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Journal articles on the topic 'Thin-walled shaft gas turbine engine'

Author: Grafiati

Published: 28 May 2022

Last updated: 31 July 2025

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1

Robotham, W. S., T. H. Hyde, E. J. Williams, and J. W. Taylor. "Elastic–plastic buckling behaviour of shafts in torsion." Aeronautical Journal 104, no. 1031 (2000): 1–7. http://dx.doi.org/10.1017/s0001924000064095.

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Abstract The development of more powerful and efficient aero-engines requires ways of increasing the torque transmitted by shafts, whilst also restricting their dimensions and weight. Thin-walled designs can assist this objective, but their use is limited by their torsional collapse behaviour. Of particular interest are conditions leading to buckling instability. The paper investigates the factors influencing this behaviour in order to provide the basis for an improved analysis method applicable to typical gas turbine aero-engine components. The Riks finite element algorithm has been successfu

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2

Katrasˇnik, T., S. Rodman, F. Trenc, A. Hribernik, and V. Medica. "Improvement of the Dynamic Characteristic of an Automotive Engine by a Turbocharger Assisted by an Electric Motor." Journal of Engineering for Gas Turbines and Power 125, no. 2 (2003): 590–95. http://dx.doi.org/10.1115/1.1563246.

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Turbocharging and subsequent charge cooling of the working medium usually causes increase of the mean effective pressure in an automotive diesel engine. Poor performance during the engine load increase is attributed to the nature of energy exchange between the engine and the turbocharger. Filling of the intake and exhaust manifolds, as well as consequent increase of the pressure and acceleration of the rotating components of the turbocharger require a certain period of time. Dynamic performance of the turbocharger can be substantially improved by means of an electric motor attached directly to

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3

Salehi, Mohsen, Hooshang Heshmat, and James F. Walton. "On the Frictional Damping Characterization of Compliant Bump Foils." Journal of Tribology 125, no. 4 (2003): 804–13. http://dx.doi.org/10.1115/1.1575774.

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High-speed rotor systems use either fluid film or rolling element bearing supports, depending upon their design and operating constraints. Regardless of bearing type used, these systems require specific bearing and support stiffness and damping characteristics to achieve the desired stable and low vibration operation. Building upon the technology of thin metallic corrugated bump foils presently used in a particular class of film riding hydrodynamic bearings, a novel corrugated bump foil damped mount is introduced which provides stiffness and damping for application with rolling element bearing

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4

Grinkrug, M. S., I. K. Andrianov, M. Kara Bally, and Yu I. Tkacheva. "SYSTEM FOR REGISTERING CRACKS IN THE BLADES OF A GAS TURBINE ENGINE USING AN IONIZING SUBSTANCE IN NON-STATIONARY CONDITIONS." Kontrol'. Diagnostika, no. 316 (October 2024): 59–64. https://doi.org/10.14489/td.2024.10.pp.059-064.

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The study is devoted to the problem of detecting cracks in the blades of gas turbine engines using a damage registration system in non-stationary conditions. The principle of operation of the system is based on the manifestation of the ionizing properties of the active substance in the system of shell capsules at high temperatures. The study examines the physico-chemical processes that occur with the active substance in the capsule when it is heated to operating temperatures. A mathematical dependence is proposed to determine the mass of the active substance to be placed in a thin-walled capsu

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5

Hu, Chun Yan, Zhi Qiang Kong, Xin Ling Liu, and Chun Hu Tao. "Effects of Gas Film Hole on Mechanical Property and Oxidative Damage of Turbine Blades." Materials Science Forum 944 (January 2019): 421–25. http://dx.doi.org/10.4028/www.scientific.net/msf.944.421.

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With the development of aero-engine with high specific flux, high thrus-weight ratio, and high turbine inlet temperature, it is an effective way to improve the cooling efficiency by designing dense gas film holes on the blade surface of the turbine blades, especially at the intake side. However, the introduction of gas film holes destroys the geometrical integrity of the blade structure, resulting in a multiaxial high stress state of the blade material around the small holes, which seriously affects the strength and life of the cooling blades. In addition, the geometry design of the gas film h

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6

Scherbakov, Alexander, Anatoly Chulenyov, Yury Deniskin, and Evgeny Grigoriev. "Application of correction factors in Rayleigh method in calculation of the fundamental frequency of vibration Cylindrical shell with rectangular cross section." E3S Web of Conferences 413 (2023): 04003. http://dx.doi.org/10.1051/e3sconf/202341304003.

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A number of gas turbine engine components, in particular, combustion chamber flame tube hoods, jet nozzles, afterburner chambers and some elements of the power body can be considered as thin-walled shells. Loads which excite vibrations of these assemblies are gas-dynamic forces of gas flow pulsation, loads transferred from supports from rotation of the unbalanced rotor, non-stationary flowing by an incoming air stream, dynamic loads, transferred to the engine through its attachment units to the aeroplane at landing and run, etc. The magnitude and nature of variation of these loads in time are

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7

Wang, Shuai, Xiaolei Wang, Yanrong Wang, and Hang Ye. "An Equivalent Damping Numerical Prediction Method for the Ring Damper Used in Gears under Axial Vibration." Symmetry 11, no. 12 (2019): 1469. http://dx.doi.org/10.3390/sym11121469.

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In aircraft gas turbine engines, gears in the transmission system are typically cyclic in structure and inevitably encounter large dynamic loads, such as meshing excitation, resulting in high vibration loads in resonance. To prevent gear resonance failure, a ring damper is employed to reduce the resonance response. As relative motion between the gear and the ring damper occurs, vibration loads can be reduced by friction energy dissipation. Moreover, the gears in the aircraft engine are thin-walled and their axial stiffness is much smaller than radial stiffness; thus, it is easier for axial vib

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8

Guo, S. M., T. V. Jones, G. D. Lock, and S. N. Dancer. "Computational Prediction of Heat Transfer to Gas Turbine Nozzle Guide Vanes With Roughened Surfaces." Journal of Turbomachinery 120, no. 2 (1998): 343–50. http://dx.doi.org/10.1115/1.2841412.

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The local Mach number and heat transfer coefficient over the aerofoil surfaces and endwalls of a transonic gas turbine nozzle guide vane have been calculated. The computations were performed by solving the time-averaged Navier–Stokes equations using a fully three-dimensional computational code (CFDS), which is well established at Rolls-Royce. A model to predict the effects of roughness has been incorporated into CFDS and heat transfer levels have been calculated for both hydraulically smooth and transitionally rough surfaces. The roughness influences the calculations in two ways; first the mix

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9

Володин, Ю. Г., О. П. Марфина, Ю. И. Матвеев, Н. В. Гречко, and И. Р. Салахов. "Experimental study of heat dissipation in physical model of combustion chamber of gas-turbine engine at its start." MORSKIE INTELLEKTUAL`NYE TEHNOLOGII)</msg> 1, no. 3(65) (2024): 125–30. http://dx.doi.org/10.37220/mit.2024.65.3.032.

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Статья посвящена изучению пускового режима газотурбинного двигателя, относящегося к переходным или нестационарным режимам, в которых за короткий промежуток времени увеличивается температура рабочего тела и, как следствие, в целом изменяется вся ситуация, связанная с теплообменом. В литературных источниках практически отсутствует информация об экспериментальных исследованиях высоко динамичных нестационарных апериодических процессов. Эксперимент выполнен на разомкнутом газодинамическом контуре с электродуговым подогревом протекающего газового потока. В качестве физической модели использована тон

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10

Zhuravlev, V. S., and T. V. Sydorenko. "About the titanium foil using in the brazed construction of small windows for the transmission of radiant energy." Uspihi materialoznavstva 2021, no. 2 (2021): 101–6. http://dx.doi.org/10.15407/materials2021.02.101.

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The aim of this work was to miniaturize the design of a brazed joint of a thin non-metallic disk with a hollow thin-walled metal cylinder for operation as part of a vacuum device in a wide temperature range. For brazing a non-metallic disk with a glass tube-shaped device body, when choosing a metal filler, the fragility of glass, its low mechanical strength in bending and tensile and a lower thermal coefficient of linear expansion than metal fillers must be taken into account. Therefore, the use of low-temperature plastic solders based on tin, indium, lead etc., which are alloyed with titanium

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11

Вишнепольский, Евгений Валериевич, Дмитрий Викторович Павленко та Ярослав Викторович Двирнык. "ПРОГНОЗИРУЕМЫЕ ЭФФЕКТЫ УПРОЧНЕНИЯ АЛМАЗНЫМ ВЫГЛАЖИВАНИЕМ ДЕТАЛЕЙ ПОЛУЧЕННЫХ С ПОМОЩЬЮ СЕЛЕКТИВНОГО ЛАЗЕРНОГО СПЕКАНИЯ". Aerospace technic and technology, № 7 (31 серпня 2020): 73–82. http://dx.doi.org/10.32620/aktt.2020.7.11.

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The analysis of the possibility of expanding the scope of selective laser sintering technology has been made for the production of parts of short-range gas turbine aircraft engines due to the strengthening of stress concentration points by local plastic deformation by diamond smoothing. The technical, economic, and social effects of the application of this technology have been considered.The stress-strain state of complex-shaped thin-walled parts such as a disk and a monowheel of a short-life aircraft engine during their manufacture according to the traditional techniques from the compact mate

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12

Kim, Daejong, Jeongpill Ki, Youngcheol Kim, and Kookyoung Ahn. "Extended Three-Dimensional Thermo-Hydrodynamic Model of Radial Foil Bearing: Case Studies on Thermal Behaviors and Dynamic Characteristics in Gas Turbine Simulator." Journal of Engineering for Gas Turbines and Power 134, no. 5 (2012). http://dx.doi.org/10.1115/1.4005215.

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Environment-friendly microturbomachinery has its broad current and future applications in fuel cells, power generation, oil-free industrial blowers and compressors, small aero propulsions engines for missiles and small aircrafts, automotive turbo chargers, etc. Air foil bearings (AFBs) have been one of the popular subjects in recent years due to ever-growing interests in the environment-friendly oil-free turbomachinery. AFBs have many noticeable attractive features compared to conventional rigid-walled air/gas bearings such as improved damping and tolerance to minor shaft misalignment and exte

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13

San Andrés, Luis, José Baker, and Adolfo Delgado. "Measurements of Leakage and Power Loss in a Hybrid Brush Seal." Journal of Engineering for Gas Turbines and Power 131, no. 1 (2008). http://dx.doi.org/10.1115/1.2967497.

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Simplicity, low cost, and easy replacement make labyrinth seals the primary seal type in gas turbines. However, excessive leakage and potential for rotordynamic instability are well known issues. Brush seals effectively control leakage in air breathing engines, albeit only applied for relatively low pressure differentials. Hybrid brush seals (HBSs) are an alternative to resolve poor reliability resulting from bristle tip wear while also allowing for reverse rotation operation. The novel configuration incorporates pads contacting the shaft, which under rotor spinning lifts off due to the genera

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14

Pankaj Thakur, Dr, Jatinder Kaur, and Satya Bir Singh. "Thermal creep transition stresses and strain rates in a circular disc with shaft having variable density." Engineering Computations 33, no. 3 (2016). http://dx.doi.org/10.1108/ec-05-2015-0110.

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Purpose The purpose of this paper is to present study of thermal creep stresses and strain rates in a circular disc with shaft having variable density by using Seth’s transition theory. Design/methodology/approach Seth’s transition theory is applied to the problem of thermal creep transition stresses and strain rates in a thin rotating disc with shaft having variable density by finite deformation. Neither the yield criterion nor the associated flow rule is assumed here. The results obtained here are applicable to compressible materials. If the additional condition of incompressibility is impos

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15

Dunn, Michael, and Randall Mathison. "History of Short-Duration Measurement Programs Related to Gas Turbine Heat Transfer, Aerodynamics, and Aeroperformance at Calspan and The Ohio State University." Journal of Turbomachinery 136, no. 4 (2013). http://dx.doi.org/10.1115/1.4024898.

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Short-duration facilities have been used for the past 35 years to obtain measurements of heat transfer, aerodynamic loading, vibratory response, film-cooling influence, purge flow migration, and aeroperformance for full-stage, high-pressure turbines operating at design-corrected conditions of flow function, corrected speed, and stage pressure ratio. This paper traces the development of experimental techniques now in use at The Ohio State University (OSU) Gas Turbine Laboratory (GTL) from initial work in this area at the Cornell Aeronautical Laboratory (CAL, later to become Calspan) from 1975 t

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