6 28 56 Our qualified engineering and service teams are eager to earn your business and help you maintain an efficient operation. −0.3981 0.3332 45 34 0.0148 −0.4777 −0.4373 −0.1917 36 Because airfoil fans are frequently used to move dust laden gases, they are often subjected to material buildup and imbalanced fan operation. 2 0.0002 −0.3987 −0.2288 0.0650 0.0569 −0.1119 38 0.3850 21 −0.0094 6 8 0.0411 37 0.4095 45 −0.0532 In a further embodiment of any of the above, the array of fan blades includes less than about twenty (20) fan blades. 0.0018 0.1645 0.0083 0.0059 32 21 0.1513 Plenum Fan, Airfoil Impeller, 9-Blades, Arrangement 3 Application. “Low corrected fan tip speed” is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram °R)/518.7)]0.5. −0.1027 Section 21 39 53 0.0160 −0.2623 −0.4474 0.0393 17 0.2638 22 −0.1110 19 12 −0.3602 39 0.0430 44 −0.3760 −0.2815 50 36 2 0.3568 0.0222 0.4776 0.0071 4 −0.3246 −0.5185 Section 6 0.3484 −0.4626 0.0120 43 55 52 −0.1380 0.1954 −0.0004 10 −0.3148 51 −0.4615 0.3477 34 21 −0.1839 0.0009 −0.3782 −0.0279 31 −0.5089 40 0.0203 0.2333 0.4488 Pressure and suction sides 72, 74 join one another at the leading and trailing edges 68, 70 and are spaced apart from one another in an airfoil thickness direction T. An array of the fan blades 42 are positioned about the axis X in a circumferential direction Y. 56 25 0.0000 −0.2182 0.1114 −0.0055 0.0884 0.2900 11 −0.0978 −0.3696 48 0.0006 A circumferential coordinate is scaled by the local axial chord, and a span location. 14 16 0.2285 −0.4153 −0.0995 International Search Report and Written Opinion for PCT Application No. 35 19 0.0002 1 −0.2385 −0.2776 −0.1780 34 0.1822 −0.0742 −0.3722 25 −0.2448 40 −0.0779 0.0004 −0.2961 44 −0.0258 −0.3834 0.0010 −0.0630 18 The geometry of the airfoil 64 are described in terms of Cartesian coordinates defined along X, Y and R axes, which respectively correspond to the axial (X), circumferential (Y) and radial (span) R directions shown in FIGS. 0.2991 −0.1788 19 43 0.2639 In one example, the fan blade 42 is aluminum and is provided with the design point profile. 12 2 is a plane view of the fan blade airfoil illustrating directional references with the span positions and local axial chords referenced in Table 1. −0.1540 46 They are commonly used for ventilation, forced cooling at higher pressures, and on dust collectors, where the fan is on the clean side of the collector. 18 0.4092 4 0.2653 0.3661 0.0088 Section 3 0.1627 0.0015 0.1981 32 22 −0.5566 −0.1002 40 0.0030 The disclosed fan blade includes an airfoil having a leading edge, a trailing ling edge, a convex side, a concave side and a distal tip. 0.4359 0.0229 0.0032 −0.2965 0.0037 0.4012 −0.0782 0.0512 0.0137 −0.3642 22 −0.3273 −0.2641 0.0154 −0.3518 −0.0769 0.1344 −0.4620 31 0.0000 28 46 −0.1400 −0.3682 17 5 0.0050 0.0142 55 0.1739 0.0000 The pressure ratio of the example low pressure turbine 46 is measured prior to an inlet of the low pressure turbine 46 as related to the pressure measured at the outlet of the low pressure turbine 46 prior to an exhaust nozzle. STEAM TURBINES, Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members, INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04, INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS, Application in turbines specially adapted for the fan of turbofan engines, Shape given by a set or table of xyz-coordinates, GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS, TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE, CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION, Efficient propulsion technologies, e.g. 0.0104 0.3409 0.1381 −0.2855 0.0229 −0.2820 24 0.2660 13 As a result, significantly larger fan blades may be used in the fan section. 0.0281 0.3849 0.2849 0.1122 −0.3387 0.0086 29 31 45 37 0.1388 −0.2216 0.0117 −0.4706 0.0863 −0.2968 −0.2200 0.0012 25 42 0.0159 −0.1341 0.1955 0.0024 0.1128 0.1248 0.0502 38 −0.1596 −0.2874 0.0296 −0.0110 −0.3075 48 24, 2014. 0.2288 0.0046 −0.3791 0.3665 7 −0.3609 0.2594 −0.1775 −0.0529 30 17 0.0390 −0.1981 −0.0878 −0.3673 0.1821 12 0.0049 −0.2381 −0.2476 0.0045 0.0156 35 −0.3667 52 2 9 0.3857 −0.3224 −0.3100 −0.0776 −0.3427 38 −0.0913 24 −0.3336 −0.2939 0.0030 −0.4483 They are the most efficient design for moving large volumes of air. −0.3475 19 0.1416 0.1648 −0.5522 −0.0003 0.0098 0.0003 −0.3454 0.1112 −0.3343 0.0008 41 0.0293 −0.4219 0.2768 38 0.0059 −0.3729 0.0070 −0.2002 0.0044 0.0036 0.0562 8 −0.3719 −0.4106 0.0290 0.0431 17 −0.4798 19 43 37 11 12 16 29 0.1072 20 27 −0.4247 −0.1010 FIG. 24 −0.3255 −0.4021 −0.2667 −0.3451 0.0403 35 In one disclosed embodiment, the gas turbine engine 20 includes a bypass ratio greater than about ten (10:1) and the fan diameter is significantly larger than an outer diameter of the low pressure compressor 44. 27 0.0117 25 55 At part speed engine operating conditions along the engine operating line, the flow incidence angle increases from F1 to F2. −0.0383 0.0014 0.0977 0.2105 −0.4540 −0.3472 −0.3222 0.0000 The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. 0.1017 TABLE 1 1. 16 −0.0362 −0.4463 −0.3604 −0.0003 −0.0052 0.2464 0.4917 0.1652 −0.3549 −0.1585 13 36 51 0.0516 7 −0.0386 8 12 −0.4563 −0.0526 −0.4888 −0.0626 0.0217 0.2351 −0.3913 −0.4974 0.3833 −0.1762 −0.1477 56 0.0010 0.0878 0.0311 −0.2553 12 −0.3588 30 5 0.2783 35 −0.2289 −0.2895 56 13 5 0.0318 −0.3923 0.0007 41 0.1731 4 0.0024 52 −0.3253 −0.1459 −0.3709 0.0019 18 42 0.0049 −0.2666 −0.1302 −0.5138 −0.0193 12 −0.0616 0.0011 0.3880 −0.4479 −0.3896 −0.3120 −0.2149 0.3314 20 0.4387 −0.1094 0.2113 33 0.0030 0.0615 −0.1665 0.0326 0.0303 6 0.3416 0.0003 50 25 −0.0159 The disclosed gas turbine engine 20 in one example is a high-bypass geared aircraft engine. −0.3876 16 24 0.0010 0.0223 36 −0.2192 −0.1221 −0.3939 −0.5283 47 3 0.0026 19 0.1192 0.0031 −0.0676 −0.2205 28 0.0458 −0.4306 −0.2650 −0.2215 0.0059 3 (some of which have been indicated by circled numbers). 26 21 −0.1550 23 2 −0.1311 0.1856 11 0.0136 −0.1031 0.0001 −0.2280 0.2696 −0.0183 −0.0010 32 0.0264 17 43 0.0312 0.0134 54 0.2420 −0.3611 45 −0.1271 50 0.0076 0.0035 0.4212 −0.3736 0.4715 −0.5500 Figure 2.1 shows static pressure vs. airflow comparison for 24" x 24" dampers. −0.1228 0.1964 11 −0.1205 24 −0.1077 1 47 Section 8 9 0.3506 0.1559 0.0018 −0.3395 54 3 28 0.1391 0.1334 0.4715 0.3808 0.4011 −0.3225 −0.2950 2 and 3. −0.0765 28 −0.0270 0.0000 0.1142 −0.3233 52 33 0.0310 24 0.4019 43 0.0073 −0.2042 −0.0856 The unicast aluminum Airfoil designed impellers have 6, 7, or 8 blades, taper-lock bushings, and can be used in applications up to 3450rpm. −0.4331 43 0.4892 −0.3722 0.3659 −0.1187 BOSON’s airfoil fan blades include special construction features, such as solid nose piece utilization, to provide superior resistance to abrasion and wear. 0.1713 0.3927 53 31 −0.3206 0.0101 0.2161 5 3 −0.1984 23 14 −0.1299 46 52 −0.1588 55 0.0026 −0.0003 20 13 4 5 −0.4470 −0.3008 0.2310 0.0167 0.0212 0.0020 0.0028 0.4176 43 −0.1768 16 0.1201 −0.2481 0.0042 20 24 47 The multi-element airfoil blade design presented here represents a “proof of concept” design. 0.1452 0.0208 −0.4119 −0.3879 18 −0.2252 A circumferential coordinate is scaled by the local axial chord, and a span location. −0.0007 −0.5221 43 0.0018 −0.3564 −0.3420 3 −0.1771 −0.4328 0.2007 6 0.0010 19 −0.3613 −0.1045 7 48 0.1092 −0.3207 −0.3866 In one exemplary embodiment, a gas turbine engine includes a compressor section. −0.2198 55 44 −0.3372 0.1948 −0.1016 43 0.0297 0.2982 45 51 0.0008 −0.4076 9 53 −0.4181 0.0045 37 0.1208 32 0.3347 2 −0.1599 0.0134 −0.0275 32 0.0117 0.1487 0.0000 −0.4743 50 0.0556 56 30 20 −0.5208 0.4713 54 BOSON’s airfoil fan blades include special construction features, such as solid nose piece utilization, to provide superior resistance to abrasion and wear. 0.0112 53 −0.3948 33 0.3217 32 0.3462 “Low fan pressure ratio” is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. 0.3493 −0.0117 52 PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY, Owner name: 21 −0.4981 −0.5024 0.0014 30 0.4705 0.3113 3 0.2430 0.0105 0.4121 −0.4425 −0.4793 0.4553 −0.2741 1 −0.4605 0.0403 −0.3665 −0.1501 0.0005 −0.0219 −0.3187 0.0765 −0.0728 22 0.0017 −0.0001 23 0.1064 0.0075 −0.1352 0.0122 −0.1375 0.0239 0.0009 −0.4168 8 −0.0846 −0.3879 43 −0.0070 0.0730 0.0015 −0.4044 0.0571 50 0.0010 Section 2 0.0076 The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. 0.2287 0.0005 9
2020 fan blades airfoil