Relevant bibliographies by topics / Hollow fan blade

Academic literature on the topic 'Hollow fan blade'

Author: Grafiati
Published: 30 May 2022
Last updated: 31 May 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Contents

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Hollow fan blade.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Hollow fan blade"

1

Guo, Xiao, Qing Zhen Yang, and Yong Qiang Shi. "Vibration Characteristics Analysis of Wide-Chord Hollow Fan Blade." Applied Mechanics and Materials 482 (December 2013): 174–78. http://dx.doi.org/10.4028/www.scientific.net/amm.482.174.

Full text
Abstract:
Wide-Chord Hollow Fan Blade is One of the New Technologies Used in Aircraft Engines. in this Paper, the Modal Analysis Method is Used to Analyze the Influence of the Rib Number and the Rib Thickness to Wide-Chord Hollow Fan Blade Vibration Characteristics. the Result Shows that the Wide-Chord Hollow Fan Blades Greatly Improves the First-Order Vibration Frequency Compared with the Solid Blades, and the First-Order Vibration Frequency of the Wide-Chord Hollow Fan Blades is Reduced with the Increasing Rib Number which is Not Good for Vibration Elimination. the Wide-Chord Hollow Fan Blades’ Vibration Frequency Changes a Little when the Rib Number is Larger than Three. in Addition, the Rib Thickness has Smaller Effect on Wide-Chord Hollow Fan Blade.
APA, Harvard, Vancouver, ISO, and other styles
2

Nikhamkin, M., and B. Bolotov. "Experimental and Finite Element Analysis of Natural Modes and Frequencies of Hollow Fan Blades." Applied Mechanics and Materials 467 (December 2013): 306–11. http://dx.doi.org/10.4028/www.scientific.net/amm.467.306.

Full text
Abstract:
Natural modes and frequencies of gas turbine engine hollow fan blades were experimentally investigated. The blades were produced with the method of super-plastic molding and pressure welding combination. Two independent experimental methods were used: three-component scanning laser vibrometry and impact modal analysis. Natural frequencies and vibration modes of a hollow fan blade and stress fields corresponding to the natural modes were got. The finite element modal analysis was carried out. The hollow fan blade was stated to have particular natural vibration modes. The investigation results can be used to detune the resonance vibrations and to verify calculation models.
APA, Harvard, Vancouver, ISO, and other styles
3

Kielb, R. E. "Mass Balancing of Hollow Fan Blades." Journal of Engineering for Gas Turbines and Power 108, no. 4 (October 1, 1986): 577–82. http://dx.doi.org/10.1115/1.3239950.

Full text
Abstract:
This paper uses a typical section model to investigate analytically the effect of mass balancing as applied to hollow, supersonic fan blades. A procedure to determine the best configuration of an internal balancing mass to provide flutter alleviation is developed. This procedure is applied to a typical supersonic shroudless fan blade which is unstable both in the solid configuration and when it is hollow with no balancing mass. The addition of an optimized balancing mass is shown to stabilize the blade at the design condition.
APA, Harvard, Vancouver, ISO, and other styles
4

Sutliff, D. L., D. L. Tweedt, E. B. Fite, and E. Envia. "Low-Speed Fan Noise Reduction with Trailing EDGE Blowing." International Journal of Aeroacoustics 1, no. 3 (September 2002): 275–305. http://dx.doi.org/10.1260/147547202320962592.

Full text
Abstract:
An experimental proof-of-concept test was conducted to demonstrate rotor-stator interaction tone noise reduction through rotor trailing edge blowing. The velocity deficit from the viscous wake of the rotor blades was reduced by injecting air into the wake from a trailing edge slot. Composite hollow rotor blades with internal flow passages were designed based on Computational Fluid Dynamics codes modeling the internal flow. The hollow blade with interior guide vanes creates flow channels through which externally supplied air flows from the root of the blade to the trailing edge. The impact of the rotor wake-stator interaction on the acoustics was also predicted analytically. The Active Noise Control Fan, located at the NASA Glenn Research Center, was used as the proof-of-concept test bed. In-duct mode and farfield directivity acoustic data were acquired at blowing rates (defined as mass flow supplied to trailing edge blowing system divided by fan mass flow) ranging from 0.5% to 2.0%. The first three blade passing frequency harmonics at fan rotational speeds of 1700 to 1900 rpm were analyzed. The acoustic tone mode power levels (PWL) in the inlet and exhaust were reduced 11.5&–0.1, 7.2&11.4, 11.8&19.1 PWL dB, respectively. The farfield tone power levels at the first three harmonics were reduced 5.4, 10.6, & 12.4 dB PWL. At selected conditions, two-component hotwire and stator vane unsteady surface pressures were acquired. These measurements show the modification of the rotor wake due to trailing edge blowing and its effect on the stator vane to illustrate the physics behind the noise reduction.
APA, Harvard, Vancouver, ISO, and other styles
5

Salnikov, Anton. "3D optimization of the hollow fan blade internal structure." Journal of Physics: Conference Series 1891, no. 1 (May 1, 2021): 012015. http://dx.doi.org/10.1088/1742-6596/1891/1/012015.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Chuan, Zeng, Jiang Xiang-hua, Chai Xiang-hai, and Shi Tong-cheng. "TC4 Hollow Fan Blade Structural Optimization Based on Bird-strike Analysis." Procedia Engineering 99 (2015): 1385–94. http://dx.doi.org/10.1016/j.proeng.2014.12.674.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

Kruglov, Alexey, Ramil Lutfullin, Radik Mulyukov, Minnaul Mukhametrakhimov, Oleg Rudenko, and Rinat Safiullin. "Promises of Low-Temperature Superplasticity for the Enhanced Production of Hollow Titanium Components." Materials Science Forum 838-839 (January 2016): 610–14. http://dx.doi.org/10.4028/www.scientific.net/msf.838-839.610.

Full text
Abstract:
Application of the conventional superplasticity (SP) allows producing the unique hollow structures. One remarkable example is the hollow titanium blade of the air engine fan produced by Rolls-Royce. However, high temperature titanium alloys processing (~ 927 °С) limits wide industrial application of the conventional SP. The solution of the mentioned issue can be found through the application of low-temperature SP. Ti-6Al-4V alloy with ultrafine grain structure at the temperature range of 600 ­ 800 °С has enough ductility resources for the superplastic forming (SPF) of the parts with the complicated shape. The formation of pores in Ti-6Al-4V alloy at uniaxial and biaxial tension at the temperature 600 °С is not observed. The effect of low-temperature SP also allows lowering pressure welding (PW) temperature essentially. Herewith, there is a possibility to produce the hollow parts by the combination of SPF and PW. The main goal is the optimization of the technological scheme and processing temperature. The use of the low-temperature SP provides high quality of hollow components such as blades.
APA, Harvard, Vancouver, ISO, and other styles
8

Cosme, Nicolas, David Chevrolet, Jérôme Bonini, Bernard Peseux, and Patrice Cartraud. "Prediction of transient engine loads and damage due to hollow fan blade-off." Revue Européenne des Éléments Finis 11, no. 5 (January 2002): 651–66. http://dx.doi.org/10.3166/reef.11.651-666.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Chai, Xianghai, Xiaoyun Zhang, Zhiqiang Wang, and Yesheng Liu. "Modeling of the Diffusion Bond for SPF/DB Titanium Hollow Structures." International Journal of Aerospace Engineering 2015 (2015): 1–9. http://dx.doi.org/10.1155/2015/694564.

Full text
Abstract:
Diffusion-bonded titanium hollow warren structures have been successfully applied in aircraft engine components, such as fan blade, and OGV, while the optimal design of the hollow warren structure to improve its impact resistance, especially under bird-strike event, has been a challenge. In this work, a series of impact tests and numerical simulations are carried out to investigate the effect of key geometric features on the overall impact strength of a panel-shaped titanium hollow warren structure. Based on experimental and numerical studies, a quantitative relationship between diffusion bonding seam strength and the overall impact strength is developed. Meanwhile, key geometric factors affecting the resultant bonding seam strength for a typical manufacturing process are identified. This work provides useful references for the optimal design to increase impact resistance for aircraft engine hollow warren structure components.
APA, Harvard, Vancouver, ISO, and other styles
10

Pereira, Michaël, Florent Ravelet, Kamel Azzouz, Tarik Azzam, Hamid Oualli, Smaïne Kouidri, and Farid Bakir. "Improved Aerodynamics of a Hollow-Blade Axial Flow Fan by Controlling the Leakage Flow Rate by Air Injection at the Rotating Shroud." Entropy 23, no. 7 (July 8, 2021): 877. http://dx.doi.org/10.3390/e23070877.

Full text
Abstract:
Axial flow fans are used in many fields in order to ensure the mass and heat transfer from air, chiefly in the heating, ventilation and air conditioning industry (HVAC). A more proper understanding of the airflow behavior through the systems is necessary to manage and optimize the fan operation. Computational fluid dynamics (CFD) represents a real tool providing the ability to access flow structures in areas that measuring equipment cannot reach. Reducing the leakage flow rate, inherent in operation, by synthetic-jet techniques improves performance. This paper presents the CFD results performed on a hollow blade fan developed by our team. The leakage flow is controlled by blowing air from 16 designated circular holes and arranged on the fan shroud. We discuss the results for two rotational speeds (1000 and 2000 rpm) and two injection rates (400 and 800 L/min). The numerical results consistent with the experimental show, for the low rotation speed and high injection ratio, significant gains in power (53%), torque (80%) and leakage flow rate (80%).
APA, Harvard, Vancouver, ISO, and other styles
More sources

Dissertations / Theses on the topic "Hollow fan blade"

1

Гараненко, Тетяна Романівна. "Розробка процесу формоутворення порожнистої лопатки з титанових сплавів для газотурбінних двигунів." Doctoral thesis, Київ, 2021. https://ela.kpi.ua/handle/123456789/40560.

Full text
Abstract:
Запропоновано конструкцію фрагменту порожнистої металевої лопатки вентилятора гофрового типу, враховуючи фактор зниження маси пера лопатки за рахунок конструктивно - технологічних рішень при збереженні експлуатаційних параметрів (властивостей статичної та динамічної міцності). Проведено порівняльний статичний та динамічний аналіз експлуатаційних навантажень лопатки вентилятора суцільної та порожнистої конструкції. На основі виконаного аналізу доведено доцільність вибраної конструкцію поперечного перерізу фрагменту порожнистої лопатки. Запропонована структура технологічного процесу виготовлення порожнистих лопаток, яка ґрунтується на поєднанні двох процесів - зварювання під тиском і формоутворення пера лопатки в ізотермічних умовах. Розроблено метод експериментально - аналітичної побудови кривих деформування на підставі випробувань на згин. Результати дослідження показали, що криві в’язкопластичного деформування матеріалів, можна використовувати для розрахунку технологічних процесів. За результатами відпрацювання комплексної технології виготовлення фрагменту порожнистої лопатки розроблено технічні рекомендації щодо реалізації процесів виготовлення порожнистих лопаток.
APA, Harvard, Vancouver, ISO, and other styles

Books on the topic "Hollow fan blade"

1

Center, Lewis Research, ed. Mass balancing of hollow fan blades. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1986.

Find full text
APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Hollow fan blade"

1

Kielb, Robert E. "Mass Balancing of Hollow Fan Blades." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-195.

Full text
Abstract:
This paper uses a typical section model to analytically investigate the effect of mass balancing as applied to hollow, supersonic fan blades. A procedure to determine the best configuration of an internal balancing mass to provide flutter alleviation is developed. This procedure is applied to a typical supersonic shroudless fan blade which is unstable in both the solid configuration and when it is hollow with no balancing mass. The addition of an optimized balancing mass is shown to stabilize the blade at the design condition.
APA, Harvard, Vancouver, ISO, and other styles
2

Nouri, Hussain, Florent Ravelet, Christophe Sarraf, and Farid Bakir. "Experimental Study of Blade Rigidity Effects on the Global and the Local Performances of a Thick Blades Axial-Flow Fan." In ASME 2010 3rd Joint US-European Fluids Engineering Summer Meeting collocated with 8th International Conference on Nanochannels, Microchannels, and Minichannels. ASMEDC, 2010. http://dx.doi.org/10.1115/fedsm-icnmm2010-30623.

Full text
Abstract:
An experimental investigation on the aerodynamic performances of thick blades axial-flow fans was carried out in this study. Two fans are considered, the first one is rotomoulded (in plastic) and the second one is milled (in aluminium). Both have exactly the same shape, except that the rotomoulded fan has hollow blades. They were designed from an existing fan (manufactured by plastic injection process) used in the cooling system of an automotive vehicle power unit. As far as shape is concerned, the only difference between the two first fans and the traditional injected fan is the blade thickness, whereas as far as rigidity is concerned, the only difference between the rotomoulded and the milled fans is the ability of the rotomoulded fan to be deformed easier than the milled fan. The aim of this study is to determine on the one hand the influence of the blade thickness and on the other hand the way the deformation of the hollow blades may affect the global and the local performances. The global performances of the fans were measured in a test bench designed according to the ISO 5801 standards. The curve of the aerodynamics characteristics (pressure head versus flow rate) and of the global efficiency are slightly lower for the roto-moulded fan. The wall pressure fluctuations were also investigated for three flow rates: one corresponding to the maximum efficiencies of both fans and the two others corresponding to an under-flow and an over-flow rate. The power spectral density (PSD) levels, are between six and nine times higher for the roto-moulded fan at nominal flow rate. At partial flow rate, however, the PSD levels are close for both fans.
APA, Harvard, Vancouver, ISO, and other styles
3

Eberlinc, Matjazˇ, Brane Sˇirok, Marko Hocˇevar, and Matevzˇ Dular. "Influence on the Axial Flow Fan Aerodynamic Characteristic Due to an Introduction of Internal Secondary Flow." In ASME 2008 Fluids Engineering Division Summer Meeting collocated with the Heat Transfer, Energy Sustainability, and 3rd Energy Nanotechnology Conferences. ASMEDC, 2008. http://dx.doi.org/10.1115/fedsm2008-55141.

Full text
Abstract:
Axial fans often show adverse flow conditions at the fan hub and at the tip of the blades. Modification of conventional axial fan blades is presented. Hollow blades were manufactured from the hub to the trailing edge at the tip of the blades. Hollow blades enabled the formation of self-induced internal flow through internal passages. The internal flow enters the internal radial flow passages of the hollow blades through the openings near the fan hub and exits through the tip trailing edge slots. Study of the influence of internal flow on the flow field of axial fan and modifications of axial fan aerodynamic characteristics is presented. The characteristics of the axial fan with the internal flow were compared to characteristics of a geometrically equivalent fan without internal flow. The results show integral measurements of performance testing using standardized test rig, and the measurements of local characteristics. The measurements of local characteristics were performed with a hot-wire anemometry, five-hole probe and computer-aided visualization. We attained reduction of adverse flow conditions near the blade tip trailing edge, boundary-layer reduction on the blade suction side and reduction of flow separation. Introduction of the self-induced blowing led to the preservation of external flow direction, defined by blade geometry and enabled maximal local energy conversion. The integral characteristic reached higher degree of efficiency.
APA, Harvard, Vancouver, ISO, and other styles
4

Ma, Ying, Shengli Xu, Haitao Liu, and Xiaofang Wang. "Optimization of Reinforcing Ribs of a Hollow Fan Blade Using Metamodel-Based Optimization Algorithm." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-57226.

Full text
Abstract:
With the development of aero-engine technology, the demand for fan blade with light weight and better structural performances is urgent. This paper focuses on the weight optimization of a hollow fan blade through changing the thickness and distribution of the inner triangular reinforcing ribs under the constraints of equivalent stress, displacement, bending and torsional frequencies. A finite element analysis process was established in the paper, considering the load of centrifugal force and gas pressure. In the CAD-based model parameterization, to avoid possible interference problems brought by design parameters, the relative locations of control points are applied to determine the locations of control points on the vane profile curves. A metamodel-based global optimization scheme is employed for improving the optimization efficiency. An optimal design with about 13.7% weight reduction is finally obtained by the above optimization procedure. The triangular reinforcing ribs of hollow fan blade were rearranged with the constraints of the stress, displacement and natural frequencies satisfied.
APA, Harvard, Vancouver, ISO, and other styles
5

Schöning, Finn, and Dragan Kozulovic. "The Heron Fan: Concept Description and Preliminary Aerothermodynamic Analysis." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76529.

Full text
Abstract:
The Heron Fan is a new concept of a fuel powered jet engine that does not utilize a conventional core engine. The fan, a single axial compressor of high diameter, creates thrust, similar to a turbofan. Its blades are hollow with inner channels to transport the core air from the hub to the tip, inducing radial compression. The combustion chamber is located in the casing region, either integrated in the blades or in an external ring. After burning, the core air is returned to the blades and is blown out through an expansion device with a large component in circumferential direction. This propels the fan in the opposite direction. The expansion device may be realized by nozzles integrated in the blade trailing edge or by turbine stages integrated in the blade tip region. Subsequently, the core air mixes with the bypass air, which passes the fan axially, and ejects through the main nozzle, producing thrust. To achieve higher compression ratios, it is possible to install core air compressor stages ahead of the fan. The main purpose of this concept is to reduce weight and complexity of the engine, leading to lower production and operating costs. This is achieved by simplifying the engine architecture, integrating the functions and shortening some of the components. In particular, the core engine has been rearranged, thus eliminating the second and in some cases the third shaft. Further, the complete expansion and parts of the compression have been integrated in the fan blade. To assess the aero-thermodynamic parameters, a preliminary cycle analysis has been done, where the most influential parameters were varied. The results show, that the above listed benefits can be achieved while maintaining an efficiency comparable to conventional turbofans. Further, a feasibility study in terms of geometry, internal flow, component implementation and installation has been done, in order to qualify the concept and to identify the most critical aspects. To incorporate the corresponding thoughts and results, as well as to find and eliminate conceptual conflicts and opposing trends, a CAD model has been generated. Overall, the results are sound and encouraging, hence justifying future investigations. However, the Heron Fan concept also brings structural, thermal and aerodynamic challenges which are illustrated and briefly discussed, but still need detailed investigation.
APA, Harvard, Vancouver, ISO, and other styles
6

Han, Pinlian, Tiefeng Chen, and Yesheng Liu. "One-Piece Flow Blade Tuning Process." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-95455.

Full text
Abstract:
Blade tuning is one of the key tasks of the modern aircraft engine design. Generally, a couple of vibration modes of a blade need to be tuned by changing the distribution of its mass and/or stiffness to avoid the resonance at some specified rotating speed. The widely used traditional method for blade tuning is a loop-based process. It requires a number of design iterations between the aero engineer and the structure engineer. It usually takes a few weeks or up to a few months, depending on the experiences of the engineers, to reach an acceptable new design. The uncertainties caused by the non-convergence associated with the loop-based iteration process have led to serious issues for both project management and quality control. To avoid the problem, this paper presents a robust one-piece flow process based on the principle of the set-based concurrent engineering and applying the concept of Lean & DFSS. Following the concept of Lean & DFSS process, the one-piece flow blade tuning starts with defining key parameters and objectives. These parameters consist of a set of design variables relevant to both structure and aero disciplines. The variation range of each parameter is predefined by the manufacture feasibility and the past design experiences. Based on the principles of DOE, only a definite number of FEA models are developed and analyzed. From these analysis results, important parameters are selected and a family of response functions of those concerned objectives is formulated. The achievable ranges of the objectives are well determined accordingly. Guided by these functions, the structure and aero engineers are then able to evaluate instantly any new design from the various combinations of the above-mentioned design parameters. A robust design can be obtained from the given sensitivity of the variance of those design parameters. This methodology can be applied to blade and vane tuning for fans, compressors and turbines alike. In this paper an example of the application of this process is presented for a hollow fan blade tuning, which is accomplished within a week as planned. The methodology can be standardized and used in many other related engineering design processes as well.
APA, Harvard, Vancouver, ISO, and other styles
7

Xianghai, Chai, Wang Zhiqiang, and Tang Zhongbin. "Failure Criteria of Diffusion-Bonded Seam Under Complex Stress State." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43837.

Full text
Abstract:
Diffusion-bonded titanium hollow warren structures have been successfully used on aircraft engine components, such as fan blade, etc., for which failure behavior under impact load is one of the major considerations during design. Studies show that the welding seam de-bonding is the major failure mechanisms under the impact loads. To effectively simulate the de-bonding, phenomenological effective bond strength needs to be properly defined for both the girder region and the edges. In this paper, the bond strength at the hollow region is calibrated through quasi-static tensile tests, in which the specimens are properly designed to represent the cross-section of the hollow region of a typical warren structure. Then, the strength of the edge region is estimated through an inverse method based on the analysis-test correlation of a hollow panel impact test. Such multi-factor coupled seam failure criteria can provide reasonable accordance with test result in the simulation of impact failure of the hollow structure. This means the model with such failure criteria incorporated can provide a useful reference to the aircraft engine hollow warren structure components design.
APA, Harvard, Vancouver, ISO, and other styles
8

Audic, S., M. Berthillier, J. Bonini, H. Bung, and A. Combescure. "Prediction of bird impact in hollow fan blades." In 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-3201.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Pourrajabian, Abolfazl, Reza Ebrahimi, Masoud Mirzaei, Mehdi Ahmadizadeh, and David Wood. "Applying Hollow Blades for Small Wind Turbines Operating at High Altitudes." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42848.

Full text
Abstract:
Since the air density reduces as the altitude increases, operation of Small Wind Turbines (SWTs) which usually have no pitch mechanism, remains as a challengeable task at high altitudes due largely to the reduction of starting aerodynamic torque. By reducing the blades moment of inertia through the use of hollow blades, the study aims to mitigate that issue and speed up the starting. A three-bladed, 2 m diameter small horizontal axis wind turbine with hollow cross-section was designed for operating at two sites with altitude of 500 and 3,000 m. The design variables consist of distribution of the chord, twist and shell thickness along the blade. The blade-element momentum theory was employed to calculate the output power and starting time and, the beam theory was used for the structural analysis to investigate whether the hollow blades could withstand the aerodynamic and centrifugal forces. A combination of the starting time and the output power was included in an objective function and then, the genetic algorithm was used to find a blade for which the output power and the starting performance, the goals of the objective function, are high while the stress limitation, the objective function constraint, is also met. While the resultant stresses remain below the allowable stress, results show that the performance of the hollow blades is far better than the solid ones such that their starting time is shorter than the solid blades by approximately 70%. However, in the presence of the generator resistive torque, the algorithm could not find the blade for the altitude near to 3000 m. To solve that problem, the tip speed ratio of the turbine was added to other design variables and another optimization process was done which led to the optimal blades not only for the lower altitude but also for the higher one.
APA, Harvard, Vancouver, ISO, and other styles
10

Kosmatka, J. "Design and Spin Testing of Integrally Damped Hollow Core Composite Fan Blades." In 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-2032.

Full text
APA, Harvard, Vancouver, ISO, and other styles
You might also be interested in the extended bibliographies on the topic 'Hollow fan blade' for particular source types:
Journal articles
We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!

To the bibliography