Relevant bibliographies by topics / Circumferential attachment of blade

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Circumferential attachment of blade'

Author: Grafiati
Published: 4 June 2021
Last updated: 17 February 2022

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Journal articles on the topic "Circumferential attachment of blade"

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Park, Juhyeon, Hoyong Lee, Gyejo Jung, and Jinyi Lee. "Nondestructive testing of turbine disk roots using solid-state GMR sensor arrays and an axial directional scanning system." International Journal of Applied Electromagnetics and Mechanics 64, no. 1-4 (December 10, 2020): 525–31. http://dx.doi.org/10.3233/jae-209360.

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A nondestructive testing device, consisting of a scanner and signal processing circuits was developed to detect cracks in turbine disk roots. The scanner consists of a longitudinal feeder and a fir-tree-shaped sensor probe. The feeder inserted the sensor probe along the grooves of the turbine blade attachment. Meanwhile, permanent magnets were placed in opposite direction, to generate a closed magnetic field between the magnetic sensors located on the crests of the sensor probe. The fatigue crack in the turbine disk root occurred in the circumferential direction of the turbine. As a result, magnetic flux leakage was caused by disturbing the flow of closed magnetic field by permanent magnets. The magnetic flux leakage was measured by a magnetic sensor. The effectiveness of the proposed device has been verified using artificial defects introduced into the turbine disk roots by electric discharge machining.
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Jin, Guang Yuan, Hua Ouyang, and Zhao Hui Du. "An Experimental Study of Sweep Effect on 3D Flow Downstream of Axial Fans at Off-Design Conditions." Applied Mechanics and Materials 281 (January 2013): 335–42. http://dx.doi.org/10.4028/www.scientific.net/amm.281.335.

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The 3D flow characteristics in axial fans with circumferential skewed blades were investigated at off-design conditions using Hot-wire test, and the effect of sweep on controlling the aerodynamic limits was discussed. Two circumferential skewed fans, with the blade skew angles at 8.3° forward and backward, respectively, were investigated in this study. The 3D instantaneous velocity components in nearfield, downstream of the fans were measured using Hot-wire Anemometry (CTA) at off-design conditions. From the measured results, the structure of passage flow in circumferential skewed fans is analyzed according to flow rate. The boundary layer flow and its relation with circumferential skewed blades, to expand stall-free operation range of axial fans, were discussed. As flow rate decreases, the 3D flow structure in blade passage is controlled by the circumferential skewed blades, and the obvious suppression of decreasing passage flow near shroud and hub region; the main flow retains at mid blade span; the radial flow can’t be neglected; the forward-skewed blade is found to be effective in controlling low energy flow in the vicinity of shroud and hub to expand stall-free operation range; the effect of skewed blades on boundary layer is discussed by radial equilibrium equation; as the centrifugal force increases, the blade radial force Fr of the circumferential forward-skewed blade has an positive effect on pressure gradient, and seems to be efficient to control the style and velocity of boundary layer movement.
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Li, H. D., and L. He. "Blade Count and Clocking Effects on Three-Bladerow Interaction in a Transonic Turbine." Journal of Turbomachinery 125, no. 4 (October 1, 2003): 632–40. http://dx.doi.org/10.1115/1.1622711.

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A computational study of the multirow interaction mechanisms has been carried out for a one-and-a-half stage (NGV-rotor-stator) transonic turbine. In addition to measurable subharmonic unsteadiness on the rotor blades induced by two fundamental stator passing frequencies, a significant aperiodic (“mistuned”) circumferential variation of unsteady forcing magnitude by about three times has been observed in the downstream stator blades. Further parametric studies with various stator blade counts illustrate that the circumferential variation pattern of the unsteady forcing is dictated by the NGV-stator blade count difference, while the local stator forcing magnitude is affected by its circumferential clocking position relative to the upstream NGV blades. The present work suggests that the circumferential clocking together with the choice of blade count should be considered as an aeromechanical design parameter. For cases with stator-stator (or rotor-rotor) blade counts resulting in a tuned (or nearly tuned) unsteady forcing pattern, the clocking position should be chosen to minimize the unsteady forcing. On the other hand, if the choice of blade counts leads to a significant aerodynamic aperiodicity (mistuning), the clocking-forcing analysis can be used to identify the most vulnerable blade that is subject to the maximum forcing.
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Chen, Yuxuan, Zhicheng Zhu, Xiao Li, Yanping Zhang, and Wei Gao. "Aerodynamic Optimization of a 10 kW Radial Inflow Turbine with Splitter Blades." Processes 9, no. 7 (July 20, 2021): 1256. http://dx.doi.org/10.3390/pr9071256.

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The application of splitter blades can improve passage obstructions and reduce flow loss of small-scale organic Rankine cycle (ORC) radial inflow turbines. In this study, taking R245fa as the working fluid, splitter blades are applied to design an impeller layout for a 10 kW ORC radial inflow turbine, and numerical simulation is conducted on different impeller schemes through Fluent 15.0. The influence of the meridian length and circumferential position of the splitter blade on the performance of the turbine impeller is studied. The results show that the meridian length and circumferential position of the splitter blade exert greater effects on the flow field distribution inside the impeller and the impeller performance. When the circumferential offset of the splitter blade is around 0.6 and the blade length is around 80% of the length of main blade, the ORC radial inflow turbine designed in this study reaches optimum performance, and its performance is better than the traditional impeller.
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Zhao, Zhen Hong, Xiu Ming Jiang, Yu Hong Du, and M. Q. Ren. "Basic Equation of the Axial Flow Pump with Linear Distribution of Discharge Velocity and Simulate." Key Engineering Materials 426-427 (January 2010): 176–81. http://dx.doi.org/10.4028/www.scientific.net/kem.426-427.176.

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The basic equation of axial flow pump is derived from the assumption， which axial plane velocity and circumferential velocity distribute linearly along the blade radius. Based on the basic equation, the axial plane velocity and circumferential velocity gradient of discharge blade are calculated, and the flow field of pump is built. Using arc method of design blade, a design case is given. The standard K- epsilon turbulence model is applied to simulate the flow field of axial flow pump by FLUENT software. The simulation results indicate that pump efficiency reach 91%, there aren’t impact or vortex in pump, and the pressure distribution on the blade suction surface is even and high, the anti-cavitation performance is improved.
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Arnone, Andrea, Michele Marconcini, Alberto Scotti Del Greco, and Ennio Spano. "Numerical Investigation of Three-Dimensional Clocking Effects in a Low Pressure Turbine." Journal of Turbomachinery 126, no. 3 (July 1, 2004): 375–84. http://dx.doi.org/10.1115/1.1740780.

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One and a half stages of a low pressure turbine were investigated using a three-dimensional time-accurate viscous solver. Unsteady analyses were carried out by varying the circumferential relative position of consecutive vanes to study the effects of clocking on performance. Assuming that efficiency improvements by clocking are linked to the wake tangential position with respect to the successive blade, a certain circumferential shift in this position can be observed along the blade height due to blade twist and nonradial stacking, giving different contributions. In order to assess this phenomenon, results from three-dimensional computations were compared with a quasi-three-dimensional analysis at mid-span. The effects of clocking on wake interaction mechanisms and unsteady blade loadings are presented and discussed.
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Zhang, L., GZ Tang, ZB Liao, and HC Shang. "Development and experimental research on circumferential impulse microturbine power generation system." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 228, no. 2 (April 4, 2013): 378–87. http://dx.doi.org/10.1177/0954406213484874.

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Circumferential impulse microturbine is a key component of the micro-electro-mechanical system and provides power to the latter. An innovative concept of microturbine power generation system was presented, and prototype improved circumferential impulse microturbine power generation systems were developed, and their output performances were tested. It is validated that the system can operate at a high speed in a dynamic equilibrium state using rolling bearings, and it is found that the output power and rotational speed of a six-blade turbine hollow-cup coil structure is higher than the output power and rotational speed of a six-blade turbine iron-core coil structure. The maximum output power of the eight-blade turbine hollow-cup coil power generation system is 1.1 W, and the maximum turbine rotational speed is 55,000 r/min. The maximum output power of the eight-blade turbine hollow-cup coil system increases up to 25% when compared to the six-blade turbine hollow-cup coil system and increases up to 83% when compared to the six-blade turbine iron-core coil system.
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Jin, G. Y., H. Ouyang, Y. D. Wu, and Z. H. Du. "Experimental and numerical investigations of the tip leakage flow of axial fans with circumferential skewed blades under off-design conditions." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 224, no. 6 (June 1, 2010): 1203–16. http://dx.doi.org/10.1243/09544062jmes1813.

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Experimental and numerical investigations of tip leakage flow of circumferential skewed axial fans were conducted under off-design conditions. Two circumferential skewed fans, with the blade skew angles of 8.3° forward and backward, respectively, and a base fan were investigated in this study. Aerodynamic and aeroacoustic performances were measured. The Navier—Stokes flow simulations were validated experimentally and the key analysis of tip leakage flow was based on computational fluid dynamics results. The simulations show that with a decrease in flowrate, the start of the tip leakage vortex moves towards the leading edge in the chordwise direction and towards the hub in the spanwise direction. These movements are less significant for the forward-skewed blade than for the backward-skewed blade. The strength of the tip leakage vortex decreases along the vortex line. The vortex strength for the forward-skew blade is significantly less than that for the backward-skewed blade. The aeroacoustic source intensity in the tip clearance region is reduced by employing circumferential skewed blades and changes with a change in flowrate in the same manner as the measured sound pressure level. The forward-skewed blade is found to be effective in eliminating noise sources in the tip clearance region and in controlling tip leakage flow to expand the stall-free operation range under off-design conditions.
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Davidson, David L. "Gas turbine disk-blade attachment crack." Journal of Failure Analysis and Prevention 5, no. 1 (February 2005): 55–71. http://dx.doi.org/10.1361/15477020522104.

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Liu, Zhibo, Fajie Duan, Guangyue Niu, Ling Ma, Jiajia Jiang, and Xiao Fu. "An Improved Circumferential Fourier Fit (CFF) Method for Blade Tip Timing Measurements." Applied Sciences 10, no. 11 (May 26, 2020): 3675. http://dx.doi.org/10.3390/app10113675.

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Rotating blade vibration measurements are very important for any turbomachinery research and development program. The blade tip timing (BTT) technique uses the time of arrival (ToA) of the blade tip passing the casing mounted probes to give the blade vibration. As a non-contact technique, BTT is necessary for rotating blade vibration measurements. The higher accuracy of amplitude and vibration frequency identification has been pursued since the development of BTT. An improved circumferential Fourier fit (ICFF) method is proposed. In this method, the ToA is not only dependent on the rotating speed and monitoring position, but also on blade vibration. Compared with the traditional circumferential Fourier fit (TCFF) method, this improvement is more consistent with reality. A 12-blade assembly simulator and experimental data were used to evaluate the ICFF performance. The simulated results showed that the ICFF performance is comparable to TCFF in terms of EO identification, except the lower PSR or more number probes that have a more negative effect on ICFF. Besides, the accuracy of amplitude identification is higher for ICFF than TCFF on all test conditions. Meanwhile, the higher accuracy of the reconstruction of ICFF was further verified in all measurement resonance analysis.
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Dissertations / Theses on the topic "Circumferential attachment of blade"

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Vrbický, Jiří. "Návrh nového typu obvodového závěsu pro lopatky parní turbíny." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2015. http://www.nusl.cz/ntk/nusl-232172.

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This thesis describes design of new circumferential blade attachment on last grade of steam turbine and following stress-strain analysis by FEM with static and cyclic loading. It was created two new design of geometry, which were created based on existing and operating constructional solution of oblique double T blade attachment. It was made stress-strain FEM analysis on original design of blades. Its results served to realize change of construction. Their target was increase load capacity and service life of new types of blade attachment.
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Shingu, Patrick, and Cabrera Miguel Garcia. "Analysis of fan blade attachment." Thesis, Högskolan i Skövde, Institutionen för ingenjörsvetenskap, 2014. http://urn.kb.se/resolve?urn=urn:nbn:se:his:diva-9972.

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This thesis work is based on the analysis of a fan blade attachment whereby a complete 3D model is presented by a partner company. The acceptability of a new design regarding the mechanical loads consisting of dividing the hub into two parts instead of using a solid hub is studied. From the model some critical parameters for the attachment of the blade with respect to the stresses are chosen such as the rotational speed, fillet size of the blade and the neck size of the blade. Parametric studies of these parameters are carried out in order to suggest the new design. Bearing in mind that a safety factor of 2 is the prerequisite, based on the analysis performed on ANSYS Workbench, it is suggested from the preliminary design that the axial fan can operate in two specific scenarios consisting of a rotational speed of 1771 rpm and a rotational speed of 1594 rpm. Using this set of parameters, a suggestion is drawn up on the blade fillet which will give lower stress. Blade fillet size of 30 to 35mm is recommended while a size of 45mm is recommended on the neck of the blade. A modal analysis is performed in order to find at what frequency will the model be vibrating and a lowest and critical frequency of 16.8 Hz is obtained. Finally, a fatigue analysis of some interesting areas is performed in order to determine the numbers of cycles before fatigue failure occur. It is recommended to use the rotational speed since these speeds have offered a High Cycle Fatigue results.
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Andersch, Philipp [Verfasser]. "On the Modeling and Analysis of Helicopter Rotor Dynamics for a Frictional Blade Attachment / Philipp Andersch." München : Verlag Dr. Hut, 2017. http://d-nb.info/1139539507/34.

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Polzer, Stanislav. "Výpočtová analýza pevnosti a životnosti turbínových lopatek." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2009. http://www.nusl.cz/ntk/nusl-228582.

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This master thesis deals with steam turbine blade attachment. Main goal is to perform strength analysis of the given geometry under static and cyclic loads by FEM and software ANSYS. Every particular model is described separately with mentioning of the problems which had to be solved. To create model of material, the tensile tests has been performed and results has been evaluate. There were planned and performed the low cycle fatigue tests to create a model of ultimate states which is used to evaluate the fatigue life of the attachment. Results of the nonlinear FEM analysis is discussed and some improvements of the geometry has been proposed to achieve better state of stress. Finally, the plan of future work has been proposed.
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Štaffa, Petr. "Návrh parní turbíny a optimalizace přihřívacího tlaku páry." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2016. http://www.nusl.cz/ntk/nusl-241692.

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The Diploma’s thesis deals with calculation of tree heat schemas with condensing steam turbine with uncontrolled steam extractions for regeneration – tree low pressure heaters, two high pressure heaters and a deaerator. Heat schemas are compared to each other according to reheat pressure. The most efficient schema is used to steam turbine thermodynamic design – design of control stage and blade stages. At the end of diploma thesis a stress analysis of the last rotor blade is made.
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Book chapters on the topic "Circumferential attachment of blade"

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Lewis, R. Ivan. "Study of Blade to Blade flows and Circumferential Stall Propagation in Radial Diffusers and Radial Fans by Vortex Cloud Analysis." In Modelling Fluid Flow, 373–88. Berlin, Heidelberg: Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-662-08797-8_26.

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Allison, Penelope M. "Casa degli Amanti Supplement." In The Insula of the Menander at Pompeii. Oxford University Press, 2007. http://dx.doi.org/10.1093/oso/9780199263127.003.0026.

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The following artefacts have been mounted for display on a board which in 2001 was hanging on the south wall of the peristyle garden of this house (Plate 125.1) i. Dimensions: 75 mm × 80 mm × 30 mm. Description: Iron lock case. In each corner is an iron attachment nail with sub-hemispherical head (diam.: c.13 mm). Traces of a keyhole. Present location: Casa degli Amanti, wooden board (middle row, right). ii. Dimensions: 85 mm × 77 mm × 25 mm. Description: Iron lock case with a flat-head, iron attachment nail (diam.: c.20 mm) in each corner. L-shaped keyhole (max. l.: 23 mm). Rectangular slit (c.3 mm × 25 mm) near one edge. Present location: Casa degli Amanti, wooden board (middle row, second right). Discussion: Both similar to cat. no. 1935. Possibly cat. nos. 1826 and 1859. See discussion on locks and keys. i. Dimensions: preserved l. of blade: c.170 mm; max. w.: c.75 mm; max. thickness: c.15 mm. Description: Curved axe blade with one side convex and the other concave. Poll badly corroded. Present location: Casa degli Amanti, wooden board (top row, left). ii. Dimensions: preserved l. of blade: c.190 mm; max. w.: c.75 mm; dimensions of poll: 55 mm × 40 mm. Description: Curved axe blade with one side convex and the other concave. Circular eye (diam.: c.30 mm) with the remains of a wooden handle. Present location: Casa degli Amanti, wooden board (top row, second from left). iii. Dimensions: preserved l. of blade: c.175 mm; max. w.: c.50 mm; poll: 55 mm × 40 mm. Description: Curved axe blade with one side convex and the other concave. Circular eye (diam.: c.30 mm). Poll badly damaged. Present location: Casa degli Amanti, wooden board (top row, third from left). Discussion: These axes are Manning type 4 (1985: 16). Possibly cat. nos. 1780 and 1781. See discussion on axes. i. Dimensions: total l.: c.210 mm; max. w. of blade: c.55 mm; max. thickness: 15 mm. Description: approximately right-angled blade. Present location: Casa degli Amanti, wooden board (second row, left). ii. Dimensions: total l.: c.215 mm; max. w. of blade: c.60 mm; max. thickness: 10 mm.
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"Failure of a Laser Beam Attachment Weld Because of Inadequate Penetration in Joint Between Cooling Components for a Jet Turbine Blade." In ASM Failure Analysis Case Histories: Air and Spacecraft. ASM International, 2019. http://dx.doi.org/10.31399/asm.fach.aero.c0047720.

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"Acrostichum. Acrostichum aureum , a. Blade on left, stipe on right, b. Base of stipe with adventitious roots and scales, c. Above, pinnule attachment; below, section of stipe showing marginal spine, d. Areoles in midrib region of pinna. e. Paraphyses. Acrostichum danaeifolium , a. Sterile blade on right, section of sterile stipe on left. b. Fertile blade on right, stipe of fertile blade on left. c. Base of stipe with scales and scale scars below; middle of blade showing pinnae attachment above, d. Single pinna. e. Areoles in the midrib region of pinna. f. Paraphyses. Both drawn by Priscilla Fawcett. From Correll and Correll 1982." In Florida Ethnobotany, 115–26. CRC Press, 2004. http://dx.doi.org/10.1201/9780203491881-10.

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Conference papers on the topic "Circumferential attachment of blade"

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Mamaev, B. I., M. M. Petukhovsky, and A. V. Pozdnyakov. "Shrouding the First Blade of High Temperature Turbines." In ASME 2013 Turbine Blade Tip Symposium. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/tbts2013-2001.

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Blade shrouding gives an opportunity to increase the HPT (high pressure turbine) first stage efficiency by 2–3 %. However, if high gas temperature and high circumferential velocity are at the stage, shrouding can be problematic due to load increasing at blade/disk attachment and high temperature of the shroud itself. To make blade/disk attachment more reliable the shroud axial width has to be decreased by increasing a relative pitch of airfoil cascades t (t = t / b, where t – pitch, b – chord) at the blade tip span. According to experience for a flow with β1 = 50 – 85°, M2 = 0.8 – 1, and Re = (0.8 – 1)•106 high efficient cascades with t = 0.93 – 1.05 can be designed. Application of such a profiling for GTE (gas turbine engine) turbine is demonstrated here. In the turbine meridian flow path the blade was drastically tapered to the tip (tip width was 53 % of the mean width and 46 % of the hub width). To lighten the blade a partial shrouding can be also applied. Model turbine tests showed that local cuts at the front shroud area and the aft shroud area at the airfoil pressure side influenced the efficiency weakly. Required shroud temperature is provided with a cooling. The aircraft turbine with a governed cooling system and a radial clearance control is an example here. In this case the shroud had 3 labyrinth ribs. The shrouding decreased radial clearance by 0.8 mm at main design modes that increased efficiency by ∼ 1.5 %. To cool down the shroud the air downstream the compressor was fed into the cavity behind the front labyrinth rib. At maximal mode with full cooling the relative coolant mass flow (to the compressor mass flow) was mc = 1.3 % and gas leakages through the labyrinth were 0.2 %. It gave acceptable mixed temperature of 530°C in the cavity over the shroud. At cruise high altitude mode and a lower gas temperature and partial cooling with mc = 0.4 % and gas leakages of 0.1 % the mixed temperature also did not exceed 530°C over the shroud. The assessment with taking into account changes of the clearance, the coolant mass flow, and gas leakages showed that the shrouding provided the engine economy improvement by 0.7 – 0.9 % for both modes. For GTPU (gas turbine power unit) the first blade shrouding can be more complicated. However, even the slight turbine efficiency increase provides considerable profits due to GTPU huge power output and long term running. So, when GTE and GTPU designing starts, it is reasonable to consider the turbine first blade shrouding. Here the integral evaluation criterion, which includes the assessment of a possible income from the unit full life cycle running, has to be applied.
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Putchkov, Igor, Alexander Arkhipov, Valery Moskovskikh, Harald Kissel, and Alexander Laqua. "Particularities of Blading Free Resonance Design for Heavy Duty Gas Turbines With Circumferential Rotor Grooves." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26853.

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Blades for heavy duty engines with circumferential rotor grooves are designed such that radial contact is made between the blade teeth and rotor groove at steady state operation conditions. However, sometimes circumferential contact arises between neighboring blade shanks, which is often caused by blade root /rotor thermal expansion. In this case, the radial fixation will give the lower limit of blade frequency band, and the circumferential will give the upper one. The Blade frequency difference between these two fixations might reach about 200–500 Hz depending on blade airfoil and root sizes. When some excitation source (e.g., vane passing frequencies caused by up-stream and down-stream vane counts) has a frequency level situated between blade frequencies caused by radial and circumferential contact, such a case is the subject of the proposed approach. In order to assess how strongly the blade might be fixed under different conditions and how long it might be in resonance during engine start-up and subsequent loading, a 3D elastic-plastic transient analysis and corresponding frequency calculation of blade/rotor assembly is used. At engine start-up the circumferential (lateral) contact between neighboring blade roots is insignificant, and the radial contact between the rotor and the blade is dominant. The lateral contact spot between neighboring blade attachments during start-up appears due to different rates of blade/rotor heating. Further heating leads to an increase of the lateral contact spot areas. The closing of these contact surfaces starts from the outer root edge and spreads toward the inner one, leading to an increase of assembly natural frequencies. Engine loading and further heating lead to the appearance of a circumferential gap between the surfaces, causing the lateral contact to disappear during steady state. The blade root coupling switches again to the usual radial contact state, with the corresponding reduction of natural frequencies. Because the described phenomenon might occur for some time during every start-up and shut-down (from several minutes to couple of hours), it becomes even more severe from a dynamics standpoint if some natural frequency of coupled system crosses the exciting frequency. Examples of assembly frequency tuning are presented.
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Lupini, Andrea, and Bogdan I. Epureanu. "A Friction-Enhanced Tuned Ring Damper for Bladed Disks." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-14815.

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Abstract This paper introduces a new type of damper for turbomachinery blisks. The major pitfalls of the damper concepts currently employed are two: the low level of relative motion that is available at the damper attachment location, and the inability to control the preload at the frictional interface. To address these issues, the proposed damper is designed as a tuned vibration absorber, which allows energy transfer from the blades to the damper provided that the natural frequency of the damper is close to that of the host structure. Thanks to the enhanced energy transfer, the damper can experience increased relative motion. Frictional contacts are then included to dissipate the energy transferred to the damper. The control of the contact preload is also important, as the centrifugal loads acting on the damper are extremely large and could result in the damper being stuck in its groove and not dissipating energy. These two requirements result in competing priorities. The damper structure must be stiff enough to withstand centrifugal loading without affecting the preload too much. However, it also must be compliant to make sure that its natural frequencies can match the ones of the host structure. For this reason, the proposed damper involves a complex geometry that is stiff in the radial direction and softer in the circumferential direction, which is the direction of the relative motion. A model of the damper is created to damp the vibration of a realistic blisk based on the NASA Rotor 67. The effectiveness of the damper is investigated using high fidelity finite element models. Due to the nonlinear nature of the contact, the equations of motion are solved using harmonic balance, and the size of the (linear part of the) system is reduced using Craig-Bampton component mode synthesis. The frequency response of the system is obtained to analyze the effectiveness of the proposed design. Preliminary results show the potential of this technology for structures with such low damping.
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Arif, Waqas, Qingmin Li, Wanshui Yu, Zixin Guo, and Hongbo Li. "Lightning Attachment Characteristics of New Generation Wind Turbine Blade." In 2019 IEEE International Conference on Power, Intelligent Computing and Systems (ICPICS). IEEE, 2019. http://dx.doi.org/10.1109/icpics47731.2019.8942581.

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Garolera, Anna Candela, Joachim Holboell, and Soren Find Madsen. "Lightning attachment to wind turbine surfaces affected by internal blade conditions." In 2012 International Conference on Lightning Protection (ICLP). IEEE, 2012. http://dx.doi.org/10.1109/iclp.2012.6344374.

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Guo, Zixin, Qingmin Li, Wanshui Yu, Waqas Arif, Yufei Ma, and Wah Hoon Siew. "Experimental Study on Lightning Attachment Manner to Rotation Wind Turbine Blade." In 2018 34th International Conference on Lightning Protection (ICLP). IEEE, 2018. http://dx.doi.org/10.1109/iclp.2018.8503300.

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Botto, D., and F. Alinejad. "Innovative Design of Attachment for Turbine Blade Rotating at High Speed." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64959.

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There is evidence of a lack of knowledge in the design of the blade/disk attachment so that the strength of the materials is not fully exploited and the load capability of the attachment is underestimated. The aim of this work is to improve the engineers’ capability in designing the attachment so that higher loads can be carried with the same material. To this end, an optimization method has been applied to the attachment design. A dovetail blade root was chosen as case study and the objective function was the static equivalent stress in the blade and the disc. The dovetail was described by variable parameters under geometrical and physical constraints. Optimization was performed with a Genetic Algorithm (GA). The result of the optimization procedure is the optimal set of parameter values that minimizes the equivalent stress on the critical areas. Moreover, a surrogate function was utilized as a booster to the GA to save computational time. Stress analysis was performed with a commercial Finite Element (FE) software to provide the exact fitness value. An in-house code was developed to manage both the optimization process and the input/output interface with the FE software. The same code provides a decision-making core. This core checks for feasibility of the geometry of the current set of parameters. The expected result is an optimized profile in terms of Von-Misses equivalent stress.
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Shehata, Mohamed, Mamdouh Abdelghanny, Ahmed Abd Elhafez, Mohamed Abdraboo, and Samir Ayad. "Effect of Shorted Blade Circumferential Positions on Centrifugal Pump Characteristics." In 10th International Energy Conversion Engineering Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-4098.

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9

Naboulsi, Sam, and Patrick Golden. "Temporal Life Prediction Analysis of a Turbine Engine Blade to Disk Attachment." In 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
20th AIAA/ASME/AHS Adaptive Structures Conference
14th AIAA. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-1398.

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10

Bo, Shangguan, Zili Xu, Yalin Liu, and An Xu. "Experimental Investigation on Damping Characteristics of Blade With Loosely Assembled Dovetail Attachment." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-22386.

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Abstract:
The damping characteristics of blade with loosely assembled dovetail attachment are investigated experimentally. An experimental method and a test rig were presented to study the blade damping characteristics. In the measurement system, an external force is imposed on blade, to simulate the centrifugal force of blade. The dynamic responses of a group of simulation blades with different dovetail attachment angles were measured in consideration of variable simulation centrifugal force. The damping characteristics of a compressor blade with dovetail attachment were measured too. Some conclusions can be drawn from the experimental results. The resonant frequency increases with the centrifugal force, gradually reaches a certain value. The amplitude of resonant response decreases at the beginning and then increases with the centrifugal force increasing, there exists a special centrifugal force on which the effect of dry friction damping is the best. The change rate of the blade response in the range of neighboring optimal centrifugal force is obviously influenced by the dovetail angle. From the results of the last stage blade of compressor, we can find that the resonant amplitude retains a low level when the centrifugal force is from 1.5kN to 4kN.
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