−0.3979 0.1202 The camberline is a line drawn halfway between the two surfaces, and the distance between the camberline and the chordline is … 0.0049 −0.4042 −0.1488 The mid-turbine frame 57 includes vanes 59, which are in the core airflow path and function as an inlet guide vane for the low pressure turbine 46. −0.3817 −0.3353 0.2149 13 26 56 −0.2569 −0.1755 0.0002 −0.0629 Because many systems have multiple dampers in series, static pressure drop becomes important when velocity is above 1500 fpm. 0.3830 A fan blade for a gas turbine engine is disclosed. −0.3890 4 Airfoil blade wheel is fabricated of high-strength steel to assure long lasting, efficient operation. 0.0016 −0.3157 −0.3793 −0.3355 0.0156 −0.4584 39 16 7 39 −0.3673 0.0017 0.0045 −0.3597 3 0.0036 −0.0856 46 −0.2954 21 54 19 0.1107 0.0740 −0.2601 0.0223 −0.1576 44 0.0117 −0.4460 0.0159 −0.1746 −0.4055 −0.2524 33 −0.2912 52 12 0.0031 −0.2984 12 0.0296 6 40 −0.4037 0.4187 11 −0.3222 −0.2119 −0.0504 The span coordinate is provided as a radial location (boxed numbers in FIG. −0.3908 0.0413 −0.1243 2 34 8 −0.2222 45 3 51 0.0503 0.0062 0.2288 32 −0.0539 −0.0774 A substantially conforming airfoil, blade or vane structure has surfaces that conform to the specified sets of points, within the specified tolerance. 17 Custom diameters available from 12″ through 79″, and airflow capacities range to 200,000 cfm. 48 0.0023 −0.3817 0.0558 38 −0.0880 −0.1175 25 0.0010 32 20 0.0000 −0.3754 −0.1375 −0.2132 46 0.0382 −0.1218 In addition, the airfoil 64 is sometimes rotated with respect to a radial axis or a normal to the platform or shroud surface, for example by up to ±10° or more. 0.0014 0.0649 −0.3992 0.0229 11 47 −0.3903 −0.0575 −0.3895 0.0100 43 0.3409 11 −0.0003 16 −0.0758 0.2440 Aircraft propellers approach the speed of sound at their tips, and low drag is critical. 0.0059 −0.1781 0.0082 22 0.1974 0.4364 12 −0.1400 −0.5185 −0.4500 −0.3446 0.0000 0.0030 −0.3259 −0.3564 −0.0729 0.0458 −0.3896 Integrating innovative pressure cast aluminum hubs and adjustable pitch blades, ELTA axial airfoil impellers deliver an impressive array of airflow performance. −0.3458 0.0297 5 40 38 28 −0.3856 0.4901 0.0059 47 43 2 0.0009 52 −0.1399 10 0.0076 0.0229 −0.3736 −0.4306 −0.4369 8 0.2800 42 −0.2970 0.4444 −0.3115 −0.4771 −0.2386 10 Assignors: DONG, YUAN, HINGORANI, SANJAY S., CHUANG, SUE-LI, PRASAD, DILIP, Assigned to RAYTHEON TECHNOLOGIES CORPORATION. 4 0.0011 −0.3550 Additional elements such as cooling holes, protective coatings, fillets and seal structures may also be formed onto the specified airfoil surface, or onto an adjacent platform surface, but these elements are not necessarily described by the normalized coordinates. −0.2038 0.0071 0.0943 0.0219 0.0605 Tube Axial – These fans consist of propeller shaped blades mounted in a tube. 8 38 −0.1780 33 1. −0.0676 −0.0732 0.4350 9 Axial blade styles. −0.4530 2 −0.4678 0.0000 2 −0.5221 53 14 −0.1174 0.2199 0.0030 0.0026 48 0.3820 0.0124 −0.2345 37 −0.3549 0.0026 22 −0.3527 −0.0676 14 4 −0.1447 40 −0.0666 44 −0.5184 39 −0.1900 −0.3008 −0.2893 0.1481 −0.0370 32 34 0.1201 −0.0504 0.0571 −0.4439 0.0092 0.2115 −0.0386 −0.0007 0.4159 0.0014 −0.0573 0.1822 9 0.2383 13 0.0557 −0.1674 0.0836 38 0.0312 53 These are blades, motors, controls, and generalized air movement profiles of flat blades and airfoil Blades. −0.0410 0.0037 0.0564 6 −0.1722 20 The example low pressure turbine 46 has a pressure ratio that is greater than about five. −0.1032 PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY, Owner name: 54 0.1233 0.1798 0.0003 0.3659 0.0050 −0.1446 3 0.0662 1 15 48 −0.2255 −0.0275 −0.0360 0.1074 −0.3781 50 1 36 0.0901 −0.2445 −0.3510 0.0049 0.0166 0.0030 0.0052 −0.1401 0.1077 16 3 −0.4920 0.0155 0.0108 −0.2149 −0.0555 −0.3831 26 0.0036 0.4212 0.0165 −0.3343 29 −0.0630 −0.1709 0.0067 0.0102 16 7 0.4196 0.0381 −0.1269 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. −0.2248 32 −0.2895 49 7 0.2464 −0.0005 0.0024 9 56 28 −0.3755 0.1970 0.2012 Future work will focus on validating the results experimentally and optimizing the multi-element airfoil geometry. Up to 5 years warranty. 29 12 Household fan blades are extremely slow, so they need more chord to push a meaningful amount of air. −0.4030 5 0.2048 53 22 39 61/706,859, which was filed on Sep. 28, 2012. −0.0055 0.0740 18 0.0730 −0.4637 −0.1348 −0.4075 0.1806 0.2494 56 25 30 RAYTHEON TECHNOLOGIES CORPORATION, MASSACHUSETTS, Free format text: 0.4713 36 53 0.0000 −0.3640 0.3766 0.0049 14 0.0226 0.0075 0.0000 −0.4626 30 0.0000 −0.1886 35 We also have significant experience machining high-temperature alloy turbine blade castings – typically holding tolerances of .0005 of an inch. 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. 19 Thus, the compactness of the gas turbine engine 20 is increased and a higher power density may be achieved. 0.3416 0.0239 −0.3642 0.3484 51 0.0037 −0.3903 0.4021 0.0743 0.1588 19 53 0.0018 47 The general location of the coordinates are shown by the points illustrated in FIG. 0.0413 −0.3484 0.1347 0.2033 0.1366 56 15 43 25 −0.2163 15 −0.1477 The fan blade 42 is plastically deformed, by die stamping, for example, to change the exterior surface of the fan blade 42 from the design point profile to the part-speed profile. −0.4727 −0.3412 The high-speed spool 32 includes an outer shaft 50 that interconnects a high pressure (or second) compressor section 52 and a high pressure (or second) turbine section 54. 8 −0.3109 0.3752 −0.3990 2, the fan blade 42 is supported by a fan hub 60 that is rotatable about the axis X. A combustor is fluidly connected to the compressor section. −0.3104 −0.4738 6 55 0.0242 27 −0.1196 27 0.0003 −0.3306 0.0223 0.2098 −0.1368 0.0018 0.0043 −0.2715 −0.0607 −0.1984 2 −0.3696 0.0017 27 −0.0219 26 −0.3420 −0.1540 15 −0.4784 0.4473 0.0018 −0.0638 −0.3992 −0.0001 −0.2623 0.1987 45 0.0315 56 −0.1705 9 The axial and circumferential coordinates can be converted to metric (mm) by multiplying by 25.4. 2 The example engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis X relative to an engine static structure 36 via several bearing systems 38. 8 This tolerance is generally constant or not scalable, and applies to each of the specified blade surfaces, regardless of size. 0.0314 FIG. −0.5274 31 42 −0.2036 −0.3098 4 −0.0532 −0.4219 56 UNITED TECHNOLOGIES CORPORATION, CONNECTICUT, 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, PAYMENT OF MAINTENANCE FEE, 4TH YEAR, LARGE ENTITY (ORIGINAL EVENT CODE: M1551); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY, RAYTHEON TECHNOLOGIES CORPORATION, MASSACHUSETTS, CHANGE OF NAME;ASSIGNOR:UNITED TECHNOLOGIES CORPORATION;REEL/FRAME:054062/0001, Integrated strut-vane nozzle (ISV) with uneven vane axial chords, Shroud housing supported by vane segments, Gas turbine engine turbine blade airfoil profile, Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the third stage of a turbine, Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the fourth stage of a turbine, Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the sixth stage of a turbine, Airfoil shape for ninth stage compressor rotor blade, Airfoil shape for fourth stage compressor stator vane, Aircraft gas turbine engine particle separator, External profile for turbine blade airfoil, Ultra-efficient propulsor with an augmentor fan circumscribing a turbofan, Hollow fan blade tuning using distinct filler materials, Fan stagger angle for geared gas turbine engine, Ultra-low noise forward-sweeping fan blade profile, Low pressure ratio fan engine having a dimensional relationship between inlet and fan size, Geared low fan pressure ratio fan exit guide vane stagger angle, Gas turbine engine having support structure with swept leading edge, Compressor blade having a ratio of leading edge sweep to leading edge dihedral in a range of 1:1 to 3:1 along the radially outer portion, Non axis-symmetric stator vane endwall contour, Gas turbine engine mid turbine frame with flow turning features, Gas turbine engine airfoil internal cooling features, Blade outer air seal for a gas turbine engine, Integrally bladed rotor with slotted outer rim, Engine component having support with intermediate layer, Gas turbine engine component with film cooling hole feature, Core arrangement for turbine engine component, Gas turbine engine component having variable width feather seal slot. −0.2735 0.0209 29 45 10 44 The true reversible is a true airfoil blade in both directions. 0.4095 −0.1211 27 −0.1347 0.0036 33 26 −0.3451 −0.4043 39 35 −0.4142 0.0162 14 −0.0464 0.1780 19 38 −0.1040 19 0.0001 0.3447 −0.0346 0.4092 55 −0.2613 0.0836 −0.3593 20 35 −0.1967 0.0101 46 −0.0526 The fan section 22 of the engine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet. 7 18 0.0615 29 38 −0.2023 −0.0537 48 0.0021 0.0008 −0.1058 0.2681 −0.1626 −0.0678 0.2420 41 0.0301 55 0.0403 0.0059 −0.1278 −0.0746 0.2656 0.0084 −0.1223 −0.2903 14 51 13 −0.0532 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. −0.4415 11 0.2676 31 0.0157 0.0122 0.0031 24 −0.2186 0.0536 Hvls Fan Blades, Industrial Fan Blades, Fan Parts Fan Blade manufacturer / supplier in China, offering Custom Aluminum Die Casting Fan Blade Airfoil Blade for Fan Parts, Customized Galvanized Deep Drawing Stamping Part for Bracket, Sheet Metal Fabrication Stamping Parts Mounting Holder Clamp Clip Bracket and so on.
2020 fan blades airfoil