Relevant bibliographies by topics / Aerospace gas turbines

Contents

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

Academic literature on the topic 'Aerospace gas turbines'

Author: Grafiati
Published: 4 June 2021
Last updated: 16 February 2022

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Journal articles on the topic "Aerospace gas turbines"

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Asgari, Hamid, Mohsen Fathi Jegarkandi, XiaoQi Chen, and Raazesh Sainudiin. "Design of conventional and neural network based controllers for a single-shaft gas turbine." Aircraft Engineering and Aerospace Technology 89, no. 1 (January 3, 2017): 52–65. http://dx.doi.org/10.1108/aeat-11-2014-0187.

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Purpose The purpose of this paper is to develop and compare conventional and neural network-based controllers for gas turbines. Design/methodology/approach Design of two different controllers is considered. These controllers consist of a NARMA-L2 which is an artificial neural network-based nonlinear autoregressive moving average (NARMA) controller with feedback linearization, and a conventional proportional-integrator-derivative (PID) controller for a low-power aero gas turbine. They are briefly described and their parameters are adjusted and tuned in Simulink-MATLAB environment according to the requirement of the gas turbine system and the control objectives. For this purpose, Simulink and neural network-based modelling is used. Performances of the controllers are explored and compared on the base of design criteria and performance indices. Findings It is shown that NARMA-L2, as a neural network-based controller, has a superior performance to PID controller. Practical implications This study aims at using artificial intelligence in gas turbine control systems. Originality/value This paper provides a novel methodology for control of gas turbines.
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Brady, C. O., and D. L. Luck. "The Increased Use of Gas Turbines as Commercial Marine Engines." Journal of Engineering for Gas Turbines and Power 116, no. 2 (April 1, 1994): 428–33. http://dx.doi.org/10.1115/1.2906839.

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Over the last three decades, aeroderivative gas turbines have become established naval ship propulsion engines, but use in the commercial marine field has been more limited. Today, aeroderivative gas turbines are being increasingly utilized as commercial marine engines. The primary reason for the increased use of gas turbines is discussed and several recent GE aeroderivative gas turbine commercial marine applications are described with particular aspects of the gas turbine engine installations detailed. Finally, the potential for future commercial marine aeroderivative gas turbine applications is presented.
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Fersini, Maurizio, R. Bianco, L. De Lorenzis, Antonio Licciulli, G. Pasquero, and G. Zanon. "Thermo-Structural Analysis of Ceramic Vanes for Gas Turbines." Advances in Science and Technology 45 (October 2006): 1759–64. http://dx.doi.org/10.4028/www.scientific.net/ast.45.1759.

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Advanced structural ceramics such as Hot Pressed Silicon Nitride (HPSN) and Reaction Bonded Silicon Carbide (RBSC), thanks to their low density (3.1 ÷ 3.4 gr/cm3) and to their thermostructural properties, are interesting candidates for aerospace applications. This research investigates the feasibility of employing such monolithic advanced ceramics for the production of turbine vanes for aerospace applications, by means of a finite element analysis. A parametric study is performed to analyse the influence of the coefficient of thermal expansion, the specific heat, the thermal conductivity, and the Weibull modulus on structural stability, heat transfer properties and thermomechanical stresses under take-off and flying conditions. A nodal point that is evidenced is the high intensity of thermal stresses on the vane, both on steady state and in transient conditions. In order to reduce such stresses various simulations have been carried out varying geometrical parameters such as the wall thickness. Several open questions are evidenced and guidelines are drawn for the design and production of ceramic vanes for gas turbines.
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Bhargava, R., M. Bianchi, A. Peretto, and P. R. Spina. "A Feasibility Study of Existing Gas Turbines for Recuperated, Intercooled, and Reheat Cycle." Journal of Engineering for Gas Turbines and Power 126, no. 3 (July 1, 2004): 531–44. http://dx.doi.org/10.1115/1.1707033.

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In the present paper, a comprehensive and simple in application design methodology to obtain a gas turbine working on recuperated, intercooled, and reheat cycle utilizing existing gas turbines is presented. Applications of the proposed design steps have been implemented on the three existing gas turbines with wide ranging design complexities. The results of evaluated aerothermodynamic performance for these existing gas turbines with the proposed modifications are presented and compared in this paper. Sample calculations of the analysis procedures discussed, including stage-by-stage analysis of the compressor and turbine sections of the modified gas turbines, have been also included. All the three modified gas turbines were found to have higher performance, with cycle efficiency increase of 9% to 26%, in comparison to their original values.
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Fatsis, Antonios. "Performance Enhancement of One and Two-Shaft Industrial Turboshaft Engines Topped With Wave Rotors." International Journal of Turbo & Jet-Engines 35, no. 2 (May 25, 2018): 137–47. http://dx.doi.org/10.1515/tjj-2016-0040.

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Abstract Wave rotors are rotating equipment designed to exchange energy between high and low enthalpy fluids by means of unsteady pressure waves. In turbomachinery, they can be used as topping devices to gas turbines aiming to improve performance. The integration of a wave rotor into a ground power unit is far more attractive than into an aeronautical application, since it is not accompanied by any inconvenience concerning the over-weight and extra dimensioning. Two are the most common types of ground industrial gas turbines: The one-shaft and the two-shaft engines. Cycle analysis for both types of gas turbine engines topped with a four-port wave rotor is calculated and their performance is compared to the performance of the baseline engine accordingly. It is concluded that important benefits are obtained in terms of specific work and specific fuel consumption, especially compared to baseline engines with low compressor pressure ratio and low turbine inlet temperature.
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Bander, F. "Multifuel Gas Turbine Propulsion for Naval Ships: Gas Turbine Cycles Implementing a Rotating Gasifier." Journal of Engineering for Gas Turbines and Power 107, no. 3 (July 1, 1985): 758–68. http://dx.doi.org/10.1115/1.3239798.

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The purpose of this paper is to investigate the possibilities of implementing a rotating gasifier to convert aero-derived gas turbines into multifuel ship propulsion units, thereby combining the advantages of lightweight and compact gas turbines with the multifuel characteristics of a rotating gasifier. Problems (and possible solutions) to be discussed are: (i) aerodynamic interaction between gas turbine and gasifier; (ii) attaining maximum energy productivity together with ease of control; (iii) corrosion and/or erosion of gas turbine components.
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Hung, W. S. Y. "Carbon Monoxide Emissions From Gas Turbines as Influenced by Ambient Temperature and Turbine Load." Journal of Engineering for Gas Turbines and Power 115, no. 3 (July 1, 1993): 588–93. http://dx.doi.org/10.1115/1.2906747.

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The emissions of carbon monoxide (CO) from gas turbines are typically below 100 ppmvd at 15 percent O2 at design full-load operating conditions. The use of water/ steam to reduce NOx emissions from gas turbines results in an increase in CO emissions from gas turbines. This is particularly true when increased rates of water/ steam injection are used to meet stringent NOx limits. Regulations limiting CO emissions from stationary gas turbines were first initiated in the late 1980s by the Federal Republic of Germany and the state of New Jersey in the United States. Since these regulations are silent on ambient and load corrections, these CO limits could be the limiting factor in the current development of dry low-NOx combustion systems by gas turbine manufacturers. In addition, since manufacturers are usually quite specific regarding the conditions for CO guarantees, a conflict for the gas turbine user, who is responsible for the permit application, is readily apparent. This paper attempts to characterize the CO emissions from gas turbines as a function of ambient temperature and turbine load. An ambient temperature correction equation for CO emissions, based on previous work, is presented. The intent is to provide more extensive information on CO emissions such that better defined CO limits can be adopted. Ultimately, this should help the combustion design engineers in developing improved dry low-emissions combustion systems for the gas turbine industry.
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Bianchi, M., G. Negri di Montenegro, A. Peretto, and P. R. Spina. "A Feasibility Study of Inverted Brayton Cycle for Gas Turbine Repowering." Journal of Engineering for Gas Turbines and Power 127, no. 3 (June 24, 2005): 599–605. http://dx.doi.org/10.1115/1.1765121.

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In the paper a feasibility study of inverted Brayton cycle (IBC) engines, for the repowering of existing gas turbines, is presented. The following main phases have been carried out: (i) identification of the more suitable gas turbines to be repowered by means of an IBC engine; (ii) designing of the IBC components. Once the IBC engines for the candidate gas turbines were designed, an analysis has been developed to check the possibility to match these engines with other gas turbines, similar to those for which the IBC engines have been designed. In all the analyzed cases the evaluated performance result only slightly worse than that obtainable by repowering the same gas turbine with IBC engines ad hoc designed.
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Bogomolov, E. N., and P. V. Kashcheeva. "Thermodynamic features of aircraft diagonal gas turbines." Russian Aeronautics (Iz VUZ) 52, no. 2 (June 2009): 250–54. http://dx.doi.org/10.3103/s1068799809020196.

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El Hadik, A. A. "The Impact of Atmospheric Conditions on Gas Turbine Performance." Journal of Engineering for Gas Turbines and Power 112, no. 4 (October 1, 1990): 590–96. http://dx.doi.org/10.1115/1.2906210.

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In a hot summer climate, as in Kuwait and other Arabian Gulf countries, the performance of a gas turbine deteriorates drastically during the high-temperature hours (up to 60°C in Kuwait). Power demand is the highest at these times. This necessitates an increase in installed gas turbine capacities to balance this deterioration. Gas turbines users are becoming aware of this problem as they depend more on gas turbines to satisfy their power needs and process heat for desalination due to the recent technical and economical development of gas turbines. This paper is devoted to studying the impact of atmospheric conditions, such as ambient temperature, pressure, and relative humidity on gas turbine performance. The reason for considering air pressures different from standard atmospheric pressure at the compressor inlet is the variation of this pressure with altitude. The results of this study can be generalized to include the cases of flights at high altitudes. A fully interactive computer program based on the derived governing equations is developed. The effects of typical variations of atmospheric conditions on power output and efficiency are considered. These include ambient temperature (range from −20 to 60°C), altitude (range from zero to 2000 m above sea level), and relative humidity (range from zero to 100 percent). The thermal efficiency and specific net work of a gas turbine were calculated at different values of maximum turbine inlet temperature (TIT) and variable environmental conditions. The value of TIT is a design factor that depends on the material specifications and the fuel/air ratio. Typical operating values of TIT in modern gas turbines were chosen for this study: 1000, 1200, 1400, and 1600 K. Both partial and full loads were considered in the analysis. Finally the calculated results were compared with actual gas turbine data supplied by manufacturers.
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Dissertations / Theses on the topic "Aerospace gas turbines"

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Moore, Gareth Edward. "Electro-mechanical interactions in aerospace gas turbines." Thesis, University of Nottingham, 2013. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.768249.

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The provision of electrical power on modern aircraft is a necessary and growing aspect of a gas turbine's function. The replacement of traditional pneumatic, hydraulic and mechanical systems with electrical equivalents means that electricity is now the dominant means of power distribution on aircraft. However, the electrical loads seen on aircraft present challenges, as they are time varying and are often non-linear. This is particularly true for loads such as radar. The aviation industry has adopted the term More Electric Aircraft (MEA) to describe the latest generation of aircraft with a high reliance on electrical power. There is potential for significant interaction between the transient variation of electrical loading and the gas turbine (both drive-train and engine core). Engine testing and initial simulation work support this view. Understanding of this phenomenon must now be furthered through modelling and testing. This thesis presents simulation models of a transmission system and generator interface, which provides a useful kernel for a modelled system to assess electro-mechanical interaction. This is extended to multi-domain simulation work through the successful interlinking of transmission, generator and an electrical load model. These models have been validated, at a domain level, against analytical expressions, and also as a complete electro-mechanical system against test data. To allow more control over test conditions, an electro-mechanical test rig is designed and constructed. The data from the test rig is analysed and compared to modelled results. This thesis also presents potential mitigation actions for avoiding unwanted electro-mechanical interactions during electrical load transients. A method of extracting transient mechanical torque information from a gas turbine's electrical generator's terminal quantities is included. At a system level, the simulation work in this thesis potentially enables the development of future designs with improved power systems integration throughout the entire airframe. High level control could allow optimisation of the power conversion process between gas turbine spool and electrical systems, with increased intelligence in the movement of power between components.
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Yen, Hsin-Yi. "NEW ANALYSIS AND DESIGN PROCEDURES FOR ENSURING GAS TURBINE BLADES AND ADHESIVE BONDED JOINTS STRUCTURAL INTEGRITY AND DURABILITY." [Columbus, Ohio] : Ohio State University, 2000. http://www.ohiolink.edu/etd/send-pdf.cgi?osu967666610.

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Thesis (Ph. D.)--Ohio State University, 2000.
Includes vita. Title from title page display. Abstract. Advisor: M.-H. Herman Shen, Dept. of Aerospace Engineering, Applied Mechanics, and Aviation. Includes bibliographical references (p. 152-154).
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Fletcher, Daniel Alden. "Internal cooling of turbine blades : the matrix cooling method." Thesis, University of Oxford, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.360259.

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Plewacki, Nicholas. "Modeling High Temperature Deposition in Gas Turbines." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1587714424017527.

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Cosher, Christopher R. "Detailed Analysis of Previous Data Relevant to Foreign Particle Ingestion by GasTurbine Engines and Application to Modern Engines." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1461152408.

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Libertowski, Nathan D. "Experimental Testing of Deposition Relevant to Turbine Cooling Geometries in order to Improve the OSU Deposition Model." The Ohio State University, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=osu1555063944642072.

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Pakmehr, Mehrdad. "Towards verifiable adaptive control of gas turbine engines." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/49025.

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This dissertation investigates the problem of developing verifiable stable control architectures for gas turbine engines. First, a nonlinear physics-based dynamic model of a twin spool turboshaft engine which drives a variable pitch propeller is developed. In this model, the dynamics of the engine are defined to be the two spool speeds, and the two control inputs to the system are fuel flow rate and prop pitch angle. Experimental results are used to verify the dynamic model of JetCat SPT5 turboshaft engine. Based on the experimental data, performance maps of the engine components including propeller, high pressure compressor, high pressure, and low pressure turbines are constructed. The engine numerical model is implemented using Matlab. Second, a stable gain scheduled controller is described and developed for a gas turbine engine that drives a variable pitch propeller. A stability proof is developed for a gain scheduled closed-loop system using global linearization and linear matrix inequality (LMI) techniques. Using convex optimization tools, a single quadratic Lyapunov function is computed for multiple linearizations near equilibrium and non-equilibrium points of the nonlinear closed-loop system. This approach guarantees stability of the closed-loop gas turbine engine system. To verify the stability of the closed-loop system on-line, an optimization problem is proposed which is solvable using convex optimization tools. Through simulations, we show the developed gain scheduled controller is capable to regulate a turboshaft engine for large thrust commands in a stable fashion with proper tracking performance. Third, a gain scheduled model reference adaptive control (GS-MRAC) concept for multi-input multi-output (MIMO) nonlinear plants with constraints on the control inputs is developed and described. Specifically, adaptive state feedback for the output tracking control problem of MIMO nonlinear systems is studied. Gain scheduled reference model system is used for generating desired state trajectories, and the stability of this reference model is also analyzed using convex optimization tools. This approach guarantees stability of the closed-loop gain scheduled gas turbine engine system, which is used as a gain scheduled reference model. An adaptive state feedback control scheme is developed and its stability is proven, in addition to transient and steady-state performance guarantees. The resulting closed-loop system is shown to have ultimately bounded solutions with a priori adjustable bounded tracking error. The results are then extended to GS-MRAC with constraints on the magnitudes of multiple control inputs. Sufficient conditions for uniform boundedness of the closed-loop system is derived. A semi-global stability result is proven with respect to the level of saturation for open-loop unstable plants, while the stability result is shown to be global for open-loop stable plants. Simulations are performed for three different models of the turboshaft engine, including the nominal engine model and two models where the engine is degraded. Through simulations, we show the developed GS-MRAC architecture can be used for the tracking problem of degraded turboshaft engine for large thrust commands with guaranteed stability. Finally, a decentralized linear parameter dependent representation of the engine model is developed, suitable for decentralized control of the engine with core and fan/prop subsystems. Control theoretic concepts for decentralized gain scheduled model reference adaptive control (D-GS-MRAC) systems is developed. For each subsystem, a linear parameter dependent model is available and a common Lyapunov matrix can be computed using convex optimization tools. With this control architecture, the two subsystems of the engine (i.e., engine core and engine prop/fan) can be controlled with independent controllers for large throttle commands in a decentralized manner. Based on this D-GS-MRAC architecture, a "plug and play" (PnP) technology concept for gas turbine engine control systems is investigated, which allows us to match different engine cores with different engine fans/propellers. With this plug and play engine control architecture, engine cores and fans/props could be used with their on-board subordinate controllers ready for integration into a functional propulsion system. Simulation results for three different models of the engine, including the nominal engine model, the model with a new prop, and the model with a new engine core, illustrate the possibility of PnP technology development for gas turbine engine control systems.
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Kulkarni, Aditya Narayan. "Computational and Experimental Investigation of Internal Cooling Passages for Gas Turbine Applications." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1590591363859471.

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Dolan, Brian. "Flame Interactions and Thermoacoustics in Multiple-Nozzle Combustors." University of Cincinnati / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1479822588098224.

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Whitaker, Steven Michael. "Informing Physics-Based Particle Deposition Models Using Novel Experimental Techniques to Evaluate Particle-Surface Interactions." The Ohio State University, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=osu1500473579986028.

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Books on the topic "Aerospace gas turbines"

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National Conference on Air Breathing Engines and Aerospace Propulsion (7th 2004 I.I.T., Kanpur). Air breathing engines and aerospace propulsion: Proceedings of NCABE 2004, 05-07 November, 2004. Edited by Raghunandan B. N, Oommen Charlie, Sullerey R. K, and Indian Institute of Technology (Kānpur, India). New Delhi: Allied Publishers, 2004.

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Shcherbakov, V. L. Pod znamenem NK: Ot zavoda £ 24 im. M.V. Frunze do OAO "Kuznet︠s︡ov". Moskva: Zolotoe krylo, 2012.

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Gas Turbine Research Establishment (Bangalore, India), Indian Institute of Science, Bangalore., National Aerospace Laboratories (India), and National Conference on Air Breathing Engines and Aerospace Propulsion (4th : 1998 : Bangalore, India), eds. Air breathing engines and aerospace propulsion: Proceedings of the fourth national conference, 3-5 December 1998, Bangalore. Bangalore: Interline Pub., 1998.

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J, Locke Randy, and Lewis Research Center, eds. Challenges to laser-based imaging techniques in gas turbine combustor systems for aerospace applications. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

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Challenges to laser-based imaging techniques in gas turbine combustor systems for aerospace applications. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

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J, Locke Randy, and Lewis Research Center, eds. Challenges to laser-based imaging techniques in gas turbine combustor systems for aerospace applications. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

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J, Locke Randy, and Lewis Research Center, eds. Challenges to laser-based imaging techniques in gas turbine combustor systems for aerospace applications. [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

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Book chapters on the topic "Aerospace gas turbines"

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Gialanella, Stefano, and Alessio Malandruccolo. "Gas Turbine Aero-Engines." In Aerospace Alloys, 17–39. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-24440-8_2.

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Shibayama, T., J. Sato, N. Sato, T. Nonomura, E. Shimohira, T. Uehara, and S. Imano. "Development of Ni-Base Disk Alloy for Large-Size Gas Turbines by Improving Macrosegregation Property of Alloy 718." In Proceedings of the 9th International Symposium on Superalloy 718 & Derivatives: Energy, Aerospace, and Industrial Applications, 1087–101. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-89480-5_72.

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Kumar, Dilip, and Sanjay G. Barad. "Structural Health Assessment of Gas Turbine Engine Carcass." In Proceedings of the National Aerospace Propulsion Conference, 479–89. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_29.

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McLean, M. "Nickel-based alloys: recent developments for the aero-gas turbine." In High Performance Materials in Aerospace, 135–54. Dordrecht: Springer Netherlands, 1995. http://dx.doi.org/10.1007/978-94-011-0685-6_4.

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Vick, Andrew, and Kelly Cohen. "Genetic Fuzzy Controller for a Gas-Turbine Fuel System." In Advances in Intelligent and Autonomous Aerospace Systems, 229–72. Reston, VA: American Institute of Aeronautics and Astronautics, Inc., 2012. http://dx.doi.org/10.2514/5.9781600868962.0229.0272.

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Sankar, Balaji, and Tahzeeb Hassan Danish. "Performance Trends of a Generic Small Gas Turbine Engine." In Proceedings of the National Aerospace Propulsion Conference, 243–62. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_14.

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Devi Priya, T., Sunil Kumar, Devendra Pratap, S. Shylaja, T. N. Satish, and A. N. Vishwanatha Rao. "Rotor Blade Vibration Measurement on Aero Gas Turbine Engines." In Proceedings of the National Aerospace Propulsion Conference, 263–73. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_15.

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Tandon, Vishal, S. N. Dileep Bushan Reddy, R. D. Bharathan, and S. V. Ramana Murthy. "Unsteady Flow Analysis of a Highly Loaded High-Pressure Turbine of a Gas Turbine Engine." In Proceedings of the National Aerospace Propulsion Conference, 119–32. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_7.

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Jagadish Babu, Chinni, Mathews P. Samuel, and Antonio Davis. "In-Depth Analysis of the Starting Process of Gas Turbine Engines." In Proceedings of the National Aerospace Propulsion Conference, 219–42. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_13.

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Vishwanatha Rao, A. N., T. N. Satish, Anagha S. Nambiar, Soumemndu Jana, V. P. S. Naidu, G. Uma, and M. Umapathy. "Challenges in Engine Health Monitoring Instrumentation During Developmental Testing of Gas Turbine Engines." In Proceedings of the National Aerospace Propulsion Conference, 275–95. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5039-3_16.

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Conference papers on the topic "Aerospace gas turbines"

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Naeem, Mohammed, and John Chinn. "Advancement in laser drilling for aerospace gas turbines." In PICALO 2008: 3rd Pacific International Conference on Laser Materials Processing, Micro, Nano and Ultrafast Fabrication. Laser Institute of America, 2008. http://dx.doi.org/10.2351/1.5057005.

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Acurio, John. "Small Gas Turbines in the 21st Century." In Aerospace Atlantic Conference & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1993. http://dx.doi.org/10.4271/931453.

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Khalil Hasan, Ahmed, and Ashwani Gupta. "Flowfield Effects on Distributed Combustion for Clean Gas Turbines." In 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-874.

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Marshall, A., N. Rizk, and J. Chin. "Two-dimensional simulation of fuel injection in gas turbines." In 37th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-341.

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Fletcher, Timothy, and Richard Brown. "Interaction of an Eulerian Flue Gas Plume with Wind Turbines." In 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-1377.

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Baranger, Philippe, Mikael Orain, and Frederic Grisch. "Fluorescence Spectroscopy of Kerosene Vapour: Application to Gas Turbines." In 43rd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-828.

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Schluter, Jorg, Juan Alonso, Heinz Pitsch, Xiaohua Wu, and Sangho Kim. "Integrated RANS-LES Computations in Gas Turbines: Compressor-Diffusor Coupling." In 42nd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-369.

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Syred, Nicholas, Milana V. Gutesha, Ali Doboon, Agustin Valera-Medina, and Philip J. Bowen. "CARSOXY (CO2-Argon-Steam-OxyFuel) Combustion in Gas Turbines for CCS Systems." In 55th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-1608.

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9

Paxson, Daniel, and Thomas Kaemming. "Foundational Performance Analyses of Pressure Gain Combustion Thermodynamic Benefits for Gas Turbines." In 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-770.

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Lieuwen, Tim, and Ben Zinn. "Theoretical investigation of combustion instability mechanisms in lean premixed gas turbines." In 36th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-641.

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