with the base portion of a blade; the
said rotor element being unitarily cast as an integral piece.
3. A method of manufacturing an integral bladed turbine rotor
element with a solid disk, porous blades, and air entrance ports in
the disk communicating with the blades, the method comprising
providing a mold with a cavity corresponding in form to the rotor
element; providing cores each corresponding in form to at least one
blade and a corresponding port, each core having a porous portion
corresponding to the blade and a solid portion defining the port;
disposing the cores in place in the mold; and pouring molten metal
into the mold so as to fill the pores in the porous portions of the
core and fill the remainder of the mold cavity around the solid
portion of the cores and the base portion of the porous blades to
provide the solid disk integral with the blades; removing the cast
element from the mold; and removing the core material from the
blades and the ports to leave porous blades extending from the disk
and into the disk communicating with the ports.
Description
My invention relates to turbine wheels and the like and to a method
of manufacturing them; it is particularly directed to unitarily
cast wheels having porous blades which may be cooled by air
circulated through the blades. The primary object of the invention
is to provide a wheel, particularly one for small turbines, which
may be economically manufactured and which is well adapted to stand
up to the rigors of service in a gas turbine engine. The structure
and method of manufacture may have other applications, however.
It is well known that turbine rotor elements including a wheel or
disk and blades cast integral with the disk are an article of
commerce. So far as I am aware, however, such wheels have not
included blades of a porous nature.
Certain United States patents may be mentioned as background of the
detailed description of my invention. Porous blades for
turbomachines are disclosed or suggested by Smith et al. U.S. Pat.
No. 2,665,881, Jan. 12, 1954, Erwin U.S. Pat. No. 2,720,356, Oct.
11, 1955, and Endres U.S. Pat. No. 2,970,807, Feb. 7, 1961. Markus
et al. U.S. Pat. No. 3,523,766, Aug. 11, 1970, is directed to a
process for making porous cast structures. Paul U.S. Pat. No.
2,611,161, Sept. 23, 1952, Bly et al. No. 3,635,791, Jan. 18, 1972,
and McLaren U.S. Pat. No. 3,648,756, Mar. 14, 1972, are directed to
the casting of turbine wheels or other bladed turbine
structures.
While the practice of my invention involves the use of known
technology in carrying out the manufacture of the rotor element, it
involves a new combination of steps effective to produce a product
which I believe to be new.
The nature of my invention and its advantages will be clear to
those skilled in the art from the succeeding detailed description
and accompanying drawings of the preferred embodiment of the
invention.
FIG. 1 is a sectional view of a turbine rotor element taken on a
plane containing the axis of rotation thereof.
FIG. 2 is an enlargement of a portion of FIG. 1 with seal rings
mounted on the rotor.
FIG. 3 is an elevation view taken on the plane indicated by the
line 3--3 in FIG. 2.
FIG. 4 is an axonometric view of a core element.
FIG. 5 is a transverse sectional view of a mold for casting the
turbine rotor element.
Referring first to FIG. 1, a turbine rotor element or wheel 2
comprises a disk 3 having a rim portion 4. The wheel bears an
annular cascade of blades 6 extending from the rim of the wheel.
The wheel may be of conventional overall outline and may be
suitably machined for connection to a shaft (not shown) or
connection to other turbine disks to form a multistage rotor.
As indicated in FIGS. 2 and 3, seal rings or seal plates 7 and 8
are mounted in circumferential grooves 10 and 11 machined in the
outer face of the rim 4. This is a somewhat schematic showing of
the seal rings, but the details of such are well known to those
skilled in the art and are immaterial to my present invention.
The disk, including the rim, is substantially all a solid, that is,
non-porous structure, but each blade 6 includes an airfoil portion
12 and a base portion 14 extending into the rim, the portions 12
and 14 being porous. A cooling air port 15 extends into the rim
from the forward face of the wheel under the base portion of each
blade. As shown, the cooling air port extends to the rear face of
the rim. Drilled or cast passages 16 through the rim at the forward
side of disk 3 admit cooling air behind seal plate 7 to the ports
15, and thus into the porous blade base 14 and on into the porous
airfoil portion 12 from which it is discharged through the porous
blade structure into the hot gas stream flowing past the blades.
This is known as transpiration cooling, the cooling being effected
by the flow of the cooling air through small pores in the structure
and out through the surface, where it additionally forms a film of
cooler air to isolate the blade to some extent from the hot motive
fluid.
Means for conducting cooling air to the face of the wheel need not
be described, since such is very well known and is widely employed
in turbine engines. The flow of the cooling air through the rotor
may be effected by a pumping action due to centrifugal force or to
a difference in pressure between the cooling air supplied and the
motive fluid passing the turbine, or in any other suitable
manner.
It should be noted that the base portion 14 of the blades
preferably terminates at some small axial distance from the forward
and rear face of the rim so that the forward and rear face of the
rim is solid, with the blade base portions constituting plugs of
porous material integral with the solid portion of the rim
extending into the periphery of the rim.
It will be apparent to those skilled in the art that the structure
described is very simple and suitable one for a turbine engine
where it is desired to cool the blades to make use of higher
temperature motive fluid than would otherwise be possible. It is
particularly suited to small turbines in which the economy of
casting the entire rotor element in one piece may be a very
important consideration in the economic suitability of a gas
turbine engine.
FIGS. 4 and 5 illustrate steps in the manufacture of the rotor
element.
FIG. 5 shows more or less schematically a mold which may be
employed in a casting process following known technology as
exemplified by the teachings of the patents referred to above. The
mold 22 includes a drag 23 and a cope 24 which define a mold cavity
25 into which metal is introduced through a sprue 26. The mold may
be ceramic, and it may be prepared by investment of a suitable
permanent or disposable pattern. The mold cavity 25 has the overall
contour or form of the rotor element prior to any machining which
may take place after casting. It defines pockets 27 which are of
the form of the portion of the blade which projects from the rotor
rim. A blade core 28 is disposed in each pocket 27.
The blade core (FIG. 4) comprises a porous portion 30 having the
form of the blade and a solid portion 31 having the form of the
cooling air port 15. The porous portion is of a fibrous nature such
that, when metal is cast into and penetrates the porous portion of
the core and the core is subsequently dissolved out by suitable
agent, the blade portion is relatively full of small capillary
passages which intercommunicate. The solid base part 31 of the core
28 may, of course, be formed by any usual technique of forming of
solid ceramic bodies. The porous blade portion 30 might be provided
by sintering together granules of suitable size, much as porous
objects are produced by powder metallurgy. It might also be made by
dipping a polyurethane foam pad of proper shape into a leachable
ceramic such as that disclosed in U.S. Pat. No. 3,576,653 of Miller
et al., Apr. 27, 1971, and then squeezing out the excess ceramic.
The foam is dipped and squeezed until the polyurethane foam fibers
are completely covered with the ceramic. The foam may then be air
dried and fired to gasify the polyurethane and leave a ceramic
foam. The porous and solid parts of the blade 28 may then be united
by a suitable cement.
The manner in which the cores 28 are disposed in mold 22 will be
obvious. Once the mold is assembled with the cores in place, the
pouring of the metal may follow the usual casting processes, such
as vacuum casting preferably. The wheel is preferably of a high
nickel base alloy, for example, Inco 713C (trademark) or Mar M246
(trademark). After the metal is solidified and cooled, the mold is
disassembled, the casting is removed, and the ceramic cores 28 are
leached out of the metal, after which any necessary machining is
accomplished in the usual manner.
It should be apparent to those skilled in the art that the
described method is highly suitable for the economical and feasible
production of the turbine rotor element described and that the
rotor element is particularly suited to the requirements of gas
turbine engines.
The term "disk," as used in the appended claims, is intended to
mean any annular body mounting the blades.
The detailed description of the preferred embodiment of the
invention for the purpose of explaining the principles thereof is
not to be considered as limiting or restricting the invention,
since many modifications may be made by the exercise of skill in
the art.
* * * * *