U.S. patent number 3,856,433 [Application Number 05/384,990] was granted by the patent office on 1974-12-24 for liquid cooled turbine bucket with dovetailed attachment.
This patent grant is currently assigned to General Electric Company. Invention is credited to John H. Eskesen, Clayton M. Grondahl.
United States Patent |
3,856,433 |
Grondahl , et al. |
December 24, 1974 |
LIQUID COOLED TURBINE BUCKET WITH DOVETAILED ATTACHMENT
Abstract
A liquid-cooled turbine bucket construction is described in
which the airfoil bucket core, platform (with metering means) and
root with dovetail configuration are integrally formed. The
pressure and suction sides of each bucket are each provided with a
liquid reservoir defined in part by metering means (e.g., a weir),
grooves in the upper surface of the platform and face of the
airfoil core and holes interconnecting these grooves with the
underside of the platform adjacent the metering means.
Inventors: |
Grondahl; Clayton M. (Elnora,
NY), Eskesen; John H. (Schenectady, NY) |
Assignee: |
General Electric Company
(Schenectady, NY)
|
Family
ID: |
23519586 |
Appl.
No.: |
05/384,990 |
Filed: |
August 2, 1973 |
Current U.S.
Class: |
416/97R; 416/92;
416/96R |
Current CPC
Class: |
F01D
5/185 (20130101); F01D 5/081 (20130101); F05D
2240/81 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); F01D 5/02 (20060101); F01D
5/08 (20060101); F01d 005/08 (); 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.
Assistant Examiner: Casaregola; Louis J.
Attorney, Agent or Firm: MaLossi; Leo I. Cohen; Joseph T.
Squillaro; Jerome C.
Claims
What we claim as new and desire to secure by by Letters Patent of
the United States is:
1. Turbine bucket construction comprising in combination:
a. integrally formed airfoil-shaped core, platform and root
portions, said root portion having a dovetailed configuration,
b. a first group of cooling grooves recessed into the upper surface
of said platform portion,
c. a second group of cooling grooves recessed into the pressure and
suction faces of the airfoil-shaped core, each of the cooling
grooves in said first group being connected to a separate cooling
groove in said second group,
d. skin material disposed over said upper surface of said platform
portion and over said pressure and suction faces thereby covering
said first and second groups of cooling grooves,
e. a pair of longitudinally-extending recesses formed in the
underside of said platform portion one of said recesses extending
along each side of, in the same direction as, and adjacent to said
dovetailed configuration, a pair of longitudinally-extending
gutters formed in the underside of said platform portion, one of
said gutters extending parallel to and adjacent each of said
recesses,
f. a pair of longitudinally-extending projections formed along the
underside of said platform portion, each of said projections
separating one recess and one gutter, each of said projections
having a crest, said crest being arcuate in cross-section and
presenting a convex cylindrical surface, the elements of the
cylindrical surfaces of both crests being parallel to the elements
of the cylindrical convex ridges of said dovetailed configuration
and
g. a plurality of holes passing through said platform portion
placing said first group of cooling grooves in flow communication
with the underside of said platform portion adjacent each of said
projections on the side thereof away from the recess adjacent
thereto.
2. The turbine bucket as recited in claim 1 wherein the crest of
the longitudinally extending projection is in the form of an arc of
a circle in cross-section.
3. The turbine bucket as recited in claim 1 wherein the far ends of
each of the recesses formed in the underside of the platform
portion are closed off by a pair of plate-like members.
4. The turbine bucket as recited in claim 1 wherein the pair of
recesses and the pair of projections are located between the pair
of gutters.
5. The turbine bucket as recited in claim 1 wherein each groove of
the second group of cooling grooves terminates in one of two
interconnected manifolds located near the tip of said bucket.
6. In a gas turbine wherein a turbine disk is mounted on a shaft
rotatably supported in a casing, said turbine disk extending
substantially perpendicular to the axis of said shaft and having
turbine buckets mounted on the outer rim thereof, means located
radially inward of said bucket adjacent said turbine disk for
supplying liquid coolant to said buckets to enter open-circuit
distribution paths comprising cooling channels and a manifold
system in each of said buckets, the improvement comprising:
a. each of said buckets having integrally formed airfoil-shaped
core, platform and root portions, said root portion having a
dovetailed configuration fitting into a matching slot in said outer
rim,
b. the platform portion of each bucket having a pair of
longitudinally-extending recesses formed in the underside thereof,
one of said recesses extending along each side of, in the same
direction as and adjacent said dovetailed configuration, a pair of
longitudinally-extending gutters formed in the underside of said
platform portion, one of said gutters extending parallel to and
adjacent each of said recesses,
c. a pair of longitudinally extending projections formed along the
underside of said platform portion, each of said projections
separating one recess and one gutter, each of said projections
having a crest, said crest being arcuate in cross-section and
presenting a convex cylinder surface, the elements of the
cylindrical surfaces of both crests being parallel to the elements
of the cylindrical convex ridges of said dovetailed configuration
and
d. in each of said buckets a plurality of first cooling grooves
recessed into the upper surface of the platform portion, said
cooling grooves being connected to a plurality of second cooling
grooves recessed into the pressure and suction faces of the
airfoil-shaped core, said second cooling grooves in turn being
connected to a manifold system adapted to discharge coolant from
said bucket,
e. skin material disposed over the upper surface of the platform
portion and over the pressure and suction faces of each of said
buckets thereby covering said first and second cooling grooves and
said manifold system except for the exit therefrom,
f. a plurality of holes passing through said platform portion
placing said first cooling grooves in flow communication with said
pair of gutters and
g. said means for supplying liquid coolant being in flow
communication with each of said longitudinally extending
recesses,
whereby once any given recess has become full of coolant, as
additional coolant enters said recess the excess coolant flows over
the adjacent crest along the length thereof and passes through said
holes, said first and second cooling grooves and said manifold for
exit from said bucket.
7. The turbine bucket as recited in claim 6 wherein the pair of
recesses and the pair of projections are located between the pair
of gutters.
8. The improvement recited in claim 6 wherein the far ends of each
of the recesses formed in the underside of the platform portion are
closed off by a pair of plate-like members.
9. The improvement recited in claim 6 wherein in a given bucket the
holes passing through the platform portion to the underside thereof
are divided into two sets, one set in flow communication with
cooling grooves on the pressure side of said bucket and the second
set in flow communication with cooling grooves on the suction side
of said bucket.
Description
BACKGROUND OF THE INVENTION
Structural arrangements for the liquid cooling of gas turbine
buckets are shown in U.S. Pat. Nos. 3,446,481 - Kydd, 3,446,482 -
Kydd and 3,658,439 - Kydd. These patents are incorporated by
reference.
Systems for supplying coolant to the cooling channels of
liquid-cooled turbine buckets are determined in part by the type of
attachment used to secure the buckets to the rotor. The art is in
need of such a distribution system particularly adapted to buckets
having dovetailed bucket-to-rotor attachment and integral platform
construction.
SUMMARY OF THE INVENTION
A liquid-cooled turbine bucket construction is described in which
the airfoil bucket core, platform (with metering means) and root
with dovetail configuration are integrally formed. The pressure and
suction sides of each bucket are each provided with a liquid
reservoir defined in part by metering means (e.g., a weir), grooves
in the upper surface of the platform and face of the airfoil core
and holes interconnecting these grooves with the underside of the
platform adjacent the metering means.
BRIEF DESCRIPTION OF THE DRAWING
The exact nature of this invention as well as objects and
advantages thereof will be readily apparent from consideration of
the following specification relating to the annexed drawings in
which:
FIG. 1 is a view partially in section showing the side view in
elevation of part of the dovetailed root, platform and airfoil and
liquid coolant feed means in register therewith;
FIG. 2 is a view partially in section with the retainer/feed ring
and a cover plate cut away to show the integral formation in the
platform of the reservoir, the longitudinally extending metering
means, platform gutter, platform coolant channels and feed holes
leading thereto and
FIG. 3 is a view taken on line 3--3 of FIG. 2 with the airfoil skin
removed in part to show the location and interconnection of the
airfoil channels, the platform channels and feed conduits leading
to the platform channels from the underside of the platform.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Turbine bucket 10 consists of skin 11, 11a (e.g., sheet metal)
affixed, as by brazing, to the unitary root/platform/airfoil core
12. Root portion 13 is formed in the conventional dovetail
configuration by which bucket 10 is retained in slot 14 of wheel
rim 16. Each groove 17 recessed in the surface of platform 18 is
connected to a similar groove 19 recessed in the surface of airfoil
portion 21 of unit 12. The cooling channels (preferably rectangular
in shape) defined by skin 11a and grooves 17 are thus in
communication on a one-to-one basis with the cooling channels
defined by skin 11 and grooves 19 and cooling liquid is conducted
therethrough at a uniform distance from the exterior surface. At
the radially outer ends thereof the rectangular cooling channels on
the pressure side of bucket 10 are in flow communication with, and
terminate at, manifold 22 recessed into airfoil portion 21. On the
suction side of bucket 10 the cooling channels are in flow
communication with, and terminate at, a similar manifold (not
shown) recessed into airfoil portion 21. Near the trailing edge of
bucket 10 a cross-over conduit (opening shown at 23) connects the
manifold on the suction side with manifold 22.
Open-circuit cooling is accomplished by spraying cooling liquid
(usually water) at low pressure in a generally radially outward
direction from nozzles, such as nozzle 24 (one shown), mounted on
each side of the rotor disk. The coolant is received in annular
gutter 26 formed in ring member 27, one of which is mounted on each
side of wheel rim 16. Ring member 27, in addition to conducting the
function of coolant distribution to each bucket also retains the
buckets 10 properly positioned in wheel rim 16 as more completely
described in U.S. Pat. application Ser. No. 385,096 - Wojcik, filed
Aug. 2, 1973 and assigned to the assignee of the instant invention.
The Wojcik application is incorporated by reference.
Coolant received in gutters 26, is directed through feed holes 28,
each of which is in flow communication with a reservoir 29
extending in a direction parallel to the axis of rotation of the
turbine disk. The openings into the feed holes 28 from gutters 26
are equally spaced around the circumference of gutters 26 to insure
equal distribution of coolant to the buckets via these feed
holes.
While coolant is spread out as a thin film in gutters 26, it
accumulates to fill each reservoir 29 (the ends thereof being
closed by means of a pair of cover plates 31). As liquid coolant
continues to reach each reservoir 29, the excess discharges over
the crest of weir 32 along the length thereof and is thereby
metered. Preferably the crest of weir 32 is arcuate (convex toward
the axis of rotation) in cross-section and is a portion of a
cylinder in configuration in order to accommodate slight
differences in the disposition of the buckets 10 relative to each
other. Although the distance of the crest of any given weir from
the axis of rotation may vary slightly from that of another weir,
the cylindrical configuration of the weir crest curving toward the
root must be accurately machined so that each element of each such
cylindrical surface extends parallel to the elements forming the
cylindrical convex ridges of the dovetailed configuration. In this
manner each element of the crest surface can be set parallel to the
axis of rotation (the axis of the shaft on which the rotor is
mounted). This machining accuracy is required in order to insure
that liquid coolant passes uniformly over the full length of the
weir crest.
Coolant that has traversed the weir crest 32 continues in the
generally radial direction to enter longitudinally extending
platform gutter 33 as a film-like distribution, passing thereafter
through the cooling channel feed holes 34. Thus, one each of
reservoir 29, weir 32 and gutter 33 constitute a set, one such set
being formed in the underside of platform 18 on each side of root
portion 13. Most of the channel feed holes 34 are in flow
communication with grooves 17 on a one-to-one basis, although a few
of these holes 34 connect directly with grooves 19. In any event,
the coolant passes from holes 34 to manifold 22 (and the suction
manifold, not shown) via bucket cooling channels.
As the coolant traverses the surfaces of the platform and of the
airfoil, these elements are kept cool. Some portion of the cooling
liquid, depending upon the rate of flow, is converted to the
gaseous or vapor state as it absorbs heat. The vapor or gas and any
remaining liquid coolant exit from the manifold 22 via opening 36,
preferably to enter a collection slot (not shown) formed in the
casing for the eventual recirculation or disposal of the ejected
fluid.
Although the cooling channels have been illustrated herein
extending spanwise of the turbine bucket, the instant invention is
equally applicable to bucket constructions in which the cooling
channels are disposed in a convoluted or spiral configuration.
* * * * *