MXPA98005245A - Turbine assembly with improved cooling and optimization of per - Google Patents

Abstract

The present invention relates to an aerodynamic plane for a turbine, having a profile not coated substantially in accordance with the Cartesian coordinate values of X, Y and Z stipulated in Table I, carried only to three decimal places, where Z is a distance from a platform on which the aerodynamic plane is mounted, and X and Y are coordinates that define the profile at each distance Z from the platform

Description

TURBINE ASSEMBLY WITH IMPROVED COOLING AND OPTIMIZATION OF THE PROFILE TECHNICAL FIELD The present invention relates to a turbine blade for a gas turbine phase, and relates particularly to a novel and improved profile for the turbine plane of a turbine, and to a greater cooling capacity for the blade of the turbine , particularly the aerodynamic plane, and from there, lower operating temperatures and extended life.

BACKGROUND In the design, manufacture and use of gas turbines, there has been a growing trend towards higher ignition temperatures, in order to optimize the operation of the turbine. Also, as the existing turbine aerodynamic planes reach the end of their life cycle, it is desirable to replace the aerodynamic planes, while simultaneously improving turbine performance through the redesign of the aerodynamic planes, and accommodating the largest ignition temperatures. Accordingly, a better cooling capacity at higher firing temperatures is highly desirable with the consequent extension of the life of the replacement aerodynamic planes.

For example, the life cycle of the aerodynamic planes for the first-produced units of the gas turbine MS6001B, manufactured by the transferee, is nearing an end. Accordingly, a new aerodynamic plane that can operate at higher firing temperatures and is compatible with existing gas turbines, but with better cooling and extended life, is considered desirable. A greater failure potential for an aerodynamic plane is a drag margin. With the aerodynamic plane time at the operating temperature, and at a given voltage level, the aerodynamic plane may tend to stretch and develop a crack or drag vacuum if it is not properly cooled. The formation of a crack or vacuum by drag reduces the surface area, which in turn increases the tension, and can cause the blade to break or crack. Accordingly, when redesigning an aerodynamic plane for an existing gas turbine, particularly for operating at higher firing temperatures, better cooling and the consequent reduction in the volume temperature of the aerodynamic plane are highly desirable to increase the drag margin. and the life of the aerodynamic plane. It is also desirable to redesign the aerodynamic plane without altering or changing any other part of the turbo machinery, and particularly without changing the union of the aerodynamic planes to the turbine wheel. That is, the redesign of the desired aerodynamic plane is limited by the original design limitations of existing turbo machinery, where the new aerodynamic plane can be used as a replacement part. Operation is also a significant consideration. For example, the separation of the boundary layer from, and the meeting to, the surface of the aerodynamic plane can be presented. Additionally, shock waves can be formed on the front edge of the aerodynamic plane. These and other factors contribute to an increase in the aerodynamic plane temperature, degrade performance and should be avoided.

DISCLOSURE OF THE INVENTION In accordance with the present invention, a novel and improved aerodynamic plane having a unique profile and other characteristics for improved operation and better cooling is provided to increase the range of drag and extend the life of the aerodynamic plane. In order to do this, an aerodynamic plane profile according to the present invention is provided, which improves turbine operation, by preventing the formation of shock waves on the front edge of the aerodynamic plane, as well as the boundary separation at length of the pressure and suction sides of the aerodynamic plane. Other characteristics of the aerodynamic plane profile include a thicker rear edge, comparing with previous aerodynamic planes, to meet the requirements of a better cooling. A thin, but cool, front edge is also provided. The oscillation angles are increased, and unique roll angles are provided. It is important that the union of each turbine blade, including its aerodynamic plane, its body and its duck tail, be the same as in the blades of the aforementioned turbine design. In addition, the improved profile and the orientation of the aerodynamic plane have a minimal effect on the remaining phases of the turbine. Additionally, weight reduction is achieved through the use of a shorter rope design. By using a Carpesian coordinate system, the profile of the aerodynamic plane is provided under environmental conditions. The cooling system for the aerodynamic plane of the present invention includes a plurality of linearly extending passages formed through the aerodynamic plane emptied from its root portion to its tip portion. Although the aerodynamic plane has a composite curve along its radial length, cooling passages extending linearly from the root to the tip are provided and configured close to the lateral pressure and suction surfaces of the airfoil. Particularly, two rows of cooling passages are formed substantially at half rope, with each row being closely adjacent to the pressure and suction sides of the airfoil. By locating the rows of passages closely adjacent to the lateral surfaces between the roll and lateral surfaces, better conduction and convection cooling is achieved. Moreover, the cooling passages extend substantially into the area of the rear edge, which has been thickened to accommodate the passages, to have a better cooling of the rear edge. In addition, to improve the cooling effect, most passages have turbulence. That is, these passages are periodically interrupted by turbulators, i.e., ribs projecting radially inward arranged in radial locations spaced along the passages, to alter the boundary layer of the cooling medium along the inner surface of the passage, and provide a turbulent flow. The turbulent flow improves the transfer of heat from the cast metal of the aerodynamic plane to the fluid medium, for example, air. Additionally, at the tip of the aerodynamic plane a recess is provided in communication with the outlet openings for the air passages of the aerodynamic plane. The recess has an opening adjacent to the rear edge, along the suction side of the aerodynamic plane. This avoids the back pressure in the cooling passages due to the proximity of the cover to the tip of the aerodynamic plane, and facilitates the flow of air outwards along the low pressure suction side of the airfoil, and inwards of the hot gas path. In a preferred embodiment according to the present invention, an aerodynamic plane for a turbine is provided, having a profile not coated substantially in accordance with the Cartesian coordinate values of X, Y and Z stipulated in Table I, carried only to three decimal places, where Z is a distance from a platform on which the aerodynamic plane is mounted, and X and Y are coordinates that define the profile at each distance Z from the platform. In a still further preferred embodiment in accordance with the present invention, there is provided an emptied turbine aerodynamic plane having a bank and a plurality of cooling passages extending from a root portion to a tip portion thereof, including first and second rows of the same on the opposite sides of the roll, and which are adjacent to the suction and pressure sides of the aerodynamic plane, respectively. In accordance with the foregoing, it is a primary object of the present invention to provide a novel and improved aerodynamic plane for a gas turbine, which has better performance, lower operating temperatures, a greater range of drag and an extended life, and whose Aerodynamic plane is useful as original equipment, as well as for a replacement aerodynamic plane on the existing turbo machinery.

BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 is a side elevational view of a turbine blade including an aerodynamic plane, a body and a duck tail, constructed in accordance with the present invention. Figure 2 is an axial view thereof. Figure 3 is a cross-sectional view of the airfoil, taken generally around line 3-3 of Figure 1. Figure 4 is a cross-sectional view of the aerofoil tip, taken generally around line 4. -4 of Figure 1. Figures 5A-5G are cross-sectional views of the airfoil, taken generally around lines 5A-5A, 5B-5B, 5C-5C, 5D-5D, 5E-5E, 5F-5F and 5G-5G of Figure 1. Figure 6 is a radial end view of the aerodynamic plane and the platform, as seen from the tip of the aerodynamic plane, looking radially inward.

Figure 7 is an enlarged fragmentary plan view of the tip of the aerodynamic plane, illustrating the recess and the opening through the suction side. Figure 8 is an enlarged fragmentary cross-sectional view of a cooling passage through an aerodynamic plane, illustrating a passage with turbulence. Figures 9A, 10A and HA are representative profiles of an aerodynamic plane, illustrating an oscillation angle, the throat, and the roll angle, respectively. Figures 9B, 10B and 11B are graphs based on diagrams of the graphs illustrating the angle of oscillation, the throat and the roll angle, respectively, for the spokes of the aerodynamic plane, as they are established from the centerline of the machine. Figure 12 is a diagram illustrating the Cartesian coordinate system for the aerodynamic plane profile given in Table I.

DETAILED DESCRIPTION OF THE DRAWINGS Referring now to the figures of the drawing, particularly Figures 1 and 2, there is illustrated a turbine blade TB, constructed in accordance with the present invention, and including an aerodynamic plane 10 mounted on a platform 12. , in turn carried by a body 14. The internal radial end of the body 14 carries a duck tail 16 for coupling the blade with a turbine wheel, not shown. As illustrated in Figures 1 to 4, the aerodynamic plane 10 has a composite curvature with the suction and pressure sides 18 and 20, respectively. As is well known, the duck tail 16 engages in the duck tail openings of the turbine wheel. The wheel space seals, i.e. the angel wings 22, are formed on the sides axially forward and backward of the body 14. The airfoils are completely emptied of directionally solidified GTD-111 alloy, which is a superalloy based in nickel known reinforced through heat treatments of hardening in solution and precipitation. Directional solidification provides the advantage of eliminating transverse grain boundaries, thus increasing drag life. To improve the cooling of the aerodynamic plane 10, a plurality of cooling medium passages, preferably air, 24 are provided through the aerodynamic plane 10 from its root portion 25 to its tip portion 26. The passages 24 they extend linearly through the compound curved aerodynamic plane, and continue through the platform 12 into a cavity 28 (Figure 5B) formed in the body 14. The cavity 28 is divided into a pair of front and rear cavities 28A and 28B (Figure 5E) with a structural rib 30 between the cavities 28A and 28B. The cavities 28A and 28B continue through the base of the body and into the corresponding cavities 32A and 32B in the duck tail 16, and which open through the lower part of the duck tail. Accordingly, it will be appreciated that a cooling medium, for example, air, can be provided to duck tail cavities 32A and 32B, and into the cavities 28A and 28B of the body, to be delivered to the passages 24 that extend through the aerodynamic plane 10. The wheel on which the aerodynamic plane, the body and the duck tail are mounted, has a single chamber that opens into the duck tail cavities 32A and 32B, when the duck tail is secured to the wheel. Accordingly, as the wheel rotates, a cooling medium is supplied from the single wheel chamber to the double cavities in the duck tail and the body, to flow radially outward through the passages 24, exiting at through the openings of the passages 24 in the tip portion 26 of the aerodynamic plane. Referring now to Figures 3 and 4, a unique configuration of the cooling passages is illustrated. In order to provide better cooling and, consequently, lower the volume temperature of the aerodynamic plane, the passages 24 are located as closely adjacent to the lateral surfaces of pressure and suction of the aerodynamic plane as possible, given the structural limitations and other limitations, such as the need to provide linearly extending passages 24. As a consequence, in the mid section of the aerofoil profile between the front edge LE and the rear edge T.E., two rows of cooling passages 24 are provided in the thicker portions of the aerofoil profile, with the rows remaining along the opposite side surfaces of the aerodynamic plane. For example, as illustrated in Figure 4, four cooling passages 24 are very closely adjacent to the suction side 18 of the airfoil, along the thickest portion of the airfoil, while three cooling passages 24 remain very close to the aerodynamic plane. closely adjacent to the pressure side 20 of the aerodynamic plane. For an aerodynamic plane of this configuration, the distance between the edges of the passages and the lateral surfaces is preferably approximately 2.54 millimeters. Accordingly, the surfaces of the aerodynamic plane 10 are cooled at the perimeter, in contrast to being cooled by the passages along a portion of the mean roll line of the cross section of the aerodynamic plane. Referring now to Figure 8, one of the cooling passages 24 is illustrated. Although the passages are linear, protuberances 40 are provided in the radially spaced positions along the passages to provide turbulent flow from the root to approximately 80 percent of the aerodynamic plane extension. Preferably, the projections comprise circular projections extending inward, spaced apart from each other along the length of the passages. Accordingly, the cooling medium, for example, air, is separated at the boundary of the passages by the rings that cause a turbulent flow and, consequently, a greater cooling for a given cooling air flow. The passage adjacent to the front edge L.E., and the two passages adjacent to the rear edge T.E, are of a smooth hole and without turbulence. However, the remaining passages have turbulence. Referring now to Figure 7, the portion of the tip 26 of the aerodynamic plane is recessed within the surrounding walls forming continuations of the sides of the aerodynamic plane, defining the recess of the tip. The base of the recess receives the open ends of the cooling passages 24. On the suction side and adjacent to the rear edge TE, a slot or opening 29 is provided, which forms an interruption of the surrounding suction side wall, making possible the exit of the cooling medium from inside the recess, into the hot gas flow stream. It will be appreciated that the portion of the tip 26 of the aerodynamic plane is in close proximity to a radially outer surrounding stationary casing., not shown. The slot 29 inward of the recess is located on the suction side, which is at a lower pressure and, therefore, more desirable than on the pressure side. Additionally, by forming an aperture, a backward pressure otherwise caused by the cover is prevented. As a result of the unique cooling configuration and the aerofoil profile as described further below, an average temperature of 50 percent of the air volume is obtained. The height of the aerodynamic plane is lower by approximately 65.5 ° C than the average temperature at the same height for the aerodynamic plane of the existing MS6001B gas turbine, for which the present blade is designed as a replacement. The average temperature for the existing MS6001B turbine is 867 ° C, while the present cooling system for the present design provides an average temperature of 801.5 ° C, with only a marginal increase in the cooling air flow of approximately 19.958 grams. of second mass / blade to approximately 22.68 grams of dough / second blade. Accordingly, the increase in the cooling passage number from a single row of 12 orifice substantially along the roll line as in the existing aerodynamic planes to 16 holes, and 3 holes remaining thereof, respectively, closely adjacent. to the suction and pressure surfaces, it provides a significant reduction in the temperature in volume, with a consequent substantial increase in the dragging margin and service life, with only a marginal increase in the cooling flow. Referring now to Figure 12, a Cartesian coordinate system is shown for the values of X, Y and Z stipulated in Table I below. The Cartesian coordinate system has the orthogonally related X, Y and Z axes, with the Z axis or the datum being substantially perpendicular to the platform 12, and generally extending in a radial direction through the aerodynamic plane. The Y axis is parallel to the center line of the machine, that is, the rotary axis. By defining the values of X and Y coordinates at selected locations in the radial direction, ie in a Z direction, the profile of the aerodynamic plane 10 can be asserted. By connecting the X and Y values with smooth continuous arcs , each profile section is fixed at each radial distance Z. The surface profiles at the different surface locations between the radial distances Z can be asserted by connecting the adjacent profiles. The X and Y coordinates to determine the section profile of the aerodynamic plane at each radial location or height of the aerodynamic plane Z, are tabulated in the following Table I, where Z is equal to 0 on the upper surface of platform 12. These tabular values are given in centimeters, represent real aerodynamic plane profiles under environmental, non-operative or non-hot conditions, and are for an uncoated aerodynamic plane, whose coatings are described below. Additionally, the sign convention assigns a positive value to the Z value, and positive and negative values for the X and Y coordinates, as typically used in a Cartesian coordinate system. The values in Table I are generated by computer, and up to five decimal places are shown. However, in view of the manufacturing limitations, the actual values useful for forming the aerodynamic plane are considered valid only up to three decimal places to determine the profile of the aerodynamic plane. In addition, there are typical manufacturing tolerances that must be taken into account in the aerodynamic plane profile. In accordance with the above, the values for the profile given in Table I are for a nominal aerodynamic plane. Therefore, it will be appreciated that more or less typical manufacturing tolerances are applicable to these X values, Y and Z, and that an aerodynamic plane having a profile substantially in accordance with these values, includes these tolerances. For example, a manufacturing tolerance of approximately + 0.254 millimeters is within the design limits for the aerodynamic plane, and a manufacturing tolerance of approximately + 0.2032 millimeters is preferably maintained. According to the foregoing, the values of X and Y carried to three decimal places, and having a manufacturing tolerance of about + 0.254 millimeters, and preferably of about + 0.2032 millimeters, are acceptable for defining the profile of the aerodynamic plane in each radial position through its entire length. As noted above, the aerodynamic plane can be coated to protect against corrosion and oxidation after the aerodynamic plane is manufactured in accordance with the values of Table I, and within the tolerances explained above. A coating against corrosion is provided, with an average thickness of 0.2032 millimeters. An over-coating against additional oxidation is provided with an average thickness of 0.0381 millimeters. With these coatings, there may be a coating material within the range of about 0.127 to 0.3048 millimeters above the aerodynamic planes at room temperature. Consequently, in addition to the manufacturing tolerances for the X and Y values stipulated in Table I, there is also an addition to these values, which counts for the coating thicknesses. The X, Y and Z coordinates given in Table I, together with the number of blades, that is, 92, provide the angles of oscillation, throat and roll angles in environmental conditions. The following discussion refers to these three parameters in the condition of hot continuous state. The orientation of the aerodynamic plane can be characterized by the angle of oscillation, the throat, and the roll angle. Referring now to Figure 9A, an oscillation angle is illustrated, which is the angle in relation to a line parallel to the rotary axis of the machine from the rear edge to the front edge. In the profile of the aerodynamic plane of the present invention, the angle of oscillation changes with the radial position of the profile along the aerodynamic plane. In Figure 9B a graph is given, given the angle of oscillation on the abscissa against the radius of the aerodynamic plane on the ordinate, the radius being in centimeters from the rotary axis of the turbine. For example, the first adjacent oscillation angle on the platform taken at 58,282 centimeters from the axis of rotation is located at almost the root of the aerodynamic plane adjacent to the platform, including a fillet between the platform and the root portion. In this place, the angle of oscillation is 13.5874 °. The additional oscillation angles are given in the diagram of Figure 9B for additional locations radially outward from the platform along the aerodynamic plane. It will be seen that the angle of oscillation increases from the root portion to the tip portion of the aerodynamic plane. In addition, the minimum distance between the adjacent aerodynamic planes is defined as the throat, and is schematically illustrated in Figure 10A. In the present invention, the throat is located along a line extending from the rear edge T.E. from an aerodynamic plane, to the intersection of the line with the closest portion of the suction side of the adjacent aerodynamic plane. The distances of the throat are variable, depending on the radial location, and consequently, the area of the throat varies along the lengths of the adjacent aerodynamic planes. In Figure 10B, a diagram and graph showing the distance of the throat in centimeters against the location of the throat along the radius in centimeters from the axis of rotation of the centerline is illustrated. Therefore, for example, at a location of 58,282 centimeters from the axis of rotation, and outward from the fillet at the junction of the aerodynamic plane and the platform, there is a throat distance of 1,523 centimeters. The other throat distances are given as a function of the radial distance from the axis of rotation. A unique roll angle? ß is provided for the aerodynamic plane herein. The roll is illustrated schematically by the dotted line of Figure HA, and is a line drawn in such a way that it extends through the centers of a series of circles touching the suction and pressure surfaces of the airfoil at the points of Tangency The roll angle is 180 ° less the sum of the angles a and b between the linear extensions of the roll line CL, both on the front and rear edge, and on lines 50 and 52 normal to the axis of the machine on those edges . The diagram illustrated in Figure 11B illustrates the roll angle for selected radial positions along the aerodynamic plane. For example, in a radial position of 52.282 centimeters from the axis of rotation that locates the profile at the root of the aerodynamic plane adjacent to the platform, and radially outward from the fillet, the roll angle? ß is 124 °, ie , 180 ° minus the sum of the angle a on the front edge, and the angle b on the rear edge. In "a preferred embodiment of the present invention, the aerodynamic plane is for the first phase of a gas turbine, and has 92 blades.The duck tail and the interconnection characteristics of the body are formed similarly to the aerodynamic plane of the first phase. above, and having an axial platform, Accordingly, the present invention is similar to the foregoing turbine in those aspects, and similarly provides an axial insertion of the ducktail into the wheel disk.

TABLE I -06986, 73232, 4.99300 -.11292, 74977, 4.99300 -.16510, 74590, 4.99300 -.21697, 73320, 4.99300 -.26777, 71563 4.99300 -.31745, 69477, 4.99300 -.36605, 67128, 4.99300. 41359, 65464, 4.99300 -.45971, 61774, 4.99300 -.50388, 58705, 4.99300 54564, -55325, 499300 58419, -51601, 499300 61859, -47507, 499300 64788, -43044, 499300 67100, - 38247, 4.99300 68699, -33177, 499300 69507, -27932, 4.99300 69456, - 22637, 4.99300 68517, -.17418, 4.99300 66741, -12420, 4.99300 64225, - 07730, 499300 61107, - 03390, 499300 57518, 00601, 4.99300 53578, 04265, 499300 49376, 07647, 499300 44982, .10788, 499300 40441, .13718, 499300 35787, 16474, 4.99300 31049, 19095, 499300 26246, .21608, 499300 21390, 24029, 499300 16490, 26367, 499300 11555, 28626, 499300 06590, .30815, 499300 01600, 32942, 499300 03415, 35021, 499300 08450, 37054, 4.99300 13500. .39044, 499300 18565, 40997, 4.99300 23643, 42917, 499300 28734, 44810, 499300 33834, .46677, 4.99300 38944, 48518, 4.99300 44061, .50337, 4.99300 49187, 52137, 4.99300 54319, .53917, 4.99300 59457, .55681, 4.99300 64600, .57432, 4.99300 69748, '".59168, 4.99300 40 .74900, .60895, 4.99300 80055 62612, 499300 85214, 64322, 499300 90373, 66027, 499300 95535, 67727, 499300 100695, 69429, 4.99300 105859, 71120. 499300 110976, 72688. 4.99300 115896, 72763, 499300 118500, 69131 , 4.99300 118500, 69131, 4.99300 118885, 65890, 499300 117591, 62949, 499300 114831, 60963, 499300 111538, 59389. 499300 108182, 57818. 499300 104826, 56258. 499300 101472, 54688, 499300 98120, 53118, 499300 94767, 51546, 499300 91417, 49969, 499300 88069, 48388, 499300 84722, 46805, 499300 81377, 45217, 499300 .78034, 43624, 499300 .74694, 42025, 499300 .71357, 40418, 499300 .68024, 38802, 499300 64695. 37176, 499300 61372, 35539. 499300 3055. 33889, 499300 .54744. 32226, 499300 .51440, 30545, 4.99300 .48145, 28847, 499300 44860, .27131. 499300 41586. 25393. 4.99300 .38324, 23631. 4.99300 .35074, 21842. 4.99300 .31840, 20024. 4.99300 .28623, .18175. 4.99300 40 .25425, .16292. 499300 22249, 14372. 499300 19096, 12411, 499300 15970, 10402. 499300 12877, 08342, 499300 09821, 06225, 4.99300 06807, 04045, 4.99300 03842, 01792, 499300 00936, -00541, 4.99300 01897, -02971, 4.99300 04638 ,. -05515, 4.99300 07260, -08191, 499300 09725, -11026, 4.99300 11972, - 14056, 4.99300 13931, -17294, 4.99300 15527, - 20734, 499300 16696, - 24348, 499300 17391, -28084, 499300 17604, -31876, 499300 17412, -35651, 4.99300 16899, - 39383, 4.99300 16071, - 43058, 4.99300 .14961, -.46651, 4.99300 .13612, -50152, 4.99300 .12077, - 53562, 4.99300 .10428, - 56899, 4.99300 .08753. -60196, 4.99300 .07198. -63501, 499300 .06033, - 66875, 4.99300 .05774, -.70251, 4.99300 .06986. - 73232, 4.99300 .02155, -.75817, 4.49400 .06458, - 77830, 4.49400 .11760, - 77634, 4.49400 .17058, - 76477. 4.49400 .22253, - 74790. 4.49400 .27335, - 72750. 4.49400 .32305, -.70430. 4.49400 .37164, - 67875. 4.49400 .41894, - - 65096. 4.49400 40 .46463, - 62074, 4.49400 50818 - 58767 449400 54900 -55140, 449400 58633, -51170, 449400 61934, - 46845, 449400 64702, -42176, 449400 66842, -37199, 449400 68264, -31982, 449400 68887, - 26620, 449400 68659, -21223, 449400 67589 - 15929, 449400 65736, - 10844 449400 63203 - 06048, 449400 60102, -01574, 449400 56553 02572, 449400 52654, 06411, 449400 48487, 09970, 449400 44112, 13278, 449400 39575, 16371, 449400 34914, 19287, 449400 30158 22059, 449400 25326, 24711, 449400 20433, 27256, 449400 15491, 29705, 449400 10510. 32068 449400 05496, 34360, 449400 00451, 36596, 449400 04618. 38779, 449400 09706, 40911, 449400 14813, 43000, 449400 19936. 45051, 449400 25074, 47070, 449400 .30225, 49058, 449400 .35386, 51015, 449400 40558, 52946. 449400 45740. 54854, 449400 50930. 56739, 449400 56127. 58605, 449400 61331, 60455. 449400 66540, 62289. 449400 40 .71754, 64109, 449400 76973, 65919 449400 82195, 67718, 449400 .87420, 69511, 449400 .92648, 71295, 4.49400 .97877, 73077, 4.49400 103102, 74848. 449400 108305, 76612, 4.49400 1.13161, 76672, 449400 1.16606 , 73288, 449400 116606, 73288, 449400 1.17007, 70022, 4.49400 1.15668, 67046, 449400 1.12824, 65050, 449400 109475, 63425, 449400 1.06075, 61807, 449400 102671, 60203, 449400 .99267. 58595, 449400 95862, 56990, 449400 .92456, 55386 449400 .89051, 53780, 449400 .85646, 52172. 449400 .82243, 50559. 449400 .78842, 48941, 449400 .75445, 47316. 449400 .72050, 45684, 449400 .68660, 44042, 449400 .65274, 42389, 449400 .61895, 40722, 449400 .58523, 39040, 449400 .55158. 37342, 449400 .51803, 35624. 4.49400 .48458, 33884. 4.49400 .45125, 32121. 4.49400 .41805, 30331, 4.49400 .38500, .28513, 4.49400 .35213, 26662, 4.49400 .31945, .24773. 4.49400 .28699. .22844. 449400 .25479; 20870, 4.49400 40 .22287. .18848, 4.49400 19129, 16775, 449400 16008, 14640, 449400 12932, 12437, 449400 09907, 10159, 449400 06944, 07799, 449400 04053, 05343, 449400 01250, 02782, 449400 01448, 00102, 4.49400 04017, - 02709, 4.49400 06427, - 05666, 449400 08642, -08781, 449400 10619, -12063, 449400 12303, -15515, 449400 13641, -19122, 4.49400 14585, -22855, 449400 15108, - 26672, 449400 15205, -30521, 449400 14904, - 34352, 449400 14274, -38128, 449400 13378, -41841, 449400 12227, - 45482, 449400 10850, - 49036, 449400 09287, - 52504, 449400 07586, -55893, 4.49400 05809, - 59225, 449400 04042, -62535, 449400 02426. -65873, 449400 01229. -69297, 449400, 00957, - 72740, 449400 .02155. -75817, 449400 .02477. - 78493, 399400 .01835. -80761. 3.99400 .07238, - 80739, 3.99400 .12664, -.79681, 3.99400 .17991, - 78054, 3.99400 23206, -.76050, 3.99400 .28306, -73751, 3.99400 .33287, -71195. 3.99400 .38150, -68413. 3.99400 40 .42874, -65414, 3.99400 47410, -62154 399400 51710, - 58597, 399400 55716, - 54724, 399400 59353, -50515, 399400 62532, - 45964, 399400 65159, -41086, 399400 67140, - 35922, 399400 68389 , - 30543, 399400 68839, - 25039, 399400 68465, -19532, 399400 67284, -14135, 399400 65360, - 08952, 399400 62785, - 04042. 399400 59665, 00557, 399400 56104, 04844, 399400 52196, 08827, 399400 48011, 12531, 399400 43609, 15985, 399400 39039, 19224, 399400 34337, 22285, 399400 29532, 25198, 399400 24645, 27979, 399400 19692, 30641, 399400 14686, 33200, 399400 09635, 35673, 399400 04547, 38080. 399400 00569, 40426, 399400 05712. 42712, 399400 10877. 44946, 399400 16062. 47137, 399400 .21266. 49290. 399400 26484. 51407, 399400 31716, 53488. 399400 .36962, 55539, 399400 42218, 57562, 399400 47485, 59560, 399400 52761, 61535. 3.99400 58044, 63491, 399400 63334, 65428, 399400 40 68630. 67350, 399400 73932, 69259, 399400 79238, 71156, 3.99400 .84548, 73043, 3.99400 .89860, 74921, 3.99400 95177, .76793, 3.99400 1.00488, 78654, 3.99400 105785, 80533, 3.99400 1.10820, 80637, 3.99400 1.14417 , 77390, 3.99400 1.14417, 77390, 3.99400 114840, 74076, 3.99400 113451, 71056, 3.99400 110518, 69043, 399400 1.07106, 67358, 3.99400 103656, 65684, 3.99400 100199, 64023, 3.99400 .96742, .62362, 399400 .93283, 60705, 399400 89821, 59051, 399400 86360, 57395, 3.99400 .82900, 55736, 399400 v .79442, .54071, 3.99400 .75987, 52398, 3.99400 .72536, 50716, 3.99400 .69090, 49024, 3.99400 .65650, .47321, 3.99400 .62216, 45602, 3.99400 .58790, 43865, 3.99400 .55373, 42110, 3.99400 .51967, .40333, 3.99400 .48573, .38532, 3.99400 .45193, .36702, 3.99400 .41828, 34842, 3.99400 .38482, 32949, 3.99400 .35155, .31019, 3.99400 .31852, .29049, 3.99400 .28574, .27030, 3.99400 .25328, .24960, 3.99400 .22113, .22833, 3.99400 40 .18945, 20645, 3.99400 15818, .18391, 3.99400 12745, .16060, 3.99400 09736, .13641, 3.99400 06801, .11128, 3.99400 03954, .08509, 3.99400 01214, .05772, 3.99400 01396, .02903, 3.99400 03851 , -.00108, 3.99400 06116, -.03271, 3.99400 08153, -.06595, 3.99400 09916, -.10081, 3.99400 11358, -.13718, 3.99400 12441, -.17481, 3.99400 13140, -.21336, 3.99400 13441, -.25241, 3.99400 13357, -.29154, 3.99400 12916, -.33036, 3.99400 12165, -.36861, 3.99400 11158, -.40615, 3.99400 09934, -.44299, 3.99400 08505, -.47906, 3.99400 06897, -51431, 3.99400 05146, -.54878, 3.99400 03294, -.58260, 3.99400 01398, -.61600, 3.99400 00461, -.64935, 3.99400 02141, -.68315, 3.99400 03376, -.71797, 3.99400 03662, -.75314, 3.99400 .02477, -.78493, 3.99400 .06935. -.81311, 3.49500 .02601, -.83799, 3.49500 .02911. -.83926, 3.49500 .08471. -.82955, 3.49500 .13938, -.81383, 3.49500 .19294, -.79415, 3.49500 .24533, -.77137, 3.49500 .29650, -.74586. 3.49500 .34650, -.71799. 3.49500 40 39528, -.68808, 3.49500 44240 -65578 349500 48749 -62078 349500 53005, -58286, -54178 56946 349500, 349500 60491, -49737, 349500 63553, -44962, 66039 349500, - 39875, 349500 67860, - 34523, 349500 68939, - 28974, 349500 69223, -23334, 349500 68698, -17711, 349500 67391 -12217, 349500 65370 - 06932, 349500 62726. -01916, 349500 59558, 02803, 349500 55963 07216, 349500 52021, 11334, 349500 47800 15178, 3.49500 43360, 18777, 349500 38746, 22167, 349500 33996, 25379, 349500 29137, 28430 349500 24187, 31335, 349500 .19165, 34113, 349500 .14083. 36787, 349500 .08955, 39381, 349500 03789, 41901, 349500 .01409, 44350, 349500 .06637, 46738, 349500 .11889, 49075, 349500 .17163, 51367, 3.49500 .22456, 53618, 3.49500 .27765, 55827, 3.49500 .33090, 58001, 3.49500 .38429, 60145, 349500 .43779, 62259, 3.49500 .49140, 64347, 3.49500 .54510, 66414. 3.49500 .59888. .68459. 3.49500 40 .65273. 70487, 3.49500 70665, 72500, 349500 76062, 74498 349500 81463, 76485, 349500 86869, 78461, 349500 92279, 80429, 349500 97689, 82387, 349500 1.03093, 84350, 349500 108236, 84679, 3.49500 1.11902, 81356, 3.49500 1.11902, 81356, 349500 112350, 77994, 3.49500 1.10929, 74927, 349500 107932, 72885, 349500 1.04473, 71135, 349500 1.00986, 69394, 3.49500 .97494, 67663, 349500 .94002, 65929, 3.49500 90509, 64197, 349500 .87016, 62465, 349500 .83523, 60730, 349500 .80033, .58988, 349500 .76547, 57237, 349500 .73067, 55475, 349500 .69592, 53699, 349500 .66124. 51910, 349500 .62664, .50105, 3.49500 .59213, 48281, 3.49500 .55773, 46435. 3.49500 .52345, 44564. 3.49500 .48931, 42668, 3.49500 .45533. .40742, 3.49500 .42153, .38782. 349500 .38793, .36786. 3.49500 .35457, .34749. 3.49500 .32146, .32670, 3.49500 .28864, .30542. 3.49500 .25617, .28357, 3.49500 .22410, .26111, 3.49500 .19249, .23799, 3.49500 40 .16139. 0.21416, 3.49500 13088, 18954, 349500 10107, 16403, 349500 07210, 13750, 349500 04413, 10987, 349500 01732, 08105, 00807 3.49500 05089, 349500 03175, 01930, 349500 05341, -01379, 349500 07264, -04841, 3.49500 08904, - 08454, 349500 .10212, -12207, 349500 11152. -16072, 349500 11706, -20011, 349500 .11872, -23983, 349500 11663, - 27950, 349500 11115, -31878, 349500 10272, - 35745, 349500 09186, - 39540, 349500 07894, - 43262, 349500 06423, -46914, 349500 04784, - 50492, 349500 03000, - 53993, 349500 01102, - 57425, 349500 .00871, - 60803, 349500 .02867, -64152, 349500 .04804, - 67508, 349500 .06542, - 70924, 349500 .07808, - 74456, 349500 .08105, - 78038, 349500 .06935. -81311, 3.49500 .11359. - 84266. 2.99600 .06992, - 86942. 2.99600 .01363, -87191, 2.99600 .04337. - 86295, 2.99600 .09949, - 84773, 2.99600 .15454, -82841, 2.99600 .20842, - 80590, 2.99600 26105, -78051, 2.99600 31249. - 75262, 2.99600 40 .36277. -.72266, 2.99600 41166 -69058 299600 45881 - 299600 65609 50378, -61891, 54603 299600, - 57877, 299600 58489, - 53544, 299600 61955, - 48880, 299600 64912, -43891, 299600 67270, -38601, 299600 68941, - 33060, 299600 69851, -27351, 299600 69962, -21573, 299600 69275, - 15837, 299600 67835, - 10236, 299600 65711, - 04847, 299600 62994, 00281, 299600 59773, 05118, 299600 56132, 09661, 299600 52147 13918, 299600 47886, 17907, 299600 .0 43403, 21660, 299600 38745, 25206, 299600 33940, 28559, 299600 29014, 31734, 299600 23988, 34755, 299600 18885, 37649, 299600 13721, 40445, 299600 08508, 43151, 299600 03253, 45771, 299600 .02039, 48320, 299600 .07361. 50810, 299600 .12709, 53247, 2.99600 .18079, S5G35, 2.99600 .23470, 57977, 2.99600 28880, 60280. 2.99600 .34304, 62548, 2.99600 39743, 64783. 2.99600 .45194, 66989. 299600 .50656, 69171, 2.99600 .56127 '71328, 2.99600 40 .61607, 73466, 2.99600 67093 75587, 299600 72586, 77691, 299600 78084, 79783, 299600 83587, 81863, 299600 89095, 83933, 299600 94605 85994, 2.99600 100115, 88050, 299600 105362, 88554, 2.99600 109146, 85197, 2.99600 109146, 85197, 299600 109626 81792, 2.99600 108202, 78677, 299600 105172, 76591, 299600 101688, 74769, 299600 98186, 72950, 299600 94682, 71132, 299600 91181, 69306, 299600 87684, 67475, 299600 84189, 65639, 299600 80697, 63793, 299600 77212, 61936, 299600 .73733, 60066, 299600 .70261, 58181, 299600 66799, 56278, 299600 63346, 54356, 299600 59905, 52414, 299600 56476, 50449, 299600 53061, 48457, 299600 .49663, 46436, 2.99600 .46282, 44385, 2.99600 42921, 42300, 2.99600 .39583, 40175. 2.99600 36272, 38008. 2.99600 .32989, 35797, 299600 .29738, 33537. 299600 26523, 31222, 2.99600 .23352, 28845. 2.99600 .20231., 26400. 2.99600 .17166", 23881. 2.99600 40 .14165, 21284, 2.99600 11237. 18602. 2.99600 08397, 15820, 2.99600 .05662, .12929, 2.99600, 03051, 09921, 2.99600 .00584, 06786, 2.99600 .01708, 03513, 2.99600 .03793, 00099, 2.99600 .05636 , - 03458, 2.99600 .07199, -07154, 2.99600 .08443, -10974, 2.99600 .09332, -14897, 2.99600 .09842, - 18888, 2.99600 .09974, - 22907, 2.99600 .09743, -26918, 2.99600 .09174, - 30890, 2.99600 .08309, - 34802. 2.99600 .07195, - 38640, 2.99600 .05877, - 42404, 2.99600 .04387, - 46097, 2.99600 .02743, -49722, 2.99600 .00954, - 53275, 2.99600 .00959, - 56757, 2.99600 .02967, -60178, 2.99600 .05036, -63551, 2.99600 .07112, - 66902, 2.99600 .09116, -70271, 2.99600 .10904, -73710, 2.99600 .12200, - 77279, 2.99600 .12506, -80911, 2.99600 .11359, -.84266, 2.99600 .15647, -.87304, 2.49700 .11239, -.90134, 2.49700 .05498, -.90491, 2.49700 -.00335, - 89672, 2.49700 -. 35 -.06088, -.88209, 2.49700 -.11738, -.86326, 2.49700 -.17274, -.84115, 2.49700 -.22683. -81605, 2.49700 -.2796 ?, -.78828, 2.49700 40 -. 40 -.33130, -.75822, 2.49700 38173, -72618, 249700 .43060, -69195, 249700 .47748, -65515, 2.49700 .52192, -61551, 2.49700 .56331, -57281, 249700 .60097, -52687, 2.49700 .63406, - 47766, 2.49700 .66172, -42530, 2.49700 .68309, -37011, 2.49700 .69739, -31276, 2.49700 .70414, - 25406, 2.49700 .70319, -.19501, 2.49700 .69475, -13652, 2.49700 .67930, - 07944, 2.49700 .65747, - 02440, 2.49700 .63000, 02813, 2.49700 .59764, .07791, 2.49700 .56113, .12482, 2.49700 .52117, 16890, 2.49700 .47837, 21039, 2.49700 .43331, .24953, 2.49700 .38633, .28638, 2.49700 .33770, 32109, 2.49700 .28773. 35394, 2.49700 .23672. 38525, 2.49700 .18491. 41531, 2.49700 .13247, .44427, 2.49700 .07947. 47222, 2.49700 .02602, 49934, 2.49700 .02781, .52575, 2.49700 .08194. .55156. 2.49700 .13635. .57681. 2.49700 .19100, .60153, 2.49700 .24587, .62580, 2.49700 .30091, .64969, 2.49700 .35612, .67320, 2.49700 .41148. .69638. 2.49700 .46695, .71929. 2.49700 .52254", .74193, 2.49700 40.57823. .76434, 2.49700 63399, 78656, 249700 68984, 80860, 249700 .74574, 83050, 249700 80169, 85226, 249700 85770, 87392, 249700 .91374, 89546, 249700 96978, 91693, 2.49700 102348, 92334, 2.49700 106263, 88977, 2.49700 106263, 88977, 249700 106773, 85538, 249700 105355, 82380, 249700 102307, 80250, 2.49700 98809, 78362, 2.49700 95302, 76469, 2.49700 91797, 74568, 2.49700 88300, 72651, 249700 .84811, 70722, 249700 81329, 68780, 249700 77855, 66822, 249700 74390, 64847, 249700 .70935, 62853, 249700 .67492, 60839, 2.49700 64061, 58802, 249700 .60645, 56741, 2.49700 .57244, 54653, 2.49700 .53860, .52536, 249700 .50496, 50387, 2.49700 .47153, 48203, 2.49700 .43834, 45983, 2.49700 .40541, 43722, 2.49700 .37278. .41416, 2.49700 .34048. 39061, 2.49700 .30855, 36656, 2.49700 .27704. 34194, 2.49700 .24600. .31669, 2.49700 .21551. .29075, 2.49700 .18565, .26405, 2.49700 .15651, 23654. 2.49700 40 .12818. .20818, 2.49700, 10076, 17889, 2.49700 .07443, 14856, 2.49700 .04940, 11709, 2.49700 .02587, .08444, 2.49700 .00406, .05055, 2.49700 .01571, 01537, 2.49700 .03314, -02107, 2.49700. 04791, -.05872, 2.49700 .05972, -.09746, 2.49700 .06826, - 13708, 2.49700 .07334, -17731, 2.49700 07488, -21782. 2.49700 .07301, -25828, 2.49700 .06794, -.29844, 2.49700 .05996, -.33806, 2.49700 .04946, - 37702, 2.49700 .03683, -41527, 2.49700 .02242, - 45280, 2.49700 .00645, - 48966, 2.49700 .01094, - 52585, 2.49700 .02968, -56135, 2.49700 .04956, -59616, 2.49700 .07033, - 63037. 2.49700 .09165, -66413, 2.49700 .11300, -.69771, 2.49700 .13355. -.73151, 2.49700 .15180. -.76608, 2.49700 .16488. - 80206, 2.49700 .16782. - 83878, 2.49700 .15647, -.87304, 2.49700 .19499, - 90397, 1.99700 .15047, - 93353. 1.99700 .09208, -.93832, 1.99700 .03256, -93120, 1.99700 .02626, -.91750, 1.99700 08411, -.89949, 1.99700 .14086, -.87809, 1.99700 .19636. -.85360, 1.99700 .25047- -82617, 1.99700 40 .30319, -.79599. 1.99700 35470, -76368, 199700 40463, -72918, 199700 45256, -69203, 199700 49806, -65202, 199700 54057, -60894, 199700 .57949, -56265, 199700 61412, -51314, 199700 64376, -46056, 199700 66771, -40520, 1.99700 68544, - 34758, 199700 69657, -28832, 1.99700 70087, -22820, 199700 69838, - 16799, 199700 68923, -10844, 1.99700 67373, -05021. 199700 65226, 00615. 1.99700 62529, 06014, 199700 59340, 11144. 199700 55721, 15985, 199700 .51742, 20550, 199700 47470, 24854, 199700 42947, 28895, 199700 .38207, 32686, 199700 33288, 36255, 1.99700 28229, 39636, 199700 23064, 42861, 1.99700 .17814, 45950, 199700 .12493, 48919, 199700 .07114, 51788, 199700 .01690, 54576, 1.99700 .03771, 57293, 1.99700 .09265, .59946, 1.99700 .14789, .62537, 1.99700 .20338, 65077. 199700 .25908, 67574. 199700 .31497, 70027. 1.99700 .37103. 72444, 1.99700 .42723. .74829. 1.99700 .48357. 77184. 1.99700 40 .54002, 79513, 199700 59656, 81820. 199700 65319, 84106 199700 .70989, 86377, 199700 .76665, 88632, 1.99700 .82347, 90875, 1.99700 .88033, 93105, 1.99700 .93723, 95322, 1.99700 .99186, 96094 , 1.99700 103209, 92728, 1.99700 1.03209, 92728, 1.99700 1.03741, 89264, 1.99700 102322, 86075, 199700 .99255. 83915, 199700 .95745, 81977, 199700 .92234, 80027, 1.99700 .88729, 78061, 1.99700 .85238, 76071, 199700 .81758, 74063, 1.99700 .78289, 72034 1.99700 .74833, 69982, 1.99700 .71391, 67906, 1.99700 .67965, 65804, 199700 .64555, 63674, 199700 .61164, 61513, 1.99700 .57793, 59320, 1.99700 54444 57093. 1.99700 .51119, .54828, 1.99700 .47821, 52522, 1.99700 .44553, .50173, 1.99700 .41317, 47779, 199700 .38117, .45335, 1.99700 .34958, .42836, 1.99700 .31845, .40279, 1.99700 .28781, .37660, 1.99700 .25772. .34976. 1.99700 .22827, .32219, 1.99700 .19956, .29381, 1.99700 .17168, .26459, 1.99700 .14475", .23448, 1.99700 40 .11885, .20344, 1.99700 09411 17142, 199700 07075, 13834 199700 04897, 10415, 199700 02897, 06885, 199700 01096, 03245, 199700 00481, -00502, 199700 01811, - 04346 199700 02873, - 08275, 199700 03651, -12273, 199700 04131, -16320, 199700 04308, -20391, 199700 04187, -24461, 199700 03785, -28510, 199700 03122, - 32522, 199700 02226 - 36483, 199700 01124, -40386, 199700 00157, - 44229, 199700 01596, -48011, 199700 03186, -51731, 199700 04923, - 55385, 199700 06797, - 58968, 199700 08790, - 62482, 199700 10880, -65931, 199700 13033. - 69332, 199700 15194. - 72709, 199700 .17277. -76106, 199700 .19118, - 79583, 199700 .20409, - 83209, 199700 .20650, -86914, 199700 , 19499, -90397, 199700 23392, - 93805, -149800 18854, -96810, 149800 12918, - 97330, 149800 06864, - 96655, 149800 00876, -95318, 149800 05016, -93540, 149800 10801, -91418, 149800 16462, -88984, 149800 21971 *; - 86235. 149800 40 27324, -83174. 1.49800 32550. -79883, 149800 37616, - 76370, 1.49800 42479, -.72588, 1.49800 47101, -.68522, 1.49800 51431, -64155, 1.49800 55418, -59477, 1.49800 .62193, .13478, .99900 59082,. 18878, .99900, 55552, .24016, .99900 .51 * 42, .28870, .99900 .38061, 41762, .99900 .33085, .45564, .99900 .27948, .49145, .99900 .22671, 52526, .99900 .17279, .55735, .99900 .11802, .58804, .99900 .06259, .61759, .99900 .00663, .64615, .99900 .04981, 67380, .99900 .10662, .70077, .99900 .16368, .72721, .99900 .22100, .75309, .99900 .27854, .77851, .99900 .33625, .80358, .99900 .39411, .82830, .99900 .45210, .85273, .99900 .51019, .87696, .99900 .56836, .90100, .99900 .62659, .92493, .99900 .68485, .94875, .99900 .74316, .97251, .99900 .80151, .99621, .99900 .85989, 1.01977, .99900 .91613, 1.03012, .99900 .95854, .99659, .99900 .95854, .99659, .99900 .96444-, .96190, .99900 40 .95077, .92966, .99900 92036 90744 99900 88555, 88712, 99900 85090, 86647 99900 81645, 84544, 99900 78227, 82397, 99900 74836, 80209, 99900 71472, 77979, 99900 68137, 75704, 99900 64834, 73382, 99900 61565, 71011, 99900 58333, 68588, 99900 55143, 66110, 99900 51995, 63576, 99900 48895, 60983, 99900 45846, 58329, 99900 42854, 55609, 99900 39924, 52821, 99900 37058, 49965, 99900 34265, 47036, 99900 31552, 44032, 99900 28925, 40949, 99900 26392, 37788, 99900 .23960, 34546, 99900 .21639. 31221, 99900 .19440. 27813, 99900 .17373, 24322, 99900 .15446, 20751, 99900 .13668, 17101, 99900 12047, 13377, 99900 10597, 09579, 99900 .09331, 05717, 99900 .08255, 01795, 99900 07377. -02176, 99900 06703. -06187, 99900 06234. - 10228, 99900 05970. - 14286, 99900 05907, -18353, 99900 06037, -22416, .99900 .06352, - 26469, .99900 40 06842. -30501, .99900 07494, - 34509, 99900 08292, - 38487, 99900 09222, - 42433, .99900 10271, -46347, .99900 11428, - 50228, .99900 12692, - 54075, .99900 14082, - 57883, .99900 15613, -61640, .99900 17275, -65338, .99900 19058, - 68976, .99900 20946, - 72556, .99900 22904, - 76087, .99900 24876, - 79593, 99900 26760, -83114, .99900 28354, - 86708, .99900 29297, - 90427, .99900 29136, -94163, 99900 27765, - 97660, .99900 32153, -101928, 49900 27283, -104652, 49900 21173, -104796, .49900 15021, -103760, .49900 08969. -102079. 49900 03031. - 99975. .49900 02791, - 97547, 49900 08490, -.94838, 49900 14042, -91850, .49900 19440, - 88578, .49900, 24711, -.85090, .49900 .29842, -.81408, .49900 .34808, -.77511. 49900 .39586. -.73389. .49900 .44143, - 69029, .49900 .48441. -.64417. .49900 .52440. -.59541. 49900 .56093. -.54405, .49900 .59355, -49019, .49900 .62184, -.43396, .49900 .64543, -37560. .49900 40 .66397. -.31549, .49900 67725, -25405 49900 68511, - 19170, 49900 68748, -12893, .49900 68433, - 06622, .49900 67562, - 00402, .49900 66136, 05715, 49900 64160, 11677, 49900 61670, 17446, .49900 58713, 22983, .49900 55311, 28256, .49900 51493, 33247, 49900 47311, 37950, 49900 42818. 42366, 49900 38065, 46502, .49900 33088, 50369, .49900 27918, 53989, 49900 22594, 57396, 49900 17154, 60626, 49900 11630, 63716 49900 06040, 66686. 49900 00388, 69548, 49900 05308, 72331, .49900 11033, 75054, 49900 16787, 77713, 49900 22568, 80322, 49900 28367, 82893, 49900 34182, 85425, .49900, 40013. 87926. .49900 .45853. 90407, 49900 .51702, 92868. .49900 .57557, 95320, .49900 .63415, 97763, 49900 .69276, 100201, .49900 .75140, 102636, .49900 .81008, 105059, .49900 .86668, 106199, .49900 .90992, 102877, .49900 .90992, 1.02877, .49900 .91619-, 99413, .49900 40 .90285, .96993, .49900 87265, 93916, 49900 83810, 91828, 49900 80382, 89692, .49900 .76985, 87502, 49900 .73628, .85253, .49900 .70310, 82946, .49900 .67032, 80582 , .49900 .63797, 78156, .49900 .60611, .75666, .49900 .57476, .73111, .49900 .54396, 70488, .49900 .51378, 67794, .49900 .48424, .65028, 49900 .45539, .62188, .49900 .42729, 59272, .49900 .40002, 56278, .49900 .37363, 53204, .49900 .34816, 50052, .49900 .32369, 46820, 49900 .30031, 43507, .49900 .27810, 40114, .49900 .25712, .36642, .49900 .23744, .33093, .49900 .21913, 29470, .49900 .20229, 25777, .49900 .18697, .22017, .49900 .17322, .18197, .49900 .16110, 14321, .49900 .15062, .10395, .49900 .14183, .06428, .49900 .13478, .02427, .49900 .12943, -01599, .49900 .12578, - 05643, .49900 .12377, - 09699, .49900 .12338, -13759, .49900 .12451, -17815, .49900 .12709, -.21864, .49900 .13102, -25901, .49900 .13624, -.29923, .49900 40 .14267. - 33926. .49900 15021 - 37908 49900 15876, -41866, 49900 16820, -45802, .49900 17842, -49716, 49900 18933, - 53608, 49900 20093, -57481, 49900 21342, -61333, .49900 22704, - 65149, .49900 24176, - 68923, .49900 25750, - 72653, 49900 27413, - 76340, 49900 29133, - 79992, 49900 30857, - 83624, 49900 32474, -87271, 49900 33751, - 90976, 49900 34304, - 94760, 49900 33754, - 98483, 49900 32153, -101928, 49900 37276, -106251, 00000 32239, -108287, 00000 26254, -107770, 00000 20337, -106192, 00000 14561, -104044, .00000 08918, -101526, 00000 03400, -98728, .00000 01995, -95694, 00000 07254, -92432, 00000 12367, - 88942, .00000 17346, - 85256. 00000 22193. -81397. 00000 26897. - 77368. .00000 31437. -73159. .00000 35783, - 68756, .00000 39908, -64145, .00000 43779, -59315, .00000 47360, -54270, .00000 50613, -49014. .00000 53509, -43555, .00000 56022 '- 37909, .00000 40 58127, -32103. .00000 59812 -26163 00000 61067, -20119 - 00000 61884, - 14003 - 00000 62260, - 07844, 00000 62188, -01674, 00000 61650, 04469, 00000 60612, 10550, 00000 59066, 16516, 00000 57012, 22304,. 00000 54431, 27867, - 00000 51325, 33169, 00000 47749, 38176, 00000 43758, 42860, 00000 39403, 47209, 00000 34748, 51261, 00000 29867, 55067, 00000 24818, 58662, 00000 19646, 62085, 00000 14386, 65377, 00000 09056, 68553, 00000 03658, 71618, 00000 01795, 74596, 00000 07285, 77503, 00000 12814, 80338, 00000 18376, 83111, 00000, 23964, 85834, 00000, 29576, 88507, 00000 35210, 91138, 00000 .40860, 93733, - 00000 .46527, 96296, .00000 .52205, 98833, - 00000 .57895, 101344, .00000 .63596, 103834, - 00000 .69305. 106303, 00000 .75025, 108745, .00000 .80556, 109824, 00000 .84807, 106574, 00000 .84807, 106574, .00000 85462, 103081, -.00000 40 .84110, 99807, -.00000 81055 97515 00000 .77585, 95347 00000 .74167, 93111, 00000 .70797, 90799, 00000 67482, 88406, .00000 64226, 85936, .00000 61031. 83385, .00000 57903, 80750 , 00000 54848, 78029, 00000 .51872, 75221, 00000 48981, 72323 00000 .46181, 69337, 00000 .43479, 66260, 00000 40881, 63095, 00000 38390, 59842, 00000 36016, 56504, 00000 33764, 53082, 00000 .31638, 49579, 00000 .29642, 45999, 00000 .27782, 42346, 00000 26063, 38625, 00000 .24489, 34840, 00000 .23063, 30997, - 00000 .21788, 27100, 00000 .20666, 23156, 00000 .19701, 19172, - 00000 .18894, .15153. 00000 .18246, .11105, 00000 .17757, .07033, 00000 .17427, 02945, .00000 .17254, -01152, 00000 .17236. -05251, .00000 .17370. -.09346, 00000 .17649, -.13433, .00000 18068, -.17509, .00000 .18622, -21567, .00000 .19301, -25605, .00000 .20096. - 29620, .00000 .20998? -33611, .00000 40 .21996, -.37578, .00000 23079, -41521, .00000 24234, -45439, .00000 25451, -.49336, .00000 .26713, -53215, .00000, 28006. -.57079, .00000, 29319, -.60934, .00000 .30646, - 64783, .00000 .31994, - 68630, .00000 .33383, - 72465, .00000 .34805, -76282, .00000 .36237, - 80090, .00000 .37647, - 83897, -.00000 .38968, -.87715, .00000 .40070, -.91566, .00000 .40704, -95446, .00000 .40506, - 99296, .00000 .39283 , -102948, .00000 Although the invention has been described in relation to what is currently considered the most practical and preferred embodiment, it should be understood that the invention should not be limited to the modality disclosed, but on the contrary, it is intended to cover different modifications and equivalent configurations included within the spirit and scope of the appended claims.

Claims (18)

1. An aerodynamic plane for a turbine, having a profile not substantially coated according to the Cartesian coordinate values of X, Y and Z stipulated in Table I, carried only to three decimal places, where Z is a distance from a platform on which the aerodynamic plane is mounted, and X and Y are coordinates that define the profile at each distance Z from the platform.

2. An aerodynamic plane according to claim 1, wherein the manufacturing tolerances for the aerodynamic plane are approximately + 0.254 millimeters.

3. An aerodynamic plane according to claim 1, wherein the blade has a coating that increases the X and Y values of Table I by no more than about 0.381 millimeters. An aerodynamic plane according to claim 1, wherein the manufacturing tolerances for the aerodynamic plane are not greater than + 0.254 millimeters, this aerodynamic plane having a coating that increases the X and Y values of Table I by no more of approximately 0.381 millimeters. 5. An aerodynamic plane according to claim 1, wherein the manufacturing tolerances for the aerodynamic plane are approximately + 0.2032 millimeters. 6. An aerodynamic plane according to claim 1, wherein the blade has a coating that increases the X and Y values of Table I within a scale of 0.127 to 0.3048 millimeters. 7. An aerodynamic plane according to claim 1, in combination with a body carrying the platform, the aerodynamic plane being integrally emptied; a plurality of cooling passages formed through the streamlined aerodynamic plane, and extending from the root to tip portions thereof, and adjacent to each of the pressure and suction sides of the aerodynamic plane. 8. An aerodynamic plane / body combination according to claim 7, wherein the passages extend linearly from the root to tip portions of the aerodynamic plane. 9. An aerodynamic plane / body combination according to claim 8, wherein at least some of the passages have inwardly extending projections in axial positions spaced therealong, to provide turbulent flow. 10. An aerodynamic plane according to claim 1, in combination with a body carrying the platform, the aerodynamic plane having passages formed therethrough, extending from the root to tip portions thereof, to flow a cooling means, a recess formed in the tip portion of the aerodynamic plane to receive the cooling medium carried by the passages, the aerodynamic plane having suction and pressure sides, the tip portion having an opening through the air side. suction of the aerodynamic plane in communication with the recess. 11. An aerodynamic plane / body combination according to claim 10, wherein the passages extend along and adjacent to each of the pressure and suction sides of the aerodynamic planes, the passages forming a pair of rows laterally separated therefrom along the pressure and suction sides, and extending between the front and rear edges of the aerofoil, at least at a location adjacent to a thicker portion of the aerodynamic plane. 12. An aerodynamic plane / body combination according to claim 11, wherein the rows lie between a roll of the aerodynamic plane and the suction and pressure sides, respectively. 13. An aerodynamic plane according to claim 1, having an angle of oscillation as stipulated in the diagram of Figure 8B, with the angle of oscillation and the radius being carried only up to three decimal places. 1

4. An aerodynamic plane according to claim 1, which has a throat as stipulated in the diagram of Figure 10B, the distance of the throat and radius being taken only up to three decimal places. 1

5. An aerodynamic plane according to claim 1, having a roll angle as stipulated in the diagram of Figure 11B, the roll angle and radius being carried only up to three decimal places. 1

6. An airfoil of an evacuated turbine having a bank and a plurality of cooling passages extending from a root portion to a tip portion thereof, including the first and second passages thereof on opposite sides of the bank. warping, and that are adjacent to the suction and pressure sides of the aerodynamic plane, respectively. 1

7. An aerodynamic plane according to claim 16, wherein the passages extend linearly between the root portion and the tip portion. 1

8. An aerodynamic plane according to claim 16, in combination with a body connected to the root portion of the aerodynamic plane, at one end of the body, and a duck tail at an opposite end of the body, having the body and the duck tail at least one cavity, each in communication with the other and with the passages, opening the cavity of the tail of duck through a surface of the same to communicate with a camera of a wheel disk to which it adapts the duck's tail for its union.