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Relevant bibliographies by topics / Aero engine casings

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Academic literature on the topic 'Aero engine casings'

Author: Grafiati

Published: 4 June 2021

Last updated: 13 February 2022

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Journal articles on the topic "Aero engine casings"

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Zhou, Nan, and Xu Liu. "Feature-based automatic NC programming for aero-engine casings." Proceedings of the Institution of Mechanical Engineers, Part B: Journal of Engineering Manufacture 233, no. 4 (April 28, 2018): 1289–301. http://dx.doi.org/10.1177/0954405418769949.

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Traditional numerical control (NC) programming methods based on commercial computer-aided manufacturing systems usually require a large number of manual interactions with high-skilled experience, which not only results in low efficiency but also unstable machining quality. Especially since the structural complexity and machining requirements keep increasing, the NC programming is becoming a bottleneck problem in machining complex parts like aero-engine casings. This article proposes a feature-based automatic NC programming approach for aero-engine casings. A machining feature classification towards the geometric and machining characteristics of aero-engine casings is given. Then, a feature-based method to extract machining regions by considering the alternatives in selecting turning or milling operations is discussed. After the construction of machining operations, an undercut region detection method is also presented to evaluate the interim machining effects reasoned by each individual machining operation for excessive cutting avoidance. By implementing the proposed approach, a feature-based NC programming system is developed on a commercial computer-aided manufacturing platform and a real aero-engine casing is chosen to demonstrate the feasibility of the proposed approach.

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Beaudoin, Marc-Antoine, and Kamran Behdinan. "Analytical lump model for the nonlinear dynamic response of bolted flanges in aero-engine casings." Mechanical Systems and Signal Processing 115 (January 2019): 14–28. http://dx.doi.org/10.1016/j.ymssp.2018.05.056.

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Zhou, Xu, Dinghua Zhang, Ming Luo, and Baohai Wu. "Chatter stability prediction in four-axis milling of aero-engine casings with bull-nose end mill." Chinese Journal of Aeronautics 28, no. 6 (December 2015): 1766–73. http://dx.doi.org/10.1016/j.cja.2015.06.001.

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Djilali, Kaid-Ameur, and Mohamed Serrier. "Experimental Method of Tribological Modelling of Different Coatings of Stainless Steel." Mechanics and Mechanical Engineering 22, no. 4 (September 2, 2020): 1273–86. http://dx.doi.org/10.2478/mme-2018-0098.

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AbstractFretting wear is a unique form of material degradation caused by small amplitude oscillatory relative motion of two surfaces in contact. Fretting wear is typically encountered at relative displacements of less than 300 μm and occurs in either a gross slip regime [1] (where there is slip displacement across the whole contact), or a partial slip regime (where there are parts of the contact where no slip displacement occurs). Fretting wear is experienced within a wide range of industrial sectors, [2] including aero engine couplings, locomotive axles and nuclear fuel casings [3]. Under higher loads and smaller displacement amplitudes, the contact will be within the partial slip regime, often resulting in fretting fatigue where the dominant damage mode is a reduction in fatigue life [4]. Friction is a very common phenomenon in daily life and industry, which is governed by the processes occurring in the thin surfaces layers of bodies in moving contact. The simple and fruitful idea used in studies of friction is that there are two main non-interacting components of friction, namely, adhesion and deformation [5, 6].

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Fois, N., M. Watson, and MB Marshall. "The influence of material properties on the wear of abradable materials." Proceedings of the Institution of Mechanical Engineers, Part J: Journal of Engineering Tribology 231, no. 2 (August 5, 2016): 240–53. http://dx.doi.org/10.1177/1350650116649528.

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In aero-engines it is possible for the blades of the compressor, turbine or fan to incur into their casings. At these interfaces a lining of composite abradable material is used to limit damage to components and thereby sustain the efficiency and longevity of the engine as a whole. These composite materials must have good abradability and erosion resistance. Previously, the wear mechanisms at the contact between the blade and the coating have been characterised using stroboscopic imaging and force measurement on a scaled test-rig platform. This work is focused on the characterisation of the wear mechanism for two different hardnesses of abradable lining. The established stroboscopic imaging technique and contact force measurements are combined with sectioning of the abradable material in order to analyse the material’s response during the tests. A measure of the thermal properties and the resulting temperature of the linings during the test have also been made to further understand the effect of coating hardness. The wear mechanism, material response, contact force and thermal properties of the coating have been used to characterise the different material behaviour with different hardness. At low incursion rates, with a soft coating, the blade tip becomes worn after an initial adhesive transfer from the coating. Post-test sectioning showed blade material and significant compaction present in the coating. The harder coating produced adhesion on the blade tip with solidification observed in the coating. Thermal diffusivity measurements and modelling indicated that thermally driven wear observed was as a consequence of the increased number of boundaries between the metal and hBN phases present interrupting heat flow, leading to a concentration of surface heat. At higher incursion rates, the wear mechanism is more similar between the coatings and a cutting mechanism dominates producing negligible adhesion and blade wear.

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Dong, Ting Jian, Jin Chen, and Hua Peng Ding. "High-Speed Cutting Machining Simulation of Aero Engine Casing Hole." Advanced Materials Research 915-916 (April 2014): 1014–17. http://dx.doi.org/10.4028/www.scientific.net/amr.915-916.1014.

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For the high-speed machining aero engine casing hole, according to the principle of metal forming and the characteristic of metal cutting plane strain, with selecting some key physical factors of the cutter - chip contact friction and abrasion model, the Cartesian orthogonal cutting model of aero engine casing hole was established by using the Deform, a sort of finite element analysis software. With taking cutting temperature for preferred aim of the cutting parameters, select the appropriate cutting parameters, the aim of aero-engine casing high-speed (cutting speed up to 700m/min) cutting has been achieved by simulation, and the feasibility of the cutting process was researched and confirmed in theoretically by analyzing the cutting force, cutting temperature and tool wear condition.

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Dhopade, Priyanka, Benjamin Kirollos, Peter Ireland, and Leo Lewis. "A Comparison of Single-Entry and Multiple-Entry Casing Impingement Manifolds for Active Thermal Tip Clearance Control." International Journal of Turbomachinery, Propulsion and Power 6, no. 2 (May 14, 2021): 10. http://dx.doi.org/10.3390/ijtpp6020010.

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In this paper, we compare using computational fluid dynamics the aero-thermal performance of two candidate casing manifolds for supplying an impingement-actuated active tip clearance control system for an aero-engine high-pressure turbine. The two geometries are (a) single-entry: an annular manifold fed at one circumferential location; (b) multiple-entry: a casing manifold split into four annular sectors, with each sector supplied separately from an annular ring main. Both the single-entry and multiple-entry systems analysed in this paper are idealised versions of active clearance control systems in current production engines. Aero-thermal performance is quantitatively assessed on the basis of the heat transfer coefficient distribution, driving temperature difference for heat transfer between the jet and casing wall and total pressure loss within the high-pressure turbine active clearance control system. We predict that the mean heat transfer coefficient (defined with respect to the inlet temperature and local wall temperature) of the single-entry active clearance control system is 77% greater than the multiple-entry system, primarily because the coolant in the multiple-entry case picks up approximately 40 K of temperature from the ring main walls, and secondarily because the average jet Reynolds number of impingement holes in the single-entry system is 1.2 times greater than in the multiple-entry system. The multiple-entry system exhibits many local hot and cold spots, depending on the position of the transfer boxes, while the single-entry case has a more predictable aero-thermal field across the system. The multiple-entry feed system uses an average of 20% of the total available pressure drop, while the feed system for the single-entry geometry uses only 2% of the total available pressure drop. From the aero-thermal results of this computational study, and in consideration of holistic aero-engine design factors, we conclude that a single-entry system is closer to an optimal solution than a multiple-entry system.

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Ma, Yingqun, Qingjun Zhao, Kai Zhang, Meng Xu, and Wei Zhao. "Effects of mount positions on vibrational energy flow transmission characteristics in aero-engine casing structures." Journal of Low Frequency Noise, Vibration and Active Control 39, no. 2 (May 17, 2019): 313–26. http://dx.doi.org/10.1177/1461348419845506.

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The main goal of the study is to apply the structural intensity method to analyze the effects of positions of the main-mount and the sub-mount on the vibrational energy flow transmission characteristics in aero-engine casing structures, so as to attenuate the vibration of the casing and the whole aero-engine. Structural intensity method, indicating magnitude and direction of the vibrational energy flow, is a powerful tool to study vibration problems from the perspective of energy. In this paper, a casing-support-rotor coupling model subjected to the rotor unbalanced forces is established by the finite element method. Formulations of the structural intensity of a shell element and the structural intensity streamline are given. A simulation system consisting of the finite element tool and the in-house program is developed to carry out forced vibration analysis and structural intensity calculation. The structural intensity field of the casing is visualized in the forms of vector diagram and streamline representation. The vibrational energy flow behaviors of the casing at the rotor design rotating speed are analyzed, and the vibrational energy flow transmission characteristics of the casing with different axial positions of the main-mount and the sub-mount are investigated. Moreover, some measures to attenuate the vibration of the casing are obtained from the numerical results, and their effectiveness is verified in the frequency domain and the time domain. The results shed new light on the effects of the mount positions on the vibration energy transmission behaviors of the casing structure. The structural intensity method is a more advanced tool for solving vibration problems in engineering. Furthermore, it may provide some guidance for the vibration attenuation of the casing and the whole aero-engine.

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SUN, Xiaofeng, Xu DONG, and Dakun SUN. "Recent development of casing treatments for aero-engine compressors." Chinese Journal of Aeronautics 32, no. 1 (January 2019): 1–36. http://dx.doi.org/10.1016/j.cja.2018.11.005.

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Wang, Nanfei, Chao Liu, and Dongxiang Jiang. "Prediction of transient vibration response of dual-rotor-blade-casing system with blade off." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 14 (April 4, 2019): 5164–76. http://dx.doi.org/10.1177/0954410019839884.

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Fan blade off occurring in a running rotor of the turbofan engine dual-rotor system will cause a sudden unbalance and inertia asymmetry, which results in large impact load and consequently induces the rubbing between blade and casing. In order to reveal the transient dynamic response characteristics of actual aero-engine when fan blade off event occurs, the dynamic model of dual-rotor-blade-casing system is developed, in which the distribution characteristics of the stiffness and mass, the load transfer, and the coupling effects of dual-rotor and casing are included. Considering several excitations caused by blade off, the physical process and mechanical characteristics of the fan blade off event are described qualitatively. Considering that only the casing acceleration signal can be used for condition monitoring in actual aero-engine, the transient response including rotor vibration displacement and casing vibration acceleration during the instantaneous status are obtained. Due to the time-varying and highly nonlinear characteristics of vibration responses, frequency slice wavelet transform is employed to isolate the vibration signal features. The results show that the impact load induced by the sudden imbalance causes significant increase of vibration amplitude. The rubbing action between blade and rotor will impose constraint effects on the rotor, which decreases the transient vibration amplitude. The inertia asymmetry has a big impact on the transient response. The vibration characteristics of casing acceleration under blade off are similar to those of rotor displacement, while casing acceleration response attenuates to stable value faster and is more sensitive to high-frequency components of vibration.

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Dissertations / Theses on the topic "Aero engine casings"

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Featherston, Carol. "Buckling of flat plates and cylindrical panels under complex load cases." Thesis, University of Oxford, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.390476.

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Books on the topic "Aero engine casings"

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Panigrahi, Shashi Kanta, and Niranjan Sarangi. Aero Engine Combustor Casing. Taylor & Francis Group, 2020.

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Aero Engine Combustor Casing: Experimental Design and Fatigue Studies. Taylor & Francis Group, 2017.

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Book chapters on the topic "Aero engine casings"

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Di Maio, D., G. Ramakrishnan, and Y. Rajasagaran. "Experimental Model Validation of an Aero-Engine Casing Assembly." In Model Validation and Uncertainty Quantification, Volume 3, 339–47. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-54858-6_34.

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Zang, Chaoping, Shuangchao Ma, and M. I. Friswell. "Finite Element Model Updating of an Assembled Aero-Engine Casing." In Topics in Model Validation and Uncertainty Quantification, Volume 5, 199–212. New York, NY: Springer New York, 2013. http://dx.doi.org/10.1007/978-1-4614-6564-5_20.

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Xue, Jing, Min Huang, Jun Yi, and Xuejun Liu. "Reliability modeling and optimization of the spray process for seal coatings on the aero-engine compressor casing." In Risk, Reliability and Safety: Innovating Theory and Practice, 1728–35. Taylor & Francis Group, 6000 Broken Sound Parkway NW, Suite 300, Boca Raton, FL 33487-2742: CRC Press, 2016. http://dx.doi.org/10.1201/9781315374987-261.

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"Introduction." In Aero Engine Combustor Casing, 1–22. Boca Raton : Taylor & Francis, a CRC title, part of the Taylor & Francis imprint, a member of the Taylor & Francis Group, the academic division of T&F Informa, plc, [2017]: CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-1.

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"References." In Aero Engine Combustor Casing, 143–51. Taylor & Francis Group, 6000 Broken Sound Parkway NW, Suite 300, Boca Raton, FL 33487-2742: CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-10.

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"Index." In Aero Engine Combustor Casing, 153–56. Taylor & Francis Group, 6000 Broken Sound Parkway NW, Suite 300, Boca Raton, FL 33487-2742: CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-11.

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"Fatigue Design Philosophy of an Aero Engine Combustor Casing." In Aero Engine Combustor Casing, 23–52. Boca Raton : Taylor & Francis, a CRC title, part of the Taylor & Francis imprint, a member of the Taylor & Francis Group, the academic division of T&F Informa, plc, [2017]: CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-2.

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"Development of Test Facility and Test Setup." In Aero Engine Combustor Casing, 53–68. Boca Raton : Taylor & Francis, a CRC title, part of the Taylor & Francis imprint, a member of the Taylor & Francis Group, the academic division of T&F Informa, plc, [2017]: CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-3.

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"Manufacturing of an Aero Engine Combustor Casing, the Experimental Evaluation of Its Fatigue Life, and Correlation with Numerical Results." In Aero Engine Combustor Casing, 69–100. Boca Raton : Taylor & Francis, a CRC title, part of the Taylor & Francis imprint, a member of the Taylor & Francis Group, the academic division of T&F Informa, plc, [2017]: CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-4.

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"Reassessment of Fatigue Life of the Modified Combustor Casing." In Aero Engine Combustor Casing, 101–12. Boca Raton : Taylor & Francis, a CRC title, part of the Taylor & Francis imprint, a member of the Taylor & Francis Group, the academic division of T&F Informa, plc, [2017]: CRC Press, 2017. http://dx.doi.org/10.1201/9781315116754-5.

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Conference papers on the topic "Aero engine casings"

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Mir-Haidari, Seyed-Ehsan, and Kamran Behdinan. "Aero-engine Casings Modal Characteristic Assessment using an Efficient and Novel Modal Assurance Criterion Methodology." In Canadian Society for Mechanical Engineering International Congress (2020 : Charlottetown, PE). Charlottetown, P.E.I.: University of Prince Edward Island. Robertson Library, 2020. http://dx.doi.org/10.32393/csme.2020.118.

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Xiao, Jiaguangyi, Yong Chen, Jie Tian, Hua Ouyang, and Anjenq Wang. "Analysis of Composite Blade/Casing Rub Stability Through Delayed Differential Equations." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91333.

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Abstract To improve aerodynamic efficiencies, the clearances between blades and casings are becoming smaller and smaller in the aero-engine industry, which might lead to the interactions between these components. These unexpected interactions are known as the so called blade/casing rubs. Abradable materials are implemented on the inner surface of the casings to reduce the potential damages caused by it. However, failures may still arise from blade/casing rubs according to experimental investigations and actual accidents. In this paper, a reduced-order delayed differential equations are used to simplify the rubbing process between composite blade and casing. It is assumed that the removal of the abradable material in blade/casing rubbing process shares a resemblance with machine tool chatters encountered in machining. The delayed differential equations are established with centrifugal stiffness and the impacts of stacking sequences on the blade damping taking into consideration. Semi-Discretization Method (SDM) is used to study the stabilities of the simplified system, which is verified by Cluster Treatment of Characteristic Roots (CTCR) and direct integrations. The results show that the stacking sequences, rub positions, blade damping and stiffness could have much impact on the relatively dangerous interaction regimes. With the help of this method, one can assist the design processes of the composite blade-casing interface in initial aero-engine structural designs.

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Schönleitner, F., T. Selic, C. Schitter, F. Heitmeir, and A. Marn. "Experimental Investigation of the Upstream Effect of Different Low Pressure Turbine Exit Guide Vane Designs on Rotor Blade Vibration." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56067.

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Exit guide vanes of turbine exit casings are designed to meet aerodynamic, structural and acoustic criteria. New low pressure turbine architectures of aero engines try to optimize components weight in order to decrease the fuel consumption and reduce noise emissions. For this purpose different designs of turbine exit guide vanes (TEGV) exist which vary geometry as well as the number of vanes in the casing. In the subsonic test turbine facility at the Institute for Thermal Turbomachinery and Machine Dynamics of Graz University of Technology, which represents a 1 ½ low pressure turbine stage, the upstream effect of these innovative turbine exit casings (TEC) designs is under investigation. Up to now the influence of the turbine exit casing in relation to the aerodynamic vibration excitation of the rotor blading is not well known. For rotor blade vibration measurements a telemetry system in combination with strain gauges is applied. The present paper is a report of blade vibration measurements within a rotating system in the area of low pressure turbines under engine relevant operating conditions. Within the test phase different turbine exit casings are under investigation at two different operating points (OP). These turbine exit casings represent different design goals, e.g. aerodynamically optimization was performed to reduce losses at the aero design point or an acoustically optimization was done to reduce noise emission at the operating point approach. All these different design intents lead to a changed upstream effect, thus changing rotor blade vibrations. To identify parameters affecting blade vibration attention is paid to aerodynamic measurements as well. Selected results of steady and unsteady flow field measurements are analyzed to draw conclusions. The upstream effect of different turbine exit casings can be quantified at OP1. Depending on the vane number both the potential effect of the TEGV increase and the upstream effect as well. Aerodynamic as well as acoustic improvements as wanted with H-TEC and inverse-cut-off TEC lead to unfavorable conditions and higher blade loading in comparison to the referenced TEC. OP2 provides additional information of downstream effects. Due to the stator vane number the rotor blading is excited in its 4th eigenfrequency. The comparison between all investigated turbine exit casings with respect to the referenced configuration provides a basis for numerical code validation and future developments.

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Hong, Jie, Xueqing He, Dayi Zhang, and Yanhong Ma. "Vibration Isolation Design for Periodical Stiffened Shells by the Wave Finite Element Method." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-70029.

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Thin plates and shells are widely used to reduce the weight in modern mechanical systems, in particularly for the aeronautic and astronautical machineries. These thin structures can result in intensive modes, and lead to the difficulty on the suppression of vibration. The excessive vibration of casing can not only lead to the failure itself but also has a significant influence on the related external pipelines and other attachments which could cause the fatigue failure for the aero-engine casings. A proper method is needed to investigate the dynamic characteristics for these casings, and to be potentially further used for the vibration isolation design. Periodic structure has received a great deal of attentions for its band gap characteristics. Sound and other vibration can be forbidden to propagate in its band gap. With regard to the applications in aero-engines, the article provides one probable vibration isolation method for the stiffened plates and shells with high strength-to-weight ratio and with periodic configuration characteristics. The vibration characteristics of the stiffened shell are usually difficult to be acquired, and there is neither an analytical solution for the complicated stiffeners configuration. Therefore, a Wave finite element method (FEM) based on the wave theory and finite element method, which can solve the dynamic response and band gap characteristics of casings with wide frequency band is presented. Taking the characteristics of the curvature into account, it is proposed for how to confirm the periodic boundaries of the shells. Moreover, the finite element model built by ANSYS is combined with MATLAB program, and the validity of Wave FEM is proved in shell with different boundaries including free-clamped boundary and free-free boundary. The results reveal that with the increase of stiffeners’ width, wider frequency range and larger attenuating ability appear in the vibration band gap. While with the increase of stiffeners’ thickness, neither the variety of the attenuating capability nor of the frequency range of band gaps is monotone. And the local resonance of stiffeners is obvious, the corresponding band gaps’ contribution to the whole system is little. Moreover, three typical configurations-hexagonal, square and triangular are considered. The configurations of stiffeners have distinct characteristics on the dispersion relation, if the weight problems are not taken into account, the square honeycomb is better than the others.

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van Paridon, Andrew, Andrew Dann, Peter Ireland, and Marko Bacic. "Design and Development of a Full-Scale Generic Transient Heat Transfer Facility (THTF) for Air System Validation." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42391.

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This paper describes the design and development of a major new facility capable of reproducing flow conditions for large civil aero engine turbine and compressor segment cavities. The facility reproduces in 3-D, typical secondary air system cruise temperatures, pressures and mass flows. The facility allows better understanding of the circumferential heat transfer effects of air system flows on turbine and compressor casings, as these have a significant influence on both steady-state and transient blade tip clearance behavior. Different air system architectural solutions are considered and 1-D transient air system modelling is used to design architecture to ensure that they meet tight performance requirements in terms of allowable pressure and temperature ripples when subject to fast switching of flows. An explanation of the design of the double-skin pressure vessel using 2-D axisymmetric thermo-mechanical analysis to understand the life-limiting features of the design is discussed. Finally we conclude the paper with some experimental results from rig commissioning and the use of these results in the determination of engine casing transients is discussed.

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Murty Pilli, Narayana, Lakshman Kasina, Kondaiah Bommisetty, Sreenivas Karri, and Kotur Srinivasan Raghavan. "A Study on the Nonlinear Dynamic Characteristics of Gas Turbine Engine Components." In ASME 2017 Gas Turbine India Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gtindia2017-4733.

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Rotating as well as static components of aero engines such as rotors and casings must be capable of withstanding vibrations which arises from various engine order excitations. HCF is attributed as one of the major failures due to its high crack propagation rate. The tolerances to vibration have become a key point to avoid resonance in operating range. Analytical predictions of individual components gives better accuracy and good agreement with test data. However, when the components are assembled, the accuracy of analyses can considerably depreciate since models describing stiffness and friction properties of joints are linearized. In such conditions proper predictions of dynamic response becomes difficult and may lead to under prediction or over prediction of dynamic response. A nonlinear analysis is required to study the influence of joints flexibility on dynamic response. In this paper different nonlinear joint models are investigated to assess the dynamic behavior of the contact interface in terms of slipping and sticking contact parameters. The study shows significant changes over dynamic characteristics when compared to linear analysis. From this study, it is evident that nonlinear behavior of the contact in dynamic analysis phase due to slip and separation plays vital role over the dynamic characteristics of the component. This study emphasizes to consider physical behavior of joints in dynamic analysis to avoid catastrophic HCF failures.

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Chana, K. S., and B. Haller. "Novel Turbine Rotor Shroud Film-Cooling Design and Validation: Part 1." In ASME Turbo Expo 2009: Power for Land, Sea, and Air. ASMEDC, 2009. http://dx.doi.org/10.1115/gt2009-60242.

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This paper is part one of a two part paper which considers a shroud film-cooling system designed using a two-dimensional approach. Heat transfer to rotor-casings has reached levels that are causing in-service difficulties to be experienced. Future designs are likely to need to employ film-cooling of some form. There is currently very little information available for film-cooling on shroudless turbine rotor-casing liners. Heat transfer literature on uncooled configurations is not extensive and in particular, spatially-detailed, time-accurate data are rare. This paper describes the aero-thermodynamic design and validation of a rotor casing film-cooling system for a transonic, high-pressure shroudless turbine stage. The design was carried out using a boundary layer code with the film-cooling hole geometry representative of an engine configuration and, has been subjected to mechanical constraints similar to those for an engine component. The design consists of two double rows of cooling holes and two ‘cooling-hole’ shape configurations, cylindrical and fan shaped. The design was tested in the QinetiQ short duration turbine test facility (TTF). Measurements taken include casing heat transfer using thin film gauges and stage exit total pressure, Mach number and flow angle using a three-hole pressure probe. Results showed that while the cooling produced a reduction in the heat transfer rate close to the injection point, the film was stripped off the casing and entrained in nozzle guide vane secondary and rotor overtip flow, where it was transported spanwise towards the hub in the rotor passage. Using the results obtained from this deign a second cooling design was carried out, using a three-dimensional approach this gave significantly better cooling performance. The thee-dimensional design and validation is reported in GT2009-60246 as part 2 of this paper.

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Gupta, Suresh. "Erosion Characteristics of Ceramic Particulate and Whisker Reinforced Aluminum Composites." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-369.

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Advanced composite materials are one of the key enabling technologies for achieving the planned revolutionary improvements in the next generation of aero gas turbine engines. For example the thrust to weight ratio of advanced military engines is targeted to double (to 20:1) within the next 10 to 15 years. A number of families of advanced composites are being developed, and metal matrix composites is one significant member of these. These can be either ceramic fiber or ceramic particulate/whiskers embedded in matrixes of aluminum, titanium or superalloys. Silicon carbide particulate/whisker reinforced aluminum has been under consideration for the cold section of front end engine components such as compressor blades, compressor stator vanes and casings. One potentially serious problem anticipated in using these composites for such application is its behavior in particulate erosion, as may happen in sandy environments and runways. This paper describes the test program undertaken to study this problem, and discusses the results obtained. It was found that the erosion rate of such composites can be considerably higher than that of non-reinforced aluminum alloys. Further, the characteristic erosion behavior is modified significantly. Also identified were new mechanisms of material removal coming into play. These are also discussed.

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Benito, Diego, Jeff Dixon, and Paul Metherell. "3D Thermo-Mechanical Modelling Method to Predict Compressor Local Tip Running Clearances." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-50780.

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This paper presents a 3D thermo-mechanical modelling method to calculate compressor local tip running clearances. The method requires a solid geometry representation of the compressor casings and main engine structures, including local geometry features such as thrust lugs, gearbox, sump, offtake bosses and struts. The finite element model is capable of predicting asymmetric temperature and displacement distributions for transient and steady-state conditions as a result of thermal, pressure and mechanical loads (e.g. thrust, gas torques, gravity, gusts, etc). This methodology has been applied to calculate local tip clearances on the intermediate pressure compressor of a civil aero-engine. The results from the 3D solid model have been compared to those obtained with more conventional analysis tools (i.e. 2D axisymmetric thermo-mechanical models and 3D isothermal shell and beam models) in order to build confidence in the new methodology. Local tip running clearances were measured on the intermediate pressure compressor by means of capacitance probes. Measured local closures for a typical square cycle including a low power idle phase and high power max take-off phase have been compared to predicted local closures to establish the validity of the new methodology.

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Ferrand, Antoine, Marc Bellenoue, Yves Bertin, Radu Cirligeanu, Patrick Marconi, and Fabien Mercier-Calvairac. "High Fidelity Modeling of the Acceleration of a Turboshaft Engine During a Restart." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76654.

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In order to decrease the fuel consumption, a new flight mode is being considered for twin-engine helicopters, in which one engine is put into sleeping mode (a mode in which the gas generator is kept at a stabilized, sub-idle speed by means of an electric motor, with no combustion), while the remaining engine operates at nominal load. The restart of the engine in sleeping mode is therefore deemed critical for safety reasons. This efficient new flight mode has raised the interest in the modeling of the restart of a turboshaft engine. In this context, the initial conditions of the simulations are better known relative to a ground start, in particular the air flow through the gas generator is constant, the fuel and oil system states are known and temperatures of the casings are equal to ambient. During the restart phase of the engine, the gas generator speed is kept at constant speed until the light-up is detected by a rise in inter-turbine temperature, then the starter torque increases, accelerating the engine towards idle speed. In this paper, the modeling of the acceleration of the gas generator from light-up to idle and above idle speeds is presented. Details on the light-up process are not addressed here. The study is based on the high-fidelity aero-thermodynamic restart model that is currently being developed for a 2000 horse power, free turbine turboshaft. In this case, the term high-fidelity refers not only to the modeling of the flow path components but it also includes all the subsystems, secondary air flows and controls with a high level of detail. The physical phenomena governing the acceleration of the turboshaft engine following a restart — mainly the transient evolution of the combustion efficiency and the power loss by heat soakage — are discussed in this paper and modeling solutions are presented. The results of the simulations are compared to engine test data, highlighting that the studied phenomena have an impact on the acceleration of the turboshaft engine and that the model is able to correctly predict acceleration trends.

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