(12) United States Patent (10) Patent No.: US 8,876,485 B2

Transcription

1 USOO B2 (12) United States Patent (10) Patent No.: US 8,876,485 B2 Gustafson et al. (45) Date of Patent: Nov. 4, 2014 (54) TURBINE NOZZLE AIRFOIL PROFILE 6,736,599 B1 5/2004 Jacks et al. 7, B2 * 5/2009 Humanchuk et al , / A1 2/2005 Arness et al ,191 (75) Inventors: R s E. SC 2007/ A1* 9/2007 Girgis et al ,223 A (US); Aaron Gregory Winn, Piedmont, 2007/ A1 * 10, 2007 Botrel et al ,223 A SC (US) 2009/ A1 6/2009 Mariotti et al. 2010/ A1* 3/2010 Spracher et al ,208.2 (73) Assignee: General Electric Company, 2010, O A1 6, 2010 Bielek et al. Schenectady, NY (US) 2012/ A1 1/2012 Bleuzen et al ,223 R 2013/ A1* 3/2013 Herzlinger et al ,223 A 2013, A1 3/2013 Collier et al ,223 A (*) Notice: Subject to any disclaimer, the term of this 2013/ A1* 5, 2013 Gustafson et al ,202 patent is extended or adjusted under 35 U.S.C. 154(b) by 508 days. * cited by examiner (21) Appl. No.: 13/304,730 Primary Examiner Ned Landrum (22) Filed: Nov. 28, 2011 Assistant Examiner Su Htay (65) Prior Publication Data (74) Attorney, Agent, or Firm Sutherland Asbill & Brennan LLP US 2013/O A1 May 30, 2013 (51) Int. Cl. (57) ABSTRACT FOID 9/04 ( ) FOID 5/14 ( ) The present application provides a turbine nozzle including (52) U.S. Cl. an airfoil shape. The airfoil shape may have a nominal profile USPC /243: 416/223 A: 416/DIG. 2: Substantially in accordance with Cartesian coordinate values 415/191: 415/193; 415/208.2:415/209.1 of X, Y and Z set forth in Table 1. The Cartesian coordinate (58) Field of Classification Search values of X, Y and Z are non-dimensional values from 0% to USPC / , , 208.2, 209.1; 100% convertible to dimensional distances in inches by mul 416/223 R, 223 A, 243, DIG. 2, DIG. 5 tiplying the Cartesian coordinate values of X, Y and Z by a See application file for complete search history. height of the airfoil in inches. The X and Y values are dis tances in inches which, when connected by Smooth continu (56) References Cited ing arcs, define airfoil profile sections at each distance Z. The U.S. PATENT DOCUMENTS 6,461,110 B1 * 10/2002 By et al ,223 A 6,474,948 B1 * 1 1/2002 Pirolla et al ,503,054 B1 1/2003 Bielek et al. airfoil profile sections at Z distances may be joined Smoothly with one another to form a complete airfoil shape. 18 Claims, 2 Drawing Sheets

2 U.S. Patent Nov. 4, 2014 Sheet 1 of 2 US 8, B2 O ". 240 X -Ho Fig. 2

3 U.S. Patent Nov. 4, 2014 Sheet 2 of 2 US 8, B2

4 1. TURBINE NOZZLEARFOL PROFILE TECHNICAL FIELD The present application and the resultant patent relate gen erally to a turbine nozzle for a turbine engine and more particularly relate to a nozzle airfoil profile for a turbine stage. BACKGROUND OF THE INVENTION In a turbine, many system requirements should be met at each stage of the turbine so as to meet design goals. These turbine design goals may include, but are not limited to, overall improved efficiency and airfoil loading capability. For example, a turbine nozzle airfoil profile should achieve ther mal and mechanical operating requirements for that particu lar stage. Moreover, component lifetime and cost targets also should be met. There is thus a desire therefore for an improved turbine nozzle airfoil profile for use in a turbine and the like. Such an improved airfoil design should achieve performance objec tives and improve overall gas turbine performance in a com ponent with a long lifetime and reasonable manufacture and operating costs. SUMMARY OF THE INVENTION The present application and the resultant patent thus pro vide a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile Substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by Smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Zdistances being joined Smoothly with one another to form a complete airfoil shape. The present application and the resultant patent further provide a turbine nozzle including an airfoil having a Suction side uncoated nominal airfoil profile Substantially in accor dance with suction-side Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by Smooth continuing arcs, define airfoil profile sections at each Z distance. The airfoil profile sections at the Z distances may be joined Smoothly with one another to form a complete suction-side airfoil shape. The X,Y and Z distances being scalable as a function of the same constant or number to provide a scaled-up or scaled-down airfoil. The present application and the resultant patent further provide a turbine with a number of nozzles having an airfoil having an airfoil shape. The airfoils having a nominal profile Substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by mul tiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are dis tances in inches which, when connected by Smooth continu ing arcs, define airfoil profile sections at each Zdistance. The US 8,876,485 B airfoil profile sections at the Z distances may be joined Smoothly with one another to form a complete airfoil shape. These and other features and improvements of the present application and the resultant patent should become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the sev eral drawings and the appended claims. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a schematic diagram of a gas turbine engine. FIG. 2 is a schematic diagram of a portion of a turbine having a nozzle arrangement as may be described herein. FIG.3 is a perspective view of a portion of a turbine nozzle showing an airfoil as may be described herein. FIG. 4 is a cross-sectional view of the airfoil of FIG. 3. DETAILED DESCRIPTION Referring now to the drawings, in which like numerals refer to like elements throughout the several views, FIG. 1 shows a schematic view of gas turbine engine 10 as may be used herein. The gas turbine engine 10 may include a com pressor 15. The compressor 15 compresses an incoming flow of air 20. The compressor 15 delivers the compressed flow of air 20 to a combustor 25. The combustor 25 mixes the com pressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35. Although only a single combustor 25 is shown, the gasturbine engine 10 may include any number of combustors 25. The flow of combustion gases 35 is in turn delivered to a turbine 40. The flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work. The mechanical work pro duced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 Such as an electrical generator and the like. The gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels. The gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, N.Y., including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like. The gas turbine engine 10 may have different configurations and may use other types of components. Other types of gas turbine engines also may be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together. FIG. 2 shows a schematic diagram of a turbine 100 as may be described herein. The turbine 100 may include a first stage 110, a second stage 120, a third stage 130, a fourth stage 140, a fifth stage 142, a sixth stage 144, and the like. Any number ofstages may be used herein. For example, the first stage 110 may include a number of circumferentially spaced nozzles 150 and buckets 160. The first stage buckets 160 are mounted on a turbine rotor 170. The nozzles 150 are circumferentially spaced one from the other and fixed about an axis of the rotor. The second stage of the turbine 100 includes a number of circumferentially spaced nozzles 180 and a number of cir cumferentially spaced buckets 190 mounted on the rotor 170. The third stage also includes a number of circumferentially spaced nozzles 200 and buckets 210 mounted on the rotor 170. The fourth stage 140 includes a number of circumferen tially spaced nozzles 220 and buckets 230 mounted on the rotor 170. The fifth stage 142 includes a number of circum ferentially spaced nozzles 232 and buckets 234 mounted on the rotor 170. The sixth stage 144 includes a number of circumferentially spaced nozzles 236 and buckets 238

5 3 mounted on the rotor 170. Again, any number of stages may be used herein. It will be appreciated that the nozzles and buckets lie in a hot gas path 240 of the turbine. Other com ponents and other configurations may be used herein. Referring to FIGS. 3 and 4, it will be appreciated that each nozzle 180 has a nozzle airfoil 250 as illustrated. The airfoil 250 may have a suction side 260 and a pressure side 270. The suction side 260 is shown in FIG. 4 and the pressure side 270 is located on the opposing side of the airfoil 250. Thus, each of the nozzles 180 has a nozzle airfoil profile at any cross section in the shape of the airfoil 250. A tip 280 is at or near the top of the airfoil 250 and a base 290 is at or near the bottom of the airfoil 250. The airfoil 250 also includes a leading edge 300, a trailing edge 310, and a chord length 320 therebetween. The base 290 corresponds to the non-dimensional Z value of Table 1 at Z equals 0. The tip 280 of the nozzle airfoil 250 corresponds to the non-dimensional Z value of Table 1 at Z equals 100. The X, Y, and Z values are given in percentage values of the airfoil length. As one example only, the height of the turbine nozzle or airfoil 250 may be from about 5 inches to about 50 inches (about 12 centimeters to about 130 centi meters). However, it is to be understood that heights below or above this range may also be employed as desired in the specific application. The airfoil 250 may be used for any stage, including but not limited to a first stage, a second stage, a third stage, a fourth stage, a fifth stage, and the like. The gas turbine hot gas path 240 requires airfoils 250 that meet system requirements of aerodynamic and mechanical blade loading and efficiency. To define the airfoil shape of each nozzle airfoil, there is a unique set or loci of points in space that meet the stage requirements and can be manufac tured. These unique loci of points meet the requirements for stage efficiency and are arrived at by iteration between aero dynamic and mechanical loadings enabling the turbine to run in an efficient, safe and Smooth manner. These points are unique and specific to the system. The locus that defines the nozzle airfoil profile includes a set of about 2,200 points with X, Y and Z dimensions relative to a reference origin coordi nate system. The Cartesian coordinate system of X, Y and Z values given in Table 1 below defines the profile of the nozzle airfoil at various locations along its length. Table 1 lists data for a non-coated airfoil. The envelope/tolerance for the coor dinates is about +/-5% in a direction normal to any airfoil surface location and/or about +/-5% of the chord length 320 in a direction nominal to any airfoil Surface location. The point data origin is the leading edge of the base 290. The coordinate values for the X. Yand Z coordinates are set forth in non-dimensionalized units by the blade height in Table 1 although other units of dimensions may be used when the values are appropriately converted. The X,Y, and Z values set forth in Table 1 are also expressed in non-dimensional form (X,Y, and Z) from 0% to 100% of the blade or airfoil height. As one example only, the Cartesian coordinate values of X,Y and Z may be convertible to dimensional distances by multi plying the X, Y and Z values by a height of the airfoil at the trailing edge and multiplying by a constant number (e.g., 100). To convert the Z value to a Z coordinate value, e.g., in inches, the non-dimensional Z value given in Table 1 is mul tiplied by the Z length of the airfoil in inches. As described above, the Cartesian coordinate system has orthogonally related X, Y and Z axes and the X axis lies generally 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 extends tangentially in the direction of rotation of the rotor and the positive Z coordinate value is radially outwardly US 8,876,485 B toward the nozzle tip. All the values in Table 1 are given at room temperature and are unfilleted. By defining X and Y coordinate values at selected locations in a Z direction normal to the X,Y plane, the profile section or airfoil shape of the nozzle airfoil, at each Zdistance along the length of the airfoil can be ascertained. By connecting the X and Y values with Smooth continuing arcs, each profile sec tion at each distance Z is fixed. The airfoil profiles of the various surface locations between the distances Z are deter mined by Smoothly connecting the adjacent profile sections to one another to form the airfoil profile. The Table 1 values are generated and shown to four deci mal places for determining the profile of the airfoil. As the blade heats up in Surface, stress and temperature will cause a change in the X, Y and Z values. Accordingly, the values for the profile given in Table I represent ambient, non-operating or non-hot conditions (e.g., room temperature) and are for an uncoated airfoil. There are typical manufacturing tolerances as well as coat ings which must be accounted for in the actual profile of the airfoil. Each section is joined smoothly with the other sec tions to form the complete airfoil shape. 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 1 below. Accordingly, a distance of +/-5% in a direction normal to any surface loca tion along the airfoil profile defines an airfoil profile envelope for this particular nozzle 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 data is scalable and the geometry pertains to all aerodynamic scales, at above and/or below 3000 RPM. The nozzle airfoil design is robust to this range of variation without impairment of mechanical and aerody namic functions. TABLE 1 N Location X Y Z. 1 Suction-Side O O O. 2 Suction-Side -OOOS O. 3 Suction-Side -O.OO73 -O.O237 O. 4 Suction-Side -OOO67 -O.O363 O. 5 Suction-Side -OOO42 -O.0486 O. 6 Suction-Side -4 -O.O606 O. 7 Suction-Side O.OO46 -O.O721 O. 8 Suction-Side O.O O. 9 Suction-Side O.O170 -O.O940 O. 10 Suction-Side O.O O. 11 Suction-Side O.O O. 12 Suction-Side O.O404 -O.1236 O. 13 Suction-Side O.O492 -O-1326 O. 14 Suction-Side O.OS O. 15 Suction-Side O.O O. 16 Suction-Side O.O O. 17 Suction-Side O O. 18 Suction-Side O.O991 -O.1707 O. 19 Suction-Side O O. 2O Suction-Side O O. 21 Suction-Side O O. 22 Suction-Side O O.1922 O. 23 Suction-Side O O.1961 O. 24 Suction-Side O O.1995 O. 25 Suction-Side O O. 26 Suction-Side O O. 27 Suction-Side O O-2060 O. 28 Suction-Side O O68 O. 29 Suction-Side O O. 30 Suction-Side O O-206S O. 31 Suction-Side O O. 32 Suction-Side O O36 O.

6

7

8

9

10

11

12

13

14

15

16 US 8,876,485 B TABLE 1-continued TABLE 1-continued N Location X Y Z. N Location X Y Z. 193 de -OOO43 O.1949 O.7OOO 71 Suction-Side O.3306 O de -O.O139 O.1940 O.7OOO 5 72 Suction-Side O.3430 O de -O.O235 O.1924 O.7OOO 73 Suction-Side 0.56O7 O.3554 O de -O.O328 O.1900 O.7OOO 74 Suction-Side O.S6SO O.3679 O de -O.O418 O.1864 O.7OOO 75 Suction-Side O.S693 O3804 O de -O.OSO2 O.1815 O.7OOO 76 Suction-Side O.3928 O de O.7OOO 77 Suction-Side O.5777 O.4053 O de -O.O634 O.1675 O.7OOO Suction-Side O.S819 O4178 O Suction-Side -O.O768 O.1832 O Suction-Side O.S861 O4304 O Suction-Side -O.O796 O.1703 O O Suction-Side O.S902 O4429 O Suction-Side -O.O O Suction-Side O.S943 O4554 O Suction-Side -O.O774 O.1442 O Suction-Side O.S984 O46.79 O Suction-Side -O.O736 O.1315 O Suction-Side O.6O2S O4805 O Suction-Side -O.O684 O O Suction-Side O.606S O4930 O Suction-Side -O.O621 O.1079 O Suction-Side O6106 OSOS6 O Suction-Side O.0969 O Suction-Side O.6147 O.S181 O Suction-Side -O.O467 O.O865 O Suction-Side O O Suction-Side -O.O379 O.O766 O Suction-Side O6228 O.S.432 O Suction-Side -O.O286 OO674 O Suction-Side O O Suction-Side -O.O187 O.OS86 O Suction-Side O-6309 O.S683 O Suction-Side -OOO84 O.OSO4 O O 91 Suction-Side O-6349 O.S809 O Suction-Side O.OO22 O.O426 O Suction-Side O.6390 O.S934 O Suction-Side O.O132 O.O352 O Suction-Side O.6430 O6060 O Suction-Side O.O244 O.O.283 O Suction-Side O.6471 O O Suction-Side O.O359 O.O219 O Suction-Side O.6S11 O6311 O Suction-Side O.O476 O.O158 O Suction-Side O.6SS2 O6436 O Suction-Side O.O101 O Suction-Side O.6592 O.6562 O O Suction-Side O.O716 O.0049 O Suction-Side O.6633 O.6687 O Suction-Side O.O839 O O Suction-Side O.6673 O.6813 O Suction-Side O.O963 -OOO45 O.8000 OO Suction-Side O.6709 O.6939 O Suction-Side O OOO86 O.8000 O1 de O6645 O.7045 O Suction-Side O O.O123 O.8000 O2 de O.6551 O.7040 O Suction-Side O O.O15S O O3 de O6494 O.6962 O Suction-Side O O.O183 O.8000 O4 de O.6452 O.6874 O Suction-Side O O.O2O6 O de O O Suction-Side O O.8000 O6 de O.6363 O.67OO O Suction-Side O O.O237 O.8000 O7 de O O.6614 O Suction-Side O O.8000 O8 de O-6272 O.6528 O Suction-Side O O.O248 O de O6224 O6443 O Suction-Side O O.0245 O de O.6176 O.6358 O Suction-Side O O.O236 O de O6128 O.6273 O Suction-Side O2S O de O6079 O6189 O Suction-Side O O.O199 O de O.6O29 O.6105 O Suction-Side O O.O170 O de O6021 O Suction-Side O O.O135 O de O.S938 O Suction-Side O OOO94 O de O Suction-Side OOO46 O de O.S823 O.5773 O Suction-Side O.OOO8 O de O.S691 O Suction-Side O.3392 O.OO69 O de O.5717 O.S609 O Suction-Side O.3506 O.O136 O O de O.S663 O.SS28 O Suction-Side O.3616 O.O2O8 O de O.S608 O.S447 O Suction-Side O.O.285 O de O.S366 O Suction-Side O.382S O.O368 O de O.S497 O.S286 O Suction-Side O.3924 O.O4S5 O de O5441 O.S2O6 O Suction-Side O4019 O.OS47 O de O Suction-Side O4111 O.O642 O de O.S328 OSO48 O Suction-Side O4198 O.0740 O de O4969 O Suction-Side O4283 O.O842 O de O.S212 O4890 O Suction-Side O4364 O.O946 O de O4812 O Suction-Side O.1052 O de OSO94 O.473S O Suction-Side O4516 O-1161 O de O4657 O.8000 S4 Suction-Side O.4588 O.1271 O de O4974 O458O O Suction-Side O4658 O.1383 O de O.4914 O4504 O Suction-Side O.4725 O.1497 O de O4852 O4428 O Suction-Side O.4789 O.1612 O de O.4790 O4353 O Suction-Side O4851 O.1728 O de O.4727 O4278 O Suction-Side O4911 O.1845 O de O4664 O4204 O Suction-Side O4970 O.1964 O de O46OO O4130 O Suction-Side OSO26 O.2083 O de O4536 O.4057 O Suction-Side OSO8O O.22O3 O de O4471 O3984 O Suction-Side O.S134 O-2324 O de O4405 O.3912 O Suction-Side O.S186 O.2445 O de O4338 O3841 O Suction-Side O.S O de O O Suction-Side O.S286 O.2689 O de O42O3 O.3700 O Suction-Side O.S334 O.2812 O de O4134 O.3631 O Suction-Side O.S382 O.2934 O de O4O64 O.3563 O Suction-Side O.S428 O.3058 O de O.3993 O.3495 O Suction-Side O.S474 O.3182 O de O.3922 O.3429 O.8000

17

18

19 31 TABLE 1-continued US 8,876,485 B2 32 TABLE 1-continued Location Y Z. N Location X Y Z O OO O1 O2 O3 O4 05 O6 O7 O O O4957 OSO13 OSO68 O.S122 O.S O.S42O OS O.S603 O.S647 O.S O.S822 O.S865 O.S O.S993 O.6O3S O6078 O612O O6163 O.62OS O.6247 O.629O O O.6417 O.6459 O.6SO2 O6544 O.6586 O6628 O.6671 O.6709 O O.6497 O.6452 O.6406 O.6359 O6312 O6264 O.6215 O.616S O.6114 O.6063 O.6O11 O.S O.S O.S742 O.S686 O.S O.SS16 O.S.458 O.S400 O.S341 O.S282 O.S223 O.S163 O.S102 OSO41 O4979 O4917 O.4854 O.4791 O.4727 O4662 O4597 O.4531 O.2SO O.2747 O.2870 O.2993 O3116 O.3240 O.3364 O3489 O O3864 O.3990 O4116 O4242 O4368 O4494 O4621 O.4747 O4874 OSOOO O.S O.S O.S887 O.6O14 O.6140 O.6267 O-6394 O.6521 O.6647 O.6774 O O.7154 O.7281 O O.7514 O.7434 O O.7084 O.6997 O.6911 O.6826 O.6741 O O6488 O6404 O.6321 O.6238 O.61S6 O6074 O.S993 O.S911 O.S O.SS11 O.S O.S119 OSO42 O4966 O4890 O4814 O.4739 O4664 O de O4464 O4S17 40 de O de O4329 O de O4261 O de O4191 O de O4121 O416O 45 de O4OSO O4O91 46 de O.3979 O4O23 47 de O de O.3833 O de O de O de O.36O7 O de O3S30 O de O S4 de O3S13 55 de O.3293 O de O.3212 O de O.3130 O de O3O46 O de O.2962 O de O de O.2791 O de O.2703 O de O.2615 O3O46 64 de O.2526 O de O.2435 O de O.2344 O de O.2252 O de O O.28SS 69 de O.206S O de O de O.1874 O de O de O.1681 O de O de O.1486 O de O de O.1290 O de O O de O.1092 O.26SO 8O de O.O993 O de O.O894 O de O.O795 O de O.O696 O de O de O.0498 O de O.O4(OO O.266O 87 de O.O3O1 O de O.O2O2 O de O.O103 O de 4 O de -OOO95 O de -O.O.194 O de -O.O293 O de -O.O392 O de -O.0490 O de O de -OO678 O de -O.O de -O.O840 O de -O.O902 O.2416 It will also be appreciated that the airfoil 250 disclosed in the above Table 1 may be scaled up or down geometrically for use in other similar turbine designs. Consequently, the coor dinate values set forth in Table 1 may be scaled upwardly or downwardly such that the airfoil profile shape remains unchanged. A scaled version of the coordinates in Table 1 would be represented by X, Y and Z coordinate values of Table 1, with the X, Y and Z. non-dimensional coordinate values converted to inches, multiplied or divided by a con stant number. An important term in this disclosure is profile. The profile is the range of the variation between measured points on an

20 33 airfoil surface and the ideal position listed in Table 1. The actual profile on a manufactured blade will be different than those in Table 1 and the design is robust to this variation meaning that mechanical and aerodynamic function are not impaired. As noted above, a + or -5% profile tolerance is used herein. The X, Y and Z values are all non-dimensionalized relative to the airfoil height. The disclosed airfoil shape optimizes and is specific to the machine conditions and specifications. The airfoil shape pro vides a unique profile to achieve (1) interaction between other stages in the high pressure turbine; (2) aerodynamic effi ciency; and (3) normalized aerodynamic and mechanical blade loadings. The disclosed loci of points allow the gas turbine or any other suitable turbine to run in an efficient, safe and Smooth manner. As also noted, any scale of the disclosed airfoil may be adopted as long as (1) interaction between other stages in the high pressure turbine; (2) aerodynamic efficiency; and (3) normalized aerodynamic and mechanical bladeloadings are maintained in the scaled turbine. The airfoil 250 described herein thus improves overall gas turbine 100 efficiency. Specifically, the airfoil 250 provides the desired turbine efficiency lapse rate (ISO, hot, cold, part load, etc.). The airfoil 250 also meets all aeromechanics and stress requirements. It should be apparent that the foregoing relates only to certain embodiments of the present application and the result ant patent. Numerous changes and modifications may be made herein by one of ordinary skill in the art without depart ing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof. We claim: 1. A turbine nozzle comprising an airfoil shape, the airfoil shape having a nominal profile in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X,Y and Zare non-dimen sional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when con nected by Smooth continuing arcs, define airfoil profile sec tions at each distance Z, the airfoil profile sections at Z dis tances being joined Smoothly with one another to form a complete airfoil shape. 2. The turbine nozzle of claim 1, wherein the turbine nozzle comprises a stage nozzle of a turbine. 3. The turbine nozzle of claim 1, wherein the turbine nozzle forms part of a stage of a turbine. 4. The turbine nozzle of claim 1, wherein the airfoil shape lies in an envelope within +/-5% of a chord length in a direction normal to any airfoil Surface location. 5. The turbine nozzle of claim 1, wherein the height of the turbine nozzle is 5 inches to 50 inches (12 centimeters to 130 centimeters) in length. 6. The turbine nozzle of claim 1, wherein the X, Y and Z distances are scalable as a function of the same constant or number to provide a scaled-up or scaled-down airfoil. US 8,876,485 B A turbine nozzle comprising a nozzle airfoil having a Suction-side uncoated nominal airfoil profile in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z 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 airfoil profile sections at the Z distances being joined Smoothly with one another to form a complete Suction-side airfoil shape, the X, Y and Z distances being scalable as a function of the same constant or number to provide a scaled-up or scaled-down airfoil. 8. The turbine nozzle of claim 7, wherein the turbine nozzle comprises a stage nozzle of a turbine. 9. The turbine nozzle of claim 7, wherein the turbine nozzle forms part of a stage of a turbine. 10. The turbine nozzle of claim 7, wherein the airfoil shape lies in an envelope within +/-5% of a chord length in a direction normal to any airfoil Surface location. 11. The turbine nozzle of claim 7, wherein the height of the turbine nozzle is 5 inches to 50 inches (12 centimeters to 130 centimeters) in length. 12. A turbine comprising a plurality of nozzles, each of the nozzles comprising an airfoil having an airfoil shape, the airfoil having a nominal profile in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X,Y and Zare non-dimen sional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when con nected by Smooth continuing arcs, define airfoil profile sec tions at each Z distance, the airfoil profile sections at Z dis tances being joined Smoothly with one another to form a complete airfoil shape. 13. The turbine of claim 12, wherein the plurality of nozzles comprises a plurality of stage nozzles of the turbine. 14. The turbine of claim 12, wherein the plurality of nozzles forms part of a stage of a turbine. 15. The turbine of claim 12, wherein the airfoil shapelies in an envelope within +/-5% of a chord length in a direction normal to any airfoil Surface location. 16. The turbine of claim 12, wherein the height of the turbine nozzle is 5 inches to 50 inches (12 centimeters to 130 centimeters) in length. 17. The turbine of claim 12, wherein the X, Y and Z dis tances are scalable as a function of the same constant or number to provide a scaled-up or scaled-down airfoil. 18. The turbine of claim 12, wherein X represents a dis tance parallel to a turbine axis of rotation. k k k k k

21 UNITED STATES PATENT AND TRADEMARK OFFICE CERTIFICATE OF CORRECTION PATENT NO. : 8, B2 Page 1 of 1 APPLICATIONNO. : 13/ DATED : November 4, 2014 INVENTOR(S) : Gustafson et al. It is certified that error appears in the above-identified patent and that said Letters Patent is hereby corrected as shown below: In the Specification Column 3, Line 48, delete the X. Y and Z and insert -- the X, Y and Z --, therefor. Column 4, Line 33, delete Scales, at and insert -- Scales, at, --, therefor. Signed and Sealed this Twenty-sixth Day of May, % 4 Michelle K. Lee Director of the United States Patent and Trademark Office