U.S. patent application number 10/681144 was filed with the patent office on 2005-04-14 for airfoil shape for a turbine bucket.
This patent application is currently assigned to GENERAL ELECTRIC COMPANY. Invention is credited to Beddard, Thomas Bradley, Pesetsky, David Samuel.
Application Number | 20050079061 10/681144 |
Document ID | / |
Family ID | 34314118 |
Filed Date | 2005-04-14 |
United States Patent
Application |
20050079061 |
Kind Code |
A1 |
Beddard, Thomas Bradley ; et
al. |
April 14, 2005 |
AIRFOIL SHAPE FOR A TURBINE BUCKET
Abstract
Second stage turbine buckets have airfoil profiles substantially
in accordance with Cartesian coordinate values of X, Y and Z set
forth Table I wherein X and Y values are in inches and the Z values
are non-dimensional values from 0.05 to 0.95 convertible to Z
distances in inches by multiplying the Z values by the height of
the airfoil in inches. The X and Y values are distances which, when
connected by smooth continuing arcs, define airfoil profile
sections at each distance Z. The profile sections at each distance
Z are joined smoothly to one another to form a complete airfoil
shape. The X and Y distances may be scalable as a function of the
same constant or number to provide a scaled up or scaled down
airfoil section for the bucket. The nominal airfoil given by the X,
Y and Z distances lies within an envelop of .+-.0.160 inches in
directions normal to the surface of the airfoil.
Inventors: |
Beddard, Thomas Bradley;
(Simpsonville, SC) ; Pesetsky, David Samuel;
(Greenville, SC) |
Correspondence
Address: |
NIXON & VANDERHYE P.C./G.E.
1100 N. GLEBE RD.
SUITE 800
ARLINGTON
VA
22201
US
|
Assignee: |
GENERAL ELECTRIC COMPANY
Schenectady
NY
|
Family ID: |
34314118 |
Appl. No.: |
10/681144 |
Filed: |
October 9, 2003 |
Current U.S.
Class: |
416/243 |
Current CPC
Class: |
F05D 2250/50 20130101;
Y10S 416/02 20130101; Y10S 416/05 20130101; F01D 5/141 20130101;
F05D 2240/301 20130101 |
Class at
Publication: |
416/243 |
International
Class: |
B63H 001/26 |
Claims
What is claimed is:
1. A turbine bucket including a bucket airfoil having an airfoil
shape, the airfoil having a nominal profile substantially in
accordance with Cartesian coordinate values of X, Y and Z set forth
in Table I wherein the Z values are non-dimensional values from
0.05 to 0.95 convertible to Z distances in inches by multiplying
the Z values by a height of the airfoil in inches, and wherein X
and Y are distances in inches which, when connected by smooth
continuing arcs, define airfoil profile sections at each distance
Z, the profile sections at the Z distances being joined smoothly
with one another to form a complete airfoil shape.
2. A turbine bucket according to claim 1 forming part of a second
stage of a turbine.
3. A turbine bucket according to claim 1 wherein said airfoil shape
lies in an envelope within .+-.0.160 inches in a direction normal
to any airfoil surface location.
4. A turbine bucket according to claim 1 wherein the height of the
turbine airfoil from Z=0.0% span to Z=100% span is 14.290
inches.
5. A turbine bucket including a bucket airfoil having an uncoated
nominal airfoil profile substantially in accordance with Cartesian
coordinate values of X, Y and Z set forth in Table I wherein the Z
values are non-dimensional values from 0.05 to 0.95 convertible to
Z distances in inches by multiplying the Z values by a height of
the airfoil in inches, and wherein X and Y are distances in inches
which, when connected by smooth continuing arcs, define airfoil
profile sections at each Z distance, the profile sections at the Z
distances being joined smoothly with one another to form a complete
airfoil shape, the X and Y distances being scalable as a function
of the same constant or number to provide a scaled-up or
scaled-down airfoil.
6. A turbine bucket according to claim 5 forming part of a second
stage of a turbine.
7. A turbine bucket according to claim 5 wherein said airfoil shape
lies in an envelope within .+-.0.160 inches in a direction normal
to any airfoil surface location.
8. A turbine bucket according to claim 5 wherein the height of the
turbine airfoil from Z=0.0% span to Z=100% span is 14.290
inches.
9. A turbine comprising a turbine wheel having a plurality of
buckets, each of said buckets including an airfoil having an
airfoil shape, said airfoil having a nominal profile substantially
in accordance with Cartesian coordinate values of X, Y and Z set
forth in Table I wherein the Z values are non-dimensional values
from 0.05 to 0.95 convertible to Z distances in inches by
multiplying the Z values by a height of the airfoil in inches, and
wherein X and Y are distances in inches which, when connected by
smooth continuing arcs, define the airfoil profile sections at each
distance Z, the profile sections at the Z distances being joined
smoothly with one another to form a complete airfoil shape.
10. A turbine according to claim 9 wherein the turbine wheel
comprises a second stage of-the turbine.
11. A turbine according to claim 9 wherein the turbine wheel has 92
buckets and X represents a distance parallel to the turbine axis of
rotation.
12. A turbine according to claim 9 wherein the height of the
turbine airfoil from Z=0.0% span to Z 100% span is 14.290
inches.
13. A turbine according to claim 9 wherein the radial distance from
an axial centerline of the turbine to the Z value at 0.0% of span
is 46.828 inches.
14. A turbine according to claim 9 wherein the radial distance from
the axial centerline of the turbine wheel to the Z value at 100% of
span is 61.118 inches.
15. A turbine comprising a turbine wheel having a plurality of
buckets, each of said buckets including an airfoil having an
uncoated nominal airfoil profile substantially in accordance with
Cartesian coordinate values of X, Y and Z set forth in Table I
wherein the Z values are non-dimensional values from 0.05 to 0.95
convertible to Z distances in inches by multiplying the Z values by
a height of the airfoil in inches, and wherein X and Y are
distances in inches which, when connected by smooth continuing
arcs, define airfoil profile sections at each distance Z, the
profile sections at the Z distances being joined smoothly with one
another to form a complete airfoil shape, the X and Y distances
being scalable as a function of the same constant or number to
provide a scaled-up or scaled-down bucket airfoil.
16. A turbine according to claim 15 wherein the turbine wheel
comprises a second stage of the turbine.
17. A turbine according to claim 15 wherein the turbine wheel has
92 buckets and X represents a distance parallel to the turbine axis
of rotation.
18. A turbine according to claim 15 wherein the height of the
turbine airfoil from Z=0.0% span to Z=100% span is 14.290
inches.
19. A turbine according to claim 15 wherein the radial distance
from an axial centerline of the turbine wheel to the Z value at
0.0% of span is 46.828 inches.
20. A turbine according to claim 15 wherein the wherein the radial
distance from the axial centerline of the turbine wheel to the Z
value at 92% of span is 61.118 inches.
21. A turbine according to claim 15 wherein said airfoil shape lies
in an envelope within .+-.0.160 inches in a direction normal to any
airfoil surface location.
Description
BACKGROUND OF THE INVENTION
[0001] The present invention relates to an airfoil for a bucket of
a stage of a gas turbine and particularly relates to a second stage
turbine bucket airfoil profile.
[0002] Many system requirements must be met for each stage of the
hot gas path section of a gas turbine in order to meet design goals
including overall improved efficiency and airfoil loading.
Particularly, the buckets of the second stage of the turbine
section must meet the thermal and mechanical operating requirements
for that particular stage.
BRIEF DESCRIPTION OF THE INVENTION
[0003] In accordance with the preferred embodiment of the present
invention there is provided a unique airfoil shape for a bucket of
a gas turbine, preferably the second stage bucket, that enhances
the performance of the gas turbine. The airfoil shape hereof also
improves the interaction between various stages of the turbine and
affords improved aerodynamic efficiency while simultaneously
reducing second stage airfoil thermal and mechanical stresses.
[0004] The bucket airfoil profile is defined by a unique loci of
points to achieve the necessary efficiency and loading requirements
whereby improved turbine performance is obtained. These unique loci
of points define the nominal airfoil profile and are identified by
the X, Y and Z Cartesian coordinates of Table I which follows. The
1100 points for the coordinate values shown in Table I are relative
to the turbine centerline and for a cold, i.e., room temperature
bucket at various cross-sections of the bucket airfoil along its
length. The positive X, Y and Z directions are axial toward the
exhaust end of the turbine, tangential in the direction of engine
rotation and radially outwardly toward the bucket tip,
respectively. The X and Y coordinates are given in distance
dimensions, e.g., units of inches, and are joined smoothly at each
Z location to form a smooth continuous airfoil cross-section. The Z
coordinates are given in non-dimensionalized form from 5% span to
95% span and therefore exclude fillet regions at the platform and
tip shroud. By multiplying the airfoil height dimension, e.g., in
inches, by the non-dimensional Z value of Table I, the airfoil
shape, i.e., the profile, of the bucket airfoil is obtained. Each
defined airfoil section in the X, Y plane is joined smoothly with
adjacent airfoil sections in the Z direction to form the complete
airfoil shape.
[0005] It will be appreciated that as each bucket airfoil heats up
in use, the profile will change as a result of mechanical loading
and temperature. Thus, the cold or room temperature profile is
given by the X, Y and Z coordinates for manufacturing purposes.
Because a manufactured bucket airfoil profile may be different from
the nominal airfoil profile given by the following table, a
distance of plus or minus 0.160 inches from the nominal profile in
a direction normal to any surface location along the nominal
profile and which includes any coating, defines a profile envelope
for this bucket airfoil. The airfoil shape is robust to this
variation without impairment of the mechanical and aerodynamic
functions of the bucket.
[0006] It will also be appreciated that the airfoil can be scaled
up or scaled down geometrically for introduction into similar
turbine designs. Consequently, the X and Y coordinates in inches of
the nominal airfoil profile given below may be a function of the
same constant or number. That is, the X and Y coordinate values in
inches may be multiplied or divided by the same constant or number
to provide a scaled up or scaled down version of the bucket airfoil
profile while retaining the airfoil section shape.
[0007] In a preferred embodiment according to the present
invention, there is provided a turbine bucket including a bucket
airfoil having an airfoil shape, the airfoil having a nominal
profile substantially in accordance with Cartesian coordinate
values of X, Y and Z set forth in Table I wherein the Z values are
non-dimensional values from 0.05 to 0.95 convertible to Z distances
in inches by multiplying the Z values by a height of the airfoil in
inches, and wherein X and Y are distances in inches which, when
connected by smooth continuing arcs, define airfoil profile
sections at each distance Z, the profile sections at the Z
distances being joined smoothly with one another to form a complete
airfoil shape.
[0008] In a further preferred embodiment according to the present
invention, there is provided a turbine bucket including a bucket
airfoil having an uncoated nominal airfoil profile substantially in
accordance with Cartesian coordinate values of X, Y and Z set forth
in Table I wherein the Z values are non-dimensional values from
0.05 to 0.95 convertible to Z distances in inches by multiplying
the Z values by a height of the airfoil in inches, and wherein X
and Y are distances in inches which, when connected by smooth
continuing arcs, define airfoil profile sections at each Z
distance, the profile sections at the Z distances being joined
smoothly with one another to form a complete airfoil shape, the X
and Y distances being scalable as a function of the same constant
or number to provide a scaled-up or scaled-down airfoil.
[0009] In a further preferred embodiment according to the present
invention, there is provided a turbine comprising a turbine wheel
having a plurality of buckets, each of the buckets including an
airfoil having an airfoil shape, the airfoil having a nominal
profile substantially in accordance with Cartesian coordinate
values of X, Y and Z set forth in Table I wherein the Z values are
non-dimensional values from 0.05 to 0.95 convertible to Z distances
in inches by multiplying the Z values by a height of the airfoil in
inches, and wherein X and Y are distances in inches which, when
connected by smooth continuing arcs, define the airfoil profile
sections at each distance Z, the profile sections at the Z
distances being joined smoothly with one another to form a complete
airfoil shape.
[0010] In a further preferred embodiment according to the present
invention, there is provided a turbine comprising a turbine wheel
having a plurality of buckets, each of the buckets including an
airfoil having an uncoated nominal airfoil profile substantially in
accordance with Cartesian coordinate values of X, Y and Z set forth
in Table I wherein the Z values are non-dimensional values from
0.05 to 0.95 convertible to Z distances in inches by multiplying
the Z values by a height of the airfoil in inches, and wherein X
and Y are distances in inches which, when connected by smooth
continuing arcs, define airfoil profile sections at each distance
Z, the profile sections at the Z distances being joined smoothly
with one another to form a complete airfoil shape, the X and Y
distances being scalable as a function of the same constant or
number to provide a scaled-up or scaled-down bucket airfoil.
BRIEF DESCRIPTION OF THE DRAWINGS
[0011] FIG. 1 is a schematic representation of a hot gas path
through multiple stages of a gas turbine and illustrates a second
stage bucket airfoil according to a preferred embodiment of the
present invention;
[0012] FIG. 2 is a perspective view of a bucket according to a
preferred embodiment of the present invention with the bucket
airfoil illustrated in conjunction with its platform and its axial
entry dovetail connection;
[0013] FIGS. 3 and 4 are side elevational views of the bucket of
FIG. 2 and associated platform and dovetail connection as viewed in
a generally circumferential direction from the suction and pressure
sides, respectively; and
[0014] FIG. 5 is a perspective view of the bucket as viewed
generally from the suction side of the airfoil.
DETAILED DESCRIPTION OF THE INVENTION
[0015] Referring now to the drawings, particularly to FIG. 1, there
is illustrated a hot gas path, generally designated 10, of a gas
turbine 12 including a plurality of turbine stages. Three stages
are illustrated. For example, the first stage comprises a plurality
of circumferentially spaced nozzles 14 and buckets 16. The nozzles
are circumferentially spaced one from the other and fixed about the
axis of the rotor. The first stage buckets 16, of course, are
mounted on the turbine rotor 17 via a rotor wheel 19. A second
stage of the turbine 12 is also illustrated, including a plurality
of circumferentially spaced nozzles 18 and a plurality of
circumferentially spaced buckets 20 mounted on the rotor 17. The
third stage is also illustrated including a plurality of
circumferentially spaced nozzles 22 and buckets 24 mounted on rotor
17 via the rotor wheel 23. It will be appreciated that the nozzles
and buckets lie in the hot gas path 10 of the turbine, the
direction of flow of the hot gas through the hot gas path 10 being
indicated by the arrow 26.
[0016] It will be appreciated that the buckets, for example, the
buckets 20 of the second stage are mounted on a rotor wheel 21
forming part of rotor 17. Each bucket 20 is provided with a
platform 30, a shank 32 and a substantially axial entry dovetail 34
for connection with a complementary-shaped mating dovetail, not
shown, on the rotor wheel 21. It will also be appreciated that each
bucket 20 has a bucket airfoil 36 as illustrated in FIGS. 2-5.
Thus, each of the buckets 20 has an airfoil profile section 38 at
any cross-section from the airfoil root 31 at a midpoint of
platform 30 to the bucket tip 33 in the shape of an airfoil (FIG.
3).
[0017] To define the airfoil shape of each second stage bucket
airfoil 36, there is a unique set or loci of points in space that
meet the stage requirements and can be manufactured. This unique
loci of points meets the requirements for stage efficiency and
reduced thermal and mechanical stresses. The loci of points are
arrived at by iteration between aerodynamic and mechanical loadings
enabling the turbine to run in an efficient, safe and smooth
manner. The loci which defines the bucket airfoil profile comprises
a set of 1100 points relative to the axis of rotation of the
turbine. A Cartesian coordinate system of X, Y and Z values given
in Table I below define the profile of the bucket airfoil at
various locations along its length. The coordinate values for the X
and Y coordinates are set forth in inches in Table I although other
units of dimensions may be used when the values are appropriately
converted. The Z values are set forth in Table I in non-dimensional
form from 5% span to 95% span. These values exclude the fillet
regions of the platform and the tip shroud. To convert the Z value
to a Z coordinate value, e.g., in inches, the non-dimensional Z
value given in the table is multiplied by the height of airfoil in
inches. The Cartesian coordinate system has orthogonally-related X,
Y and Z axes and the X axis lies parallel to the turbine rotor
centerline, i.e., the rotary axis and a positive X coordinate value
is axial toward the aft, i.e., exhaust end of the turbine. The
positive Y coordinate value looking aft extends tangentially in the
direction of rotation of the rotor and the positive Z coordinate
value is radially outwardly toward the bucket tip.
[0018] By defining X and Y coordinate values at selected locations
in a Z direction normal to the X, Y plane, the profile section of
the bucket airfoil, e.g., the profile section 38 illustrated in
FIG. 3, at each Z distance along the length of the airfoil can be
ascertained. By connecting the X and Y values with smooth
continuing arcs, each profile section 38 at each distance Z is
fixed. The airfoil profiles of the various surface locations
between the distances Z are determined by smoothly connecting the
adjacent profile sections 38 to one another to form the airfoil
profile. These values represent the airfoil profiles at ambient,
non-operating or non-hot conditions and are for an uncoated
airfoil.
[0019] The Table I values are generated and shown to four decimal
places for determining the profile of the airfoil. However, the
fourth decimal place is not significant and may be rounded up or
down. There are typical manufacturing tolerances as well as
coatings which must be accounted for in the actual profile of the
airfoil. Accordingly, the values for the profile given in Table I
are for a nominal airfoil. It will therefore be appreciated that
.+-. typical manufacturing tolerances, i.e., .+-. values, including
any coating thicknesses, are additive to the X and Y values given
in Table I below. Accordingly, a distance of .+-.0.160 inches in a
direction normal to any surface location along the airfoil profile
defines an airfoil profile envelope for this particular bucket
airfoil design and turbine, i.e., a range of variation between
measured points on the actual airfoil surface at nominal cold or
room temperature and the ideal position of those points as given in
the Table below at the same temperature. The bucket airfoil design
is robust to this range of variation without impairment of
mechanical and aerodynamic functions.
[0020] The coordinate values given in Table I below provide the
preferred nominal profile envelope.
1TABLE I X (5%) Y (5%) Z (5%) -2.1522 -0.5661 0.05 -2.0268 -0.5826
0.05 -1.9086 -0.5264 0.05 -1.7978 -0.4561 0.05 -1.6874 -0.3851 0.05
-1.5738 -0.3195 0.05 -1.4570 -0.2598 0.05 -1.3371 -0.2065 0.05
-1.2141 -0.1608 0.05 -1.0882 -0.1238 0.05 -0.9600 -0.0959 0.05
-0.8302 -0.0772 0.05 -0.6993 -0.0677 0.05 -0.5681 -0.0679 0.05
-0.4373 -0.0779 0.05 -0.3076 -0.0976 0.05 -0.1796 -0.1264 0.05
-0.0537 -0.1636 0.05 0.0695 -0.2085 0.05 0.1900 -0.2605 0.05 0.3076
-0.3188 0.05 0.4221 -0.3828 0.05 0.5336 -0.4520 0.05 0.6422 -0.5257
0.05 0.7478 -0.6035 0.05 0.8508 -0.6849 0.05 0.9511 -0.7695 0.05
1.0491 -0.8567 0.05 1.1450 -0.9463 0.05 1.2389 -1.0380 0.05 1.3309
-1.1316 0.05 1.4214 -1.2266 0.05 1.5104 -1.3230 0.05 1.5983 -1.4205
0.05 1.6849 -1.5191 0.05 1.7700 -1.6189 0.05 1.8535 -1.7202 0.05
1.9350 -1.8231 0.05 2.0139 -1.9279 0.05 2.0907 -2.0343 0.05 2.1662
-2.1417 0.05 2.2398 -2.2503 0.05 2.3245 -2.3492 0.05 2.4476 -2.3383
0.05 2.4836 -2.2203 0.05 2.4197 -2.1058 0.05 2.3501 -1.9946 0.05
2.2820 -1.8824 0.05 2.2149 -1.7696 0.05 2.1496 -1.6558 0.05 2.0859
-1.5411 0.05 2.0234 -1.4257 0.05 1.9614 -1.3100 0.05 1.8994 -1.1943
0.05 1.8371 -1.0789 0.05 1.7739 -0.9638 0.05 1.7100 -0.8493 0.05
1.6450 -0.7352 0.05 1.5790 -0.6218 0.05 1.5118 -0.5091 0.05 1.4431
-0.3973 0.05 1.3727 -0.2865 0.05 1.3005 -0.1770 0.05 1.2261 -0.0689
0.05 1.1494 0.0376 0.05 1.0702 0.1422 0.05 0.9880 0.2446 0.05
0.9027 0.3442 0.05 0.8138 0.4407 0.05 0.7211 0.5336 0.05 0.6243
0.6223 0.05 0.5234 0.7061 0.05 0.4181 0.7844 0.05 0.3084 0.8564
0.05 0.1944 0.9214 0.05 0.0762 0.9783 0.05 -0.0458 1.0264 0.05
-0.1713 1.0648 0.05 -0.2995 1.0927 0.05 -0.4296 1.1094 0.05 -0.5607
1.1143 0.05 -0.6917 1.1078 0.05 -0.8217 1.0898 0.05 -0.9496 1.0606
0.05 -1.0746 1.0209 0.05 -1.1961 0.9715 0.05 -1.3136 0.9130 0.05
-1.4264 0.8461 0.05 -1.5342 0.7713 0.05 -1.6364 0.6890 0.05 -1.7326
0.5997 0.05 -1.8222 0.5039 0.05 -1.9047 0.4019 0.05 -1.9795 0.2941
0.05 -2.0460 0.1810 0.05 -2.1031 0.0629 0.05 -2.1497 -0.0597 0.05
-2.1844 -0.1862 0.05 -2.2030 -0.3160 0.05 -2.2002 -0.4470 0.05 X
(10%) Y (10%) Z (10%) -2.0657 -0.4577 0.10 -1.9407 -0.4441 0.10
-1.8276 -0.3841 0.10 -1.7193 -0.3154 0.10 -1.6105 -0.2474 0.10
-1.4987 -0.1846 0.10 -1.3838 -0.1275 0.10 -1.2658 -0.0775 0.10
-1.1444 -0.0361 0.10 -1.0202 -0.0043 0.10 -0.8938 0.0177 0.10
-0.7662 0.0298 0.10 -0.6380 0.0320 0.10 -0.5100 0.0243 0.10 -0.3830
0.0068 0.10 -0.2576 -0.0201 0.10 -0.1343 -0.0555 0.10 -0.0136
-0.0988 0.10 0.1043 -0.1492 0.10 0.2193 -0.2059 0.10 0.3314 -0.2683
0.10 0.4404 -0.3359 0.10 0.5464 -0.4081 0.10 0.6495 -0.4843 0.10
0.7499 -0.5641 0.10 0.8477 -0.6471 0.10 0.9431 -0.7328 0.10 1.0364
-0.8209 0.10 1.1276 -0.9110 0.10 1.2170 -1.0030 0.10 1.3047 -1.0966
0.10 1.3909 -1.1915 0.10 1.4758 -1.2877 0.10 1.5596 -1.3848 0.10
1.6422 -1.4829 0.10 1.7237 -1.5819 0.10 1.8039 -1.6820 0.10 1.8826
-1.7833 0.10 1.9595 -1.8859 0.10 2.0347 -1.9898 0.10 2.1085 -2.0948
0.10 2.1809 -2.2006 0.10 2.2609 -2.3002 0.10 2.3806 -2.2955 0.10
2.4116 -2.1799 0.10 2.3489 -2.0681 0.10 2.2831 -1.9580 0.10 2.2180
-1.8475 0.10 2.1539 -1.7364 0.10 2.0913 -1.6244 0.10 2.0301 -1.5118
0.10 1.9694 -1.3988 0.10 1.9089 -1.2857 0.10 1.8483 -1.1726 0.10
1.7871 -1.0599 0.10 1.7253 -0.9475 0.10 1.6626 -0.8356 0.10 1.5990
-0.7243 0.10 1.5344 -0.6134 0.10 1.4687 -0.5033 0.10 1.4016 -0.3940
0.10 1.3331 -0.2856 0.10 1.2628 -0.1783 0.10 1.1906 -0.0722 0.10
1.1163 0.0323 0.10 1.0396 0.1350 0.10 0.9601 0.2357 0.10 0.8776
0.3339 0.10 0.7919 0.4293 0.10 0.7026 0.5214 0.10 0.6095 0.6096
0.10 0.5125 0.6935 0.10 0.4113 0.7723 0.10 0.3059 0.8453 0.10
0.1962 0.9118 0.10 0.0824 0.9708 0.10 -0.0354 1.0215 0.10 -0.1566
1.0632 0.10 -0.2809 1.0949 0.10 -0.4074 1.1156 0.10 -0.5353 1.1251
0.10 -0.6635 1.1233 0.10 -0.7910 1.1102 0.10 -0.9169 1.0858 0.10
-1.0403 1.0510 0.10 -1.1605 1.0061 0.10 -1.2767 0.9520 0.10 -1.3884
0.8891 0.10 -1.4951 0.8179 0.10 -1.5962 0.7391 0.10 -1.6914 0.6531
0.10 -1.7800 0.5604 0.10 -1.8617 0.4616 0.10 -1.9358 0.3569 0.10
-2.0017 0.2469 0.10 -2.0583 0.1319 0.10 -2.1044 0.0123 0.10 -2.1382
-0.1114 0.10 -2.1542 -0.2385 0.10 -2.1454 -0.3661 0.10 X (20%) Y
(20%) Z (20%) -2.0064 -0.1864 0.20 -1.8894 -0.2084 0.20 -1.7752
-0.1647 0.20 -1.6689 -0.1035 0.20 -1.5645 -0.0391 0.20 -1.4586
0.0228 0.20 -1.3500 0.0797 0.20 -1.2380 0.1298 0.20 -1.1226 0.1712
0.20 -1.0040 0.2024 0.20 -0.8830 0.2226 0.20 -0.7607 0.2317 0.20
-0.6381 0.2296 0.20 -0.5162 0.2170 0.20 -0.3957 0.1942 0.20 -0.2773
0.1622 0.20 -0.1614 0.1219 0.20 -0.0485 0.0742 0.20 0.0615 0.0200
0.20 0.0615 0.0200 0.20 0.1685 -0.0401 0.20 0.2724 -0.1052 0.20
0.3734 -0.1748 0.20 0.4715 -0.2484 0.20 0.5669 -0.3256 0.20 0.6597
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0.80 0.7161 0.1416 0.80 0.6687 0.2259 0.80 0.6209 0.3099 0.80
0.5726 0.3936 0.80 0.5238 0.4771 0.80 0.4744 0.5602 0.80 0.4244
0.6429 0.80 0.3738 0.7253 0.80 0.3223 0.8071 0.80 0.2698 0.8882
0.80 0.2159 0.9685 0.80 0.1605 1.0477 0.80 0.1034 1.1257 0.80
0.0443 1.2022 0.80 -0.0169 1.2770 0.80 -0.0806 1.3497 0.80 -0.1473
1.4197 0.80 -0.2171 1.4866 0.80 -0.2904 1.5496 0.80 -0.3674 1.6080
0.80 -0.4481 1.6612 0.80 -0.5324 1.7084 0.80 -0.6202 1.7489 0.80
-0.7110 1.7819 0.80 -0.8044 1.8068 0.80 -0.8996 1.8233 0.80 -0.9959
1.8311 0.80 -1.0925 1.8294 0.80 -1.1883 1.8169 0.80 -1.2816 1.7920
0.80 -1.3698 1.7526 0.80 -1.4465 1.6943 0.80 -1.4949 1.6118 0.80 X
(90%) Y (90%) Z (90%) -1.3647 1.7661 0.90 -1.2844 1.7209 0.90
-1.1932 1.6997 0.90 -1.1020 1.6789 0.90 -1.0124 1.6519 0.90 -0.9256
1.6170 0.90 -0.8425 1.5740 0.90 -0.7632 1.5243 0.90 -0.6878 1.4689
0.90 -0.6162 1.4087 0.90 -0.5479 1.3447 0.90 -0.4824 1.2779 0.90
-0.4193 1.2088 0.90 -0.3583 1.1378 0.90 -0.2994 1.0651 0.90 -0.2422
0.9910 0.90 -0.1865 0.9158 0.90 -0.1321 0.8396 0.90 -0.0786 0.7628
0.90 -0.0261 0.6854 0.90 0.0256 0.6074 0.90 0.0767 0.5289 0.90
0.1271 0.4501 0.90 0.1771 0.3710 0.90 0.2267 0.2916 0.90 0.2760
0.2120 0.90 0.3250 0.1323 0.90 0.3737 0.0524 0.90 0.4222 -0.0276
0.90 0.4706 -0.1078 0.90 0.5189 -0.1879 0.90 0.5671 -0.2681 0.90
0.6153 -0.3484 0.90 0.6635 -0.4286 0.90 0.7118 -0.5088 0.90 0.7602
-0.5889 0.90 0.8088 -0.6689 0.90 0.8575 -0.7488 0.90 0.9063 -0.8286
0.90 0.9553 -0.9084 0.90 1.0043 -0.9881 0.90 1.0535 -1.0677 0.90
1.1028 -1.1473 0.90 1.1526 -1.2265 0.90 1.2031 -1.3053 0.90 1.2538
-1.3840 0.90 1.3092 -1.4590 0.90 1.3963 -1.4660 0.90 1.4335 -1.3864
0.90 1.3983 -1.3000 0.90 1.3592 -1.2149 0.90 1.3200 -1.1299 0.90
1.2804 -1.0451 0.90 1.2406 -0.9604 0.90 1.2004 -0.8759 0.90 1.1599
-0.7915 0.90 1.1190 -0.7073 0.90 1.0779 -0.6233 0.90 1.0365 -0.5393
0.90 0.9948 -0.4555 0.90 0.9529 -0.3719 0.90 0.9107 -0.2883 0.90
0.8683 -0.2049 0.90 0.8256 -0.1216 0.90 0.7825 -0.0385 0.90 0.7390
0.0443 0.90 0.6952 0.1270 0.90 0.6509 0.2095 0.90 0.6062 0.2917
0.90 0.5610 0.3736 0.90 0.5152 0.4553 0.90 0.4688 0.5366 0.90
0.4219 0.6175 0.90 0.3743 0.6981 0.90 0.3260 0.7783 0.90 0.2769
0.8580 0.90 0.2270 0.9371 0.90 0.1761 1.0157 0.90 0.1241 1.0935
0.90 0.0711 1.1706 0.90 0.0168 1.2468 0.90 -0.0389 1.3220 0.90
-0.0963 1.3960 0.90 -0.1557 1.4683 0.90 -0.2173 1.5388 0.90 -0.2812
1.6071 0.90 -0.3476 1.6731 0.90 -0.4168 1.7361 0.90 -0.4891 1.7955
0.90 -0.5649 1.8503 0.90 -0.6445 1.8996 0.90 -0.7276 1.9425 0.90
-0.8141 1.9782 0.90 -0.9034 2.0060 0.90 -0.9952 2.0239 0.90 -1.0886
2.0294 0.90 -1.1816 2.0202 0.90 -1.2705 1.9917 0.90 -1.3448 1.9360
0.90 -1.3880 1.8543 0.90 X (95%) Y (95%) Z (95%) -1.3374 1.9806
0.95 -1.3211 1.8911 0.95 -1.2461 1.8393 0.95 -1.1572 1.8126 0.95
-1.0688 1.7844 0.95 -0.9830 1.7490 0.95 -0.9010 1.7055 0.95 -0.8235
1.6545 0.95 -0.7504 1.5973 0.95 -0.6814 1.5353 0.95 -0.6160 1.4694
0.95 -0.5536 1.4007 0.95 -0.4938 1.3297 0.95 -0.4360 1.2571 0.95
-0.3797 1.1833 0.95 -0.3246 1.1086 0.95 -0.2707 1.0330 0.95 -0.2178
0.9567 0.95 -0.1658 0.8799 0.95 -0.1145 0.8025 0.95 -0.0639 0.7247
0.95 -0.0137 0.6466 0.95 0.0360 0.5681 0.95 0.0852 0.4895 0.95
0.1342 0.4106 0.95 0.1828 0.3315 0.95 0.2311 0.2523 0.95 0.2792
0.1729 0.95 0.3272 0.0934 0.95 0.3749 0.0138 0.95 0.4226 -0.0658
0.95 0.4703 -0.1454 0.95 0.5181 -0.2251 0.95 0.5659 -0.3046 0.95
0.6139 -0.3841 0.95 0.6621 -0.4634 0.95 0.7105 -0.5426 0.95 0.7590
-0.6218 0.95 0.8076 -0.7008 0.95 0.8562 -0.7799 0.95 0.9049 -0.8590
0.95 0.9535 -0.9381 0.95 1.0020 -1.0172 0.95 1.0509 -1.0961 0.95
1.1006 -1.1745 0.95 1.1515 -1.2521 0.95 1.2019 -1.3301 0.95 1.2553
-1.4057 0.95 1.3404 -1.4224 0.95 1.3859 -1.3479 0.95 1.3541 -1.2613
0.95 1.3160 -1.1766 0.95 1.2777 -1.0921 0.95 1.2390 -1.0077 0.95
1.2001 -0.9234 0.95 1.1607 -0.8394 0.95 1.1211 -0.7554 0.95 1.0812
-0.6716 0.95 1.0411 -0.5879 0.95 1.0008 -0.5043 0.95 0.9602 -0.4208
0.95 0.9194 -0.3374 0.95 0.8782 -0.2542 0.95 0.8368 -0.1711 0.95
0.7951 -0.0882 0.95 0.7530 -0.0055 0.95 0.7105 0.0770 0.95 0.6675
0.1593 0.95 0.6241 0.2414 0.95 0.5803 0.3232 0.95 0.5358 0.4047
0.95 0.4908 0.4858 0.95 0.4451 0.5666 0.95 0.3988 0.6471 0.95
0.3517 0.7271 0.95 0.3039 0.8067 0.95 0.2554 0.8858 0.95 0.2060
0.9644 0.95 0.1559 1.0425 0.95 0.1050 1.1201 0.95 0.0533 1.1973
0.95 0.0009 1.2739 0.95 -0.0523 1.3499 0.95 -0.1066 1.4252 0.95
-0.1621 1.4996 0.95 -0.2190 1.5730 0.95 -0.2771 1.6452 0.95 -0.3368
1.7162 0.95 -0.3989 1.7853 0.95 -0.4639 1.8515 0.95 -0.5331 1.9133
0.95 -0.6077 1.9686 0.95 -0.6866 2.0174 0.95 -0.7685 2.0610 0.95
-0.8538 2.0976 0.95 -0.9425 2.1247 0.95 -1.0341 2.1393 0.95 -1.1267
2.1376 0.95 -1.2162 2.1141 0.95 -1.2903 2.0594 0.95
[0021] In this preferred embodiment of a second stage turbine
bucket, there are ninety-two (92) bucket airfoils which are
air-cooled. In the preferred embodiment of the second stage bucket
hereof, the bucket radial height is 14.290 inches between 0% span
and 100% span. The airfoil radial height at 0% span from the engine
centerline is 46.828 inches and 61.118 inches at 100% span. The
airfoil sections in Table I start at Z=5% span and end at Z=95%
span and this eliminates fillet regions. While not forming part of
the present invention, each second stage bucket airfoil 36 includes
a plurality of internal air-cooling passages, not shown, which
exhaust cooling air into the hot gas path adjacent the tip shroud
42.
[0022] It will also be appreciated that the airfoil disclosed in
the above Table I may be scaled up or down geometrically for use in
other similar turbine designs. Consequently, the coordinate values
set forth in Table I may be scaled upwardly or downwardly such that
the airfoil profile shape remains unchanged. The X and Y coordinate
values of Table I multiplied or divided by a constant number would
represent a scaled version.
[0023] To scale the bucket airfoil in the Z direction, the constant
may also be applied to the 5% and 95% radial spans given in Table
I.
[0024] While the invention has been described in connection with
what is presently considered to be the most practical and preferred
embodiment, it is to be understood that the invention is not to be
limited to the disclosed embodiment, but on the contrary, is
intended to cover various modifications and equivalent arrangements
included within the spirit and scope of the appended claims.
* * * * *