U.S. patent number 3,816,022 [Application Number 05/285,631] was granted by the patent office on 1974-06-11 for power augmenter bucket tip construction for open-circuit liquid cooled turbines.
This patent grant is currently assigned to General Electric Company. Invention is credited to William H. Day.
United States Patent |
3,816,022 |
Day |
June 11, 1974 |
**Please see images for:
( Certificate of Correction ) ** |
POWER AUGMENTER BUCKET TIP CONSTRUCTION FOR OPEN-CIRCUIT LIQUID
COOLED TURBINES
Abstract
Nozzle construction is disposed in the passage employed for the
discharge of coolant flow from an open-circuit liquid cooled gas
turbine. This improved construction relief upon for the recovery of
reaction energy from the coolant is shown applied to both
unshrouded and shrouded turbine buckets.
Inventors: |
Day; William H. (Scotia,
NY) |
Assignee: |
General Electric Company
(Schenectady, NY)
|
Family
ID: |
23095071 |
Appl.
No.: |
05/285,631 |
Filed: |
September 1, 1972 |
Current U.S.
Class: |
416/92; 416/97R;
416/95; 416/96A; 416/191 |
Current CPC
Class: |
F01D
5/185 (20130101); F05D 2240/81 (20130101); F05B
2240/801 (20130101) |
Current International
Class: |
F01D
5/18 (20060101); F01d 005/18 () |
Field of
Search: |
;416/92,96,97,95,90
;415/115 |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
Primary Examiner: Powell, Jr.; Everette A.
Attorney, Agent or Firm: MaLossi; Leo I. Cohen; Joseph T.
Squillars; Jerome C.
Claims
What I claim as new and desire to secure by letters patent of the
United States is:
1. 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 affixed to the outer rim thereof with platform
means disposed therebetween, said buckets receiving a driving force
from a hot motive fluid moving in a direction generally parallel to
said axis of said shaft and the driving force being transmitted to
said shaft via rotation of said turbine disk, means located
radially inward of said platform for introducing liquid coolant
within said turbine in a radially outward direction into an
open-circuit coolant distribution system comprising cooling
channels extending beneath the airfoil surfaces of each of said
buckets, metering means located radially inward of and in flow
communication with said cooling channels and a manifold and
discharge portion located in the tip region of each of said buckets
in flow communication with the radially outer ends of cooling
channels of the given bucket whereby coolant is metered into,
proceeds through and exits from cooling channels into said manifold
and discharge portion, the improvement comprising:
a. manifold means located beneath the bucket surface near the tip
of each bucket in flow communication with the discharge end of each
coolant channel and
b. said manifold and discharge portion including a
convergent-divergent nozzle disposed to discharge coolant flow from
said open circuit coolant distribution system in a rearward
direction relative to the direction of rotation of said turbine
disk.
2. The improvement of claim 1 wherein the manifold means consists
of a slot formed in the bucket core on each side of each turbine
bucket, the two slots being interconnected at some point upstream
of the convergent-divergent nozzle by a passage extending through
the separating bucket core material and said nozzle is located to
discharge coolant flow from the trailing edge of said bucket.
3. The improvement of claim 1 wherein each turbine bucket is
connected at its distal end to shroud construction and the
convergent-divergent nozzle is formed in said shroud construction,
said nozzle being disposed to discharge into a cavity formed in the
turbine casing.
4. The improvement of claim 3 wherein the manifold structure in the
manifold and discharge portion is disposed on both the pressure and
suction sides of each bucket and is in flow communication with the
nozzle via passageways in the bucket core and shroud
construction.
5. A unitary turbine bucket/shroud structure comprising a turbine
bucket and a shroud element, said turbine bucket having a network
of subsurface cooling channels and manifold structure formed
therein, the radially outward ends of said channels being in flow
communication with said manifold structure, said shroud element
being affixed to the distal end of the core of said turbine bucket
and having nozzle construction formed therein, said nozzle
construction being in flow communication with said manifold
structure and being disposed to discharge flow therefrom in a
direction generally opposite to the direction in which said
bucket/shroud structure is intended to be moved in use.
6. The unitary turbine bucket/shroud structure of claim 5 wherein
the nozzle construction is a convergent-divergent nozzle.
7. The unitary turbine bucket/shroud structure of claim 5 wherein
in addition to the cooling channels communicating with the manifold
structure, other cooling channels near the leading and trailing
edges communicate directly with passages extending through the
shroud element in a generally radial direction instead of
communicating with the manifold structure and nozzle
construction.
8. In the operation of 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 affixed to the outer rim thereof
with platform means disposed therebetween, said buckets receiving a
driving force from a hot motive fluid moving in a direction
generally parallel to said axis of said shaft and the driving force
being transmitted to said shaft via rotation of said turbine disk,
means located radially inward of said platform for introducing
liquid coolant within said turbine in a radially outward direction
into an open-circuit coolant distribution system by which said
coolant is metered into cooling channels in said buckets, proceeds
as liquid and vapor through said channels and exits from said
channels into manifold and discharge means forming part of said
open-circuit coolant distribution system, the improvement
comprising:
a. creating and maintaining a pressure differential between said
open-circuit coolant distribution system and the ambient to which
the coolant flow is discharged, said pressure differential being
sufficiently high that the coolant flow reaching said manifold and
discharge means is discharged at supersonic velocities and
b. discharging said coolant flow in a rearward direction relative
to the direction of rotation of said turbine disk.
Description
BACKGROUND OF THE INVENTION
Structural arrangements for the open-circuit liquid cooling of gas
turbine buckets are shown in U.S. Pat. Nos. 3,446,481 -- Kydd and
3,446,482 -- Kydd. These patents are incorporated by reference.
The provisions for open-circuit liquid cooling disclosed therein
are particularly important for the capability offered thereby for
increasing the turbine inlet temperature to an operating range of
from 2,500.degree. F to at least 3,500.degree. F thereby obtaining
an increase in power output ranging from about 100 to 200 percent
and an increase in thermal efficiency ranging to as high as 50
percent. Such open-circuit liquid cooled turbine structures are
referred to as "ultra high temperature" gas turbines.
The coolant passages shown in the Kydd patents extend radially of
the buckets from below the surface of the platforms to the distal
ends thereof and are open at both ends. During operation these
coolant passages do not run full of liquid coolant. Since all of
these coolant passages open at the inner ends thereof into a region
of common pressure, when the outer ends of all of these same
coolant passages open to the local ambient pressure at various
locations around the bucket tip, hot gas will flow into some of
these passages and this is highly undesirable.
A solution to this problem is set forth in U.S. Patent Application
Ser. No. 93,057 -- Kydd now U.S. Pat. No. 3,736,071, filed Nov. 27,
1970 and assigned to the assignee of the instant invention. Bucket
tip designs are shown therein for manifolding fluid discharge from
open-ended coolant passages in the turbine bucket. The fluid so
manifolded (e.g., steam mixed with water in a water-cooled system)
is discharged from the trailing end of the bucket into an annular
collection slot located in register therewith in the wall of the
turbine casing. The collection of coolant by this fluid
discharge/collection slot combination to enable recirculation
thereof is important from environmental considerations and because
of the reduction afforded thereby in the requirement for make-up
coolant.
It would be desirable to be able to retain this capability for
collecting the coolant (or at least the liquid component thereof)
leaving the liquid cooled turbine buckets and at the same time be
able to simultaneously recover at least a significant portion of
the kinetic energy present in the coolant discharge flow.
Energy recovery from the coolant discharge of elastic fluid
turbines has been taught in the art in turbines wherein gas
(generally air) is used as the cooling medium. Such power augmenter
constructions are described in British Patent Specification Nos.
520,045 and 586,838. However, in a practical sense the velocities
of the exiting cooling gas are limited to sub-sonic flow and,
because the discharged coolant does not contain a liquid component,
no consideration is given to the problem of collecting any portion
of the coolant discharge stream.
SUMMARY OF THE INVENTION
The instant invention provides constructions by which not only is
the coolant discharge from liquid-cooled gas turbine buckets
collected to the extent desired, but simultaneously therewith, the
coolant vapor is made to discharge at supersonic flow thereby
enabling the efficient recovery of reaction energy therefrom. These
dual functions are made possible by combining the capability in
this liquid cooled system for increasing the pressure of vapor
generated in the system with the use of a convergent-divergent
nozzle for discharging the coolant flow from the turbine bucket. By
increasing the pressure upstream of the nozzle sufficiently so that
the discharging vaporized portion of the coolant discharge flow
will be moving at supersonic speeds, a very significant upstream
thrust is produced on the bucket acting counter to the downstream
force imposed by the working fluid and thereby reducing the axial
bending stress on the bucket.
It is to be understood that, where reference is made herein to
"vapor," "vaporize" or similar language, the term is intended to
embody "gas" or "gasify" or comparable term.
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 transverse sectional view through a liquid cooled gas
turbine showing the rotor disk rim, shrouded liquid-cooled turbine
bucket affixed thereto and a collection slot in the turbine casing
aligned with the turbine blade outlet for the coolant flow;
FIG. 2 is a sectional view taken on line 2--2 of FIG. 1;
FIG. 3 is a view directed radially inward showing the
interrelationship between a shroud segment and the turbine bucket
connected thereto;
FIG. 4 is a view similar to FIG. 1 showing a second embodiment of
the power augmenter of this invention and
FIG. 5 is a sectional view taken on line 5--5 of FIG. 4.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Turbine bucket 10 consists of metal skin 11 bonded to hollow core
12 having spanwise extending grooves 13a formed in the airfoil
surfaces thereof. The rectangular cooling channels, or passages, 13
defined by skin 11 and grooves 13a conduct cooling liquid
therethrough at a uniform depth beneath skin 11.
As shown, cooling channel 13b and cooling channel 13c (and,
possibly, a similar channel, not shown, on the opposite side of the
core 12) in the trailing edge of bucket 10 extend up to the tip of
the bucket and communicate with passages 14 and 14a, respectively,
passing through shroud element 16.
At the upper ends of cooling channels 13 on the pressure side of
bucket 10, these cooling channels are in flow communication with
and terminate at manifold 17 recessed into core 12. On the suction
side of bucket 10, cooling channels 13 are in flow communication
with and terminate at manifold 17a (FIG. 2) recessed into core
12.
Requisite open-circuit discharge of coolant from manifolds 17, 17a
is insured by the provision of discharge means according to this
invention, which place manifolds 17, 17a into flow communication
with annular cavity 18 in casing 19. These discharge means consist
of passageways 21, 21a, which connect to manifolds 17, 17a,
respectively, and extend in a generally radially outward direction
through the tip portion of core 12. Passageways 21 and 21a merge
upon entering enlarged, shaped passageway 22 in shroud element 16.
The coolant flow discharge passes from passageway 22 to cavity 18
via a nozzle comprising converging portion 23, throat 24 and
diverging portion 26. Cutaway portion 27 of each shroud element 16
forms the extension of diverging portion 26. The structural
interrelationship between nozzle portion 26 and its extension 27
becomes manifest in considering any two abutting shroud elements
16.
Thus, heated coolant (gas or vapor and excess liquid coolant)
discharge from manifolds 17, 17a passes through passageways 21,
21a, shaped chamber 22 and the convergent-divergent nozzle to empty
into annular cavity 18 thereby providing for collection of the
largest part of the coolant flow discharged from buckets 10.
Coolant flow collected in this manner may be removed from cavity 18
and be condensed, cooled and recirculated (in a simple cycle
system) or, in the case of a combined steam turbine/gas turbine
cycle, the coolant so collected may be conducted to, and form part
of, the feed water input to the steam turbine cycle.
Coolant streams conducted through coolant passages 13b, 13c (and a
similar passage, not shown, on the opposite side of the bucket)
traverse tip shroud 16 and serve both to cool labyrinth seals 28
and 29, respectively, and to enhance their sealing capability. A
small purge of coolant passes into the gas stream via each seal
thereby insuring exclusion of the hot working fluid from collection
cavity 18.
If the pressure in cavity 18 is maintained below the pressure in
the working fluid (either upstream or downstream of bucket 10), the
pressure ratio across the power augmenter nozzle in each tip shroud
16 can be increased sufficiently to provide supersonic flow through
convergent-divergent nozzle 26. Another way in which the pressure
upstream of nozzle 26 is raised sufficiently to produce supersonic
flow is by creating an optimum balance between the rate of coolant
supply, heat transfer to bucket 10 and the area of throat 24
employed as is taught in U.S. Patent Application Ser. No. 285,633
-- Moore, filed Sept. 1, 1972, assigned to the assignee of this
invention and incorporated by reference.
Since the direction of the discharge coolant stream is rearward
relative to the direction of rotation of bucket 10 the effective
reaction force F acting at angle .alpha. to the tangent line
provides two useful force components. Thus, F cos .alpha.
represents useful torque and F sin .alpha. reduces the centrifugal
stress on bucket 10. The reaction energy (F cos .alpha.) recovered
from the coolant discharge as described hereinabove may actually
produce a net gain in power under some operating conditions, but
any extent of reaction energy recovery will offset, at least in
part, the pumping energy required to accelerate the coolant to
bucket tip speed.
The bucket/rotor interconnection does not form part of this
invention and other arrangements e.g., dovetail buckets may be
preferred.
In the exemplary construction shown, the root end of core 12
consists of a number of finger-like projections or tines 31. These
tines 31 may present a generally rectangular profile as shown or
each tine may be tapered toward the distal end thereof to present a
generally triangular profile. Rim 32 of turbine disk 33 has grooves
34 machined therein extending to various depths and having widths
matching the different lengths and widths of bucket tines 31 such
that tines 31 will fit snuggly into the completed grooves 34 in an
interlocking relationship.
Once the proper fit has been obtained the appropriate amount of
brazing alloy is placed in each groove 34 and the buckets are
inserted and held in fixed position by a fixture. This fixture is
biased to maintain a tight fit between tines 31 and grooves 34
regardless of thermal expansion. Conventional brazing alloys having
melting points ranging from 700.degree. to 1,100.degree. C may be
used. Single metals, such as copper, may also be used.
Thereafter, the assembly (the rim with all the buckets properly
located) is furnace-brazed to provide an integral structure.
Steel alloys may be used for the skin and core, preferably those
containing at least 12 percent by weight of chromium for corrosion
resistance and heat treatable to achieve high strength.
The cutting of grooves 34 into rim 32 not only provides the
requisite configuration for fastening the bucket root and lessens
the weight of the rim, but in addition the ribs 36 between grooves
34 provide area on the upper surfaces thereof for attachment
thereto of platform elements 37 having cooling channels 38 in
juxtaposition with grooves 34 and are interconnected by other
cooling channels, not shown. The separating walls 39 between
cooling channels 38 are dimensioned to coincide with the width of
ribs 36, when in juxtaposition therewith.
Construction for metering of the coolant to the buckets is more
fully described in U.S. Pat. No. 3,658,439 -- Kydd, incorporated by
reference.
As is described in the Kydd U.S. Pat. No. 3,446,481 and Kydd U.S.
Pat. No. 3,446,482 cooling liquid (usually water) is sprayed at low
pressure in a generally radially outward direction from nozzles
(not shown herein, but preferably located on each side of disk 33)
and impinges on disk 33. The coolant thereupon moves into gutters
41, 41a defined in part by downwardly extending lip portions 42,
42a. The cooling liquid accumulates in gutters 41, 41a (cooling the
portions with which it comes into contact) being retained therein
until this liquid has been accelerated to the prevailing disk rim
velocity.
After the cooling liquid in gutters 41, 41a has been so
accelerated, this liquid drains therefrom passing radially outward
through holes 43, 43a to the underside of platform 37 from where it
is introduced into slots 13a and cooling channels 13 via a metering
system (not shown). Individual holes (not shown) may be provided to
interconnect gutter 41 with cooling channel 13b to assure greater
cooling capability at the leading edge of buckets 10. In transit,
the coolant passes over the undersurfaces of platform elements 37
and keeps these elements cool.
As the cooling liquid moves through cooling channels 13 of any
given bucket 10 a portion (the amount will depend upon the rate of
flow selected) is converted to the gaseous or vapor state as it
absorbs heat from the skin 11 and core 12 of the bucket. At the
outer ends of cooling channels 13 the vapor generated and any
remaining liquid coolant pass into manifolds 17 and 17a and exit
from the manifold system as described hereinabove.
FIGS. 4 and 5 set forth a second embodiment of this invention
wherein bucket 50 is unshrouded. The rotor, platform and
bucket/rotor interconnection are the same as in the embodiment of
FIG. 1. Cooling channels 13 terminate in manifolds 51 and 51a,
these manifolds being interconnected by passage 52. Coolant flow
received by manifold 51 from cooling channels 13 and from manifold
51a is discharged therefrom via convergent-divergent nozzle 53 in
flow communication with manifold 51. In order to accommodate nozzle
53, one or more of the cooling channel grooves 13a are made to
merge with adjacent grooves 13a in order to conduct coolant flow
therethrough to manifold 51.
As the coolant flow is discharged, nozzle 53 will more accurately
direct any liquid content therein into collection slot 54 of casing
56. Convergent-divergent nozzle 53 is employed, because as has been
noted hereinabove in connection with the preferred embodiment, with
a liquid cooled system sufficient head is provided by the coolant
supply to enable build-up of the pressure upstream of nozzle 53 to
a point at which the critical pressure ratio (the ratio of the
upstream pressure to the pressure of the ambient) is greater than
that required for supersonic flow (e.g., greater than about
2:1).
Also, the shape of the diverging portion of nozzle 43 is such that
the liquid component of the discharge stream is readily directed
radially and more effectively collected while most of the vapor (or
gas) component is ejected in the generally backward (relative to
direction of rotation) direction. The total reaction force exerted
by the vapor content of the coolant discharge is represented by F
and component F cos .beta. represents the useful torque produced,
while component F sin .beta. produces an upstream thrust on the
bucket reducing the axial bending stress on the bucket because of
its counteraction to the downstream force, imposed by the hot gas
stream.
The congergent-divergent nozzle constructions in both embodiments
may be built into the bucket and shroud castings as part of the
casting procedure. In the case of the bucket/shroud construction,
the tip shroud may conveniently be cast in two parts later joined
together over a circumferentially extending surface. Although it is
essential that a convergent-divergent nozzle be used in the
unshrouded construction, convergent nozzles may be used as well in
the shrouded construction.
A further advantage of the nozzle is that by creating a velocity of
the water and stream relative to the bucket comparable to the tip
speed, the velocity thereof relative to the stationary parts is
reduced. This reduces impact erosion of the stationary parts,
permitting longer life and/or the use of softer, cheaper materials
than would otherwise be required.
The structural integrity of the bucket as a pressure vessel and the
desired boiling temperature of the cooling water must be accounted
for in setting the liquid/vapor pressure in the bucket. The best
tradeoff is one that permits acceptable mechanical and thermal
stresses in the metal while giving maximum relative energy recovery
by the nozzle design.
* * * * *