−0.3896 44 −0.1780 −0.5185 −0.0789 0.4706 14 0.3313 50 −0.1588 0.0842 0.0659 −0.1403 −0.3192 −0.4325 51 1 0.0322 9 0.0157 0.1344 0.4414 −0.3016 Section 17 29 15 53 0.4261 11 43 0.1207 −0.0003 −0.0006 29 0.0686 0.1564 0.0000 0.0422 56 −0.0910 23 36 33 30 0.1652 −0.1156 45 0.4012 −0.3385 0.2817 0.4012 −0.1839 −0.0982 0.2716 2. 0.0104 0.0114 0.0144 0.0004 0.4082 −0.0622 0.0374 47 30 51 12 51 −0.4798 0.3319 −0.1359 0.2978 −0.1087 −0.4287 0.3392 0.0651 −0.5138 0.0966 49 54 16 0.0083 0.0031 −0.0002 2 5 0.0000 22 0.3508 13 20 −0.1246 −0.0637 −0.1331 0.0006 23 −0.3719 46 12 0.3667 40 0.0264 7 29 0.3477 −0.1363 48 0.1892 −0.1599 −0.3923 0.0183 0.0521 0.0001 35 A combustor 56 is arranged between the high pressure compressor 52 and the high pressure turbine 54. 46 −0.5412 0.1509 0.2626 −0.2523 −0.4162 0.0003 0.0207 44 −0.0819 −0.1765 −0.3109 The disclosure can be further understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein: FIG. 0.0010 19 −0.1911 −0.4348 0.1559 0.0160 0.0089 17 −0.3242 0.0292 −0.0193 0.1136 0.0025 34 −0.0142 27 0.0010 51 44 ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:CHUANG, SUE-LI;DONG, YUAN;HINGORANI, SANJAY S.;AND OTHERS;SIGNING DATES FROM 20120927 TO 20121022;REEL/FRAME:029216/0054, Free format text: −0.0539 21 0.0585 0.0036 −0.0007 18 −0.3879 −0.1301 33 0.0307 27 Multi-Wing America keeps moving forward in reversing fan technology with its expanding series of reversible impellers.Multi-Wing’s innovative true reversing airfoil blades produce equal airflow in both directions because each is a true airfoil section. 0.2512 −0.4054 −0.2222 8 −0.5270 51 −0.3564 CHANGE OF NAME;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:054062/0001. 13 0.3679 36 0.2048 −0.1002 48 0.0002 −0.4034 −0.0957 0.0013 22 −0.3590 −0.2183 −0.3861 52 53 −0.4241 0.4387 −0.4483 24 0.0008 −0.1348 −0.5500 The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. −0.4331 −0.1299 0.0030 41 15 −0.2547 40 −0.1588 17 0.0161 −0.0527 0.0664 0.0115 −0.0666 A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. 0.0003 Section 20 −0.0648 47 23 0.1517 −0.4153 0.4131 19 0.3416 −0.3458 0.4488 −0.0219 1 46 −0.1020 0.0413 The inner shaft 40 and the outer shaft 50 are concentric and rotate via the bearing systems 38 about the engine central longitudinal axis X. 32 −0.1059 0.2068 22 −0.3629 0.0054 In one example, the high pressure turbine 54 includes at least two stages to provide a double stage high pressure turbine 54. 39 42 0.0734 0.0013 In one exemplary embodiment, a fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. −0.0004 Section 21 0.0159 −0.4620 1 0.4369 Section 23 0.2781 53 0.1092 0.0019 −0.1733 38 181, Rajdanga Main Road, Near Nabaday Sangha Kolkata - 700107, West Bengal, India, Because airfoil fans are frequently used to move dust laden gases, they are often subjected to material buildup and imbalanced fan operation. 0.2021 −0.2389 −0.3573 0.2800 22 A circumferential coordinate is scaled by the local axial chord, and a span location. −0.4055 −0.0069 −0.4157 29 0.0516 −0.0141 0.2768 −0.1705 −0.4671 −0.0732 1 “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. −0.1158 In one example, the fan blade 42 is aluminum and is provided with the design point profile. 23 −0.3441 −0.3813 Description: exhaust application is ideal for Chicago's SQA airfoil fan.For dirty air or dusty air, the SQB version with backward inclined blades is recommended. 0.0273 0.1856 0.1087 −0.2162 52 −0.4584 0.0024 −0.0544 −0.1547 0.0057 0.4212 2 −0.0596 0.0045 26 −0.3856 7 −0.1375 0.0119 0.0020 The example geared architecture 48 is an epicyclical gear train, such as a planetary gear system, star gear system or other known gear system, with a gear reduction ratio of greater than about 2.3. 20 −0.1900 0.0014 33 High efficiency, non-overloading airfoil wheels are provided on all sizes and arrangements. −0.3798 0.3722 14 −0.0575 0.0297 0.0019 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. 0.2646 10 −0.2735 0.0010 0.0046 −0.1984 −0.4356 35 24 0.2660 −0.1060 33 −0.4162 35 0.4186 50 −0.1190 −0.3098 −0.2973 49 0.0010 38 24 −0.3729 31 0.2952 −0.2715 0.1079 32 15 −0.3242 18 −0.2827 −0.2564 39 −0.0934 −0.1587 −0.2952 0.0004 40 18 0.0060 0.3768 24 The hot combustion gases are communicated through the turbine section, which extracts energy from the hot combustion gases to power the compressor section and other gas turbine engine loads. 0.4901 The axial and circumferential coordinates can be converted to metric (mm) by multiplying by 25.4. The example low pressure turbine 46 has a pressure ratio that is greater than about five. −0.1058 7 37 18 0.2877 0.3484 −0.2323 0.0015 Alternatively, substantial conformance is based on a determination by a national or international regulatory body, for example in a part certification or part manufacture approval (PMA) process for the Federal Aviation Administration, the European Aviation Safety Agency, the Civil Aviation Administration of China, the Japan Civil Aviation Bureau, or the Russian Federal Agency for Air Transport. 0.4011 0.0556 −0.3721 5 0.0024 41 20 −0.3233 50 −0.0629 −0.0055 0.0000 30 27 −0.3527 −0.2248 16 41 0.0315 34 −0.4478 −0.2895 3 −0.0706 54 −0.3212 13 32 0.0030 7 −0.3879 31 0.0234 −0.4059 −0.0281 0.2849 41 −0.4064 38 −0.3069 0.2420 0.2567 0.1498 37 −0.3704 −0.3939 0.0016 0.4892 40 43 −0.1765 18 27 1 schematically illustrates a gas turbine engine embodiment. 23 −0.1218 0.1640 0.0000 0.0068 0.2133 0.0003 −0.0529 0.4011 −0.0616 −0.2036 −0.0530 0.3820 30 0.2123 32 −0.4485 −0.0708 −0.3218 23 0.0737 0.3832 −0.3642 −0.2613 The unicast aluminum Airfoil designed impellers have 6, 7, or 8 blades, taper-lock bushings, and can be used in applications up to 3450rpm. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location. 0.0409 −0.1284 −0.0681 −0.0001 0.1846 0.0002 43 3 36 −0.1629 0.2134 0.1949 −0.0708 −0.4370 21 −0.3116 22 −0.0005 0.0736 16 4 56 −0.1986 52 43 −0.5534 −0.3736 −0.3542 −0.1311 0.4360 0.0022 −0.0742 41 0.0845 0.0011 13 0.0390 0.0291 51 0.0896 54 −0.4061 0.0031 The materials contained in this website are protected by applicable copyright and trade-mark law. 5 −0.2588 55 14 0.4062 −0.0117 −0.2476 The example gas turbine engine includes the fan 42 that comprises in one non-limiting embodiment less than about twenty-six (26) fan blades. 37 34 1 13 −0.2180
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