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Relevant bibliographies by topics / Aircraft gas-turbines

Academic literature on the topic 'Aircraft gas-turbines'

Author: Grafiati

Published: 4 June 2021

Last updated: 29 July 2024

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Dissertations / Theses
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Journal articles on the topic "Aircraft gas-turbines"

1

Wells, Robert L. "AIRCRAFT GAS TURBINES." Journal of the American Society for Naval Engineers 61, no. 4 (March 18, 2009): 785–98. http://dx.doi.org/10.1111/j.1559-3584.1949.tb02655.x.

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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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Shende, R. W., and S. K. Sane. "Squeeze Film Damping for Aircraft Gas Turbines." Defence Science Journal 38, no. 4 (January 13, 1988): 439–56. http://dx.doi.org/10.14429/dsj.38.5874.

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Valenti, Michael. "A Drier Way To Clean Turbines." Mechanical Engineering 120, no. 03 (March 1, 1998): 98–100. http://dx.doi.org/10.1115/1.1998-mar-7.

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A high-pressure injection system that needs less water to clean gas turbines than conventional methods can reduce equipment maintenance costs for aircraft, offshore platforms, and power plants. Gas Turbine Efficiency (GTE) in Jarfalla, Sweden, has developed a high-pressure injection system that cleans turbines using atomized droplets and needs 90 percent less liquid than previous methods. With this technique, the operators of offshore oil platforms, power plants, refineries, and aircraft in several countries are reducing the purchase costs of new fluids, the disposal costs of spent cleaning fluids, and maintenance downtime. In creating their washing system, designers considered the differences in cleaning aviation and stationary engines. The turbine-washing system is available in mobile versions for aircraft engines and permanently installed versions, for the off-line cleaning of stationary turbines. GTE also designed two models to serve the very small and very large turbines. The GTE 30 A services the small turbines, ranging from 0.5 to 10 megawatts, that are used in industrial, power-generation, marine, and test-cell applications as well as turboprop aircraft, turbofan craft, and helicopters.

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Gregory, Brent A. "How Many Turbine Stages?" Mechanical Engineering 139, no. 05 (May 1, 2017): 56–57. http://dx.doi.org/10.1115/1.2017-may-5.

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This article discusses various stages of turbines and the importance of having more stages in turbine design. The article also highlights reasons that determine the designer’s choice to select the number of turbine stages for a given design of gas turbine. The highest performance turbines are defined by lower work requirements and slower velocities in the gas path. The fundamental factors determining performance might be relegated to only two factors: demand on the turbine and axial velocity. Aircraft engine technologies drive new initiatives because of the need to increase firing temperature and dramatically improve efficiency for substantially less weight. Also, the expansion across each stage determined the annulus area so that the optimums implied by the Pearson chart were largely ignored in the article. Developments in aircraft engine gas turbines have forced heavy frame gas turbines’ original equipment manufacturers to rethink many historical paradigms.

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Mannan, S. K., and Shalesh J. Patel. "INCONEL Alloy 783: An Oxidation Resistant, Low Expansion Superalloy for Gas and Steam Turbine Applications." Materials Science Forum 546-549 (May 2007): 1271–76. http://dx.doi.org/10.4028/www.scientific.net/msf.546-549.1271.

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Recently developed alloy 783 (nominal composition of Ni-34Co-26Fe-5.4Al-3Nb-3Cr, UNS R30783) is precipitation strengthened by Ni3Al-type gamma prime and NiAl-type beta phases. The alloy is being used for seals/casings in aircraft gas turbines and for bolting in steam turbines due to its low co-efficient of thermal expansion, high strength, and good oxidation resistance. It has also been specified for other aircraft gas turbine components such as rings for casings and shrouds. This paper presents the alloy’s basic characteristics, applications, and hot and cold workability.

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Langston, Lee S. "Riding the Surge." Mechanical Engineering 135, no. 05 (May 1, 2013): 37–41. http://dx.doi.org/10.1115/1.2013-may-2.

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This article explores the advantages of gas turbines in the marine industry. Marine gas turbines, which are designed specifically for use on ships, have long been one of the segments of the gas turbine market. One advantage that gas turbines have over conventional marine diesels is volume. Gas turbines are the prime movers for the modern combined cycle electric power plant. Both CFM International (a joint venture of General Electric and France’s Snecma) and Pratt & Whitney are working on new engines for this multibillion dollar single-aisle, narrow-body market. Pratt & Whitney’s new certified PW1500G geared turbofans will have a first flight powering the first Bombardier CSeries aircraft. On land, sea, and air, the surge in gas turbine production is remarkable. The experts suggest that what the steam engine was to the 19th century and the internal combustion engine was to the 20th, the gas turbine might be to the 21st century: the ubiquitous prime mover of choice.

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Langston, Lee S. "Old and New." Mechanical Engineering 141, no. 06 (June 1, 2019): 38–43. http://dx.doi.org/10.1115/1.2019-jun2.

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As prime movers go, gas turbines are virtually brand new, compared to, say, wind and water turbines which have been around for millennia. But they have also reached a considerable level of maturity. Gas turbines now dominate both the world’s aircraft propulsion and a good portion of electric power generation. The fortunes of the industry are not uniform, however. The commercial jet engine market is robust and growing; the military jet engine, electric power, and other markets have been relatively flat or declining. But those are the sectors where the possibilities lie. They aren’t new, but they have the potential for renewal. This study delves deeper into the current status and trends in theworldwide gas turbine market.

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Cowles, B. A. "High cycle fatigue in aircraft gas turbines—an industry perspective." International Journal of Fracture 80, no. 2-3 (April 1996): 147–63. http://dx.doi.org/10.1007/bf00012667.

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Rohacs, Jozsef, Istvan Jankovics, Istvan Gal, Jerzy Bakunowicz, Giuseppe Mingione, and Antonio Carozza. "Small Aircraft Infrared Radiation Measurements Supporting the Engine Airframe Aero-thermal Integration." Periodica Polytechnica Transportation Engineering 47, no. 1 (March 12, 2018): 51–63. http://dx.doi.org/10.3311/pptr.11514.

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The large, EU Supported ESPOSA (Efficient Systems and propulsion for Small Aircraft) project has developed new small gas turbines for small aircraft. One of the important tasks was the engine - airframe aero-thermal radiation integration that included task of minimizing the infrared radiation of the small aircraft, too. This paper discusses the factors influencing on the aircraft infrared radiation, its possible simulation and measurements and introduces the results of small aircraft infrared radiation measurements. The temperature of aircraft hot parts heated by engines were determined for validation of methodology developed and applied to engine - aircraft thermal integration.

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Dissertations / Theses on the topic "Aircraft gas-turbines"

1

Janakiraman, S. V. "Fluid flow and heat transfer in transonic turbine cascades." Thesis, This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-06112009-063614/.

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Roy-Aikins, J. E. A. "A study of variable geometry in advanced gas turbines." Thesis, Cranfield University, 1988. http://hdl.handle.net/1826/3907.

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The loss of performance of a gas turbine engine at off-design is primarily due to the rapid drop of the major cycle performance parameters with decrease in power and this may be aggravated by poor component performance. More and more stringent requirements are being put on the performance demanded from gas turbines and if future engines are to exhibit performances superior to those of present day: engines, then a means must be found of controlling engine cycle such that the lapse rate of the major cycle parameters with power is reduced. In certain applications, it may be desirable to vary engine cycle with operating conditions in an attempt to re-optimize performance. Variable geometry in key engine components offers the advantage of either improving the internal performance of a component or re-matching engine cycle to alter the flow-temperature-pressure relationships. Either method has the potential to improve engine performance. Future gas turbines, more so those for aeronautical applications, will extensively use variable geometry components and therefore, a tool must exist which is capable of evaluating the off-design performance of such engines right from the conceptual stage. With this in mind, a computer program was developed which can simulate the steady state performance of arbitrary gas turbines with or without variable geometry in the gas path components. The program is a thermodynamic component-matching analysis program which uses component performance maps to evaluate the conditions of the gas at the various engine stations. The program was used to study the performance of a number of cycles incorporating variable geometry and it was concluded that variable geometry can significantly improve the off-design performance of gas turbines.

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Holt, Daniel B. "Design, fabrication, and testing of a miniature impulse turbine driven by compressed gas /." Online version of thesis, 2004. http://hdl.handle.net/1850/11793.

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Lim, Chia Hui. "The influence of film cooling on turbine aerodynamic performance." Thesis, University of Cambridge, 2011. https://www.repository.cam.ac.uk/handle/1810/283872.

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Birmaher, Shai. "A method for aircraft afterburner combustion without flameholders." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/28081.

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Thesis (M. S.)--Aerospace Engineering, Georgia Institute of Technology, 2009.
Committee Chair: Zinn, Ben; Committee Member: Fuller, Thomas; Committee Member: Gaeta, Rick; Committee Member: Jagoda, Jeff; Committee Member: Neumeier, Yedidia

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Aygun, Aysegul. "Novel thermal barrier coatings (TBCs) that are resistant to high temperature attack by CaO-MgO-Al₂O₃-SiO₂ (CMAS) glassy deposits." Columbus, Ohio : Ohio State University, 2008. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=osu1221589661.

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Acharya, Vishal Srinivas. "Dynamics of premixed flames in non-axisymmetric disturbance fields." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50213.

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With strict environmental regulations, gas turbine emissions have been heavily constrained. This requires operating conditions wherein thermo-acoustic flame instabilities are prevalent. During this process the combustor acoustics and combustion heat release fluctuations are coupled and can cause severe structural damage to engine components, reduced operability, and inefficiency that eventually increase emissions. In order to develop an engine without these problems, there needs to be a better understanding of the physics behind the coupling mechanisms of this instability. Among the several coupling mechanisms, the “velocity coupling” process is the main focus of this thesis. The majority of literature has treated axisymmetric disturbance fields which are typical of longitudinal acoustic forcing and axisymmetric excitation of ring vortices. Two important non-axisymmetric disturbances are: (1) transverse acoustics, in the case of circumferential modes of a multi-nozzle annular combustor and (2) helical flow disturbances, seen in the case of swirling flow hydrodynamic instabilities. With significantly less analytical treatment of this non-axisymmetric problem, a general framework is developed for three-dimensional swirl-stabilized flame response to non-axisymmetric disturbances. The dynamics are tracked using a level-set based G-equation applicable to infinitely thin flame sheets. For specific assumptions in a linear framework, general solution characteristics are obtained. The results are presented separately for axisymmetric and non-axisymmetric mean flames. The unsteady heat release process leads to an unsteady volume generation at the flame front due to the expansion of gases. This unsteady volume generation leads to sound generation by the flame as a distributed monopole source. A sound generation model is developed where ambient pressure fluctuations are generated by this distributed fluctuating heat release source on the flame surface. The flame response framework is used to provide this local heat release source input. This study has been specifically performed for the helical flow disturbance cases to illustrate the effects different modes have on the generated sound. Results show that the effects on global heat release and sound generation are significantly different. Finally, the prediction from the analytical models is compared with experimental data. First, a two-dimensional bluff-body stabilized flame experiment is used to obtain measurements of both the flow and flame position in time. This enables a local flame response comparison since the data are spatially resolved along the flame. Next, a three-dimensional swirl-stabilized lifted flame experiment is considered. The measured flow data is used as input to the G-equation model and the global flame response is predicted. This is then compared with the corresponding value obtained using global CH* chemilumenescence measurements.

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Bobba, Mohan Krishna. "Flame stabilization and mixing characteristics in a stagnation point reverse flow combustor." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/26502.

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Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2008.
Committee Chair: Seitzman, Jerry; Committee Member: Filatyev, Sergei; Committee Member: Jagoda, Jechiel; Committee Member: Lieuwen, Timothy; Committee Member: Shelton, Samuel; Committee Member: Zinn, Ben. Part of the SMARTech Electronic Thesis and Dissertation Collection.

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Sudol, Eugene G. "Evaluation of aircraft turbine redesigns." Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA237599.

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Thesis (M.S. in Management)--Naval Postgraduate School, June 1990.
Thesis Advisor(s): Carrick, Paul M. Second Reader: Doyle, Richard B. "June 1990." Description based on title screen as viewed on October 16, 2009. DTIC Identifier(s): Jet Engines, Engine Components, Cost Analysis, Gas Turbines, Optimizations, Naval Logistics, Aircraft Maintenance, CIP(Component Improvement Program), Benefits, Redesign, Naval Aircraft, Mean Time Between Failure, Data Bases, Theses. Author(s) subject terms: Aircraft Turbine Engine Redesigns Component Improvement Program. Includes bibliographical references (p. 58-60). Also available in print.

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Silva, Douglas Felipe Rodrigues da. "Design and analysis of a multivariable robust control system for aircraft gas turbines." Instituto Tecnológico de Aeronáutica, 2012. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2202.

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Gas turbine engines are important thermal machines used in industrial and transportation fields. They convert fuel energy into mechanical power or thrust for aerial and maritime vehicles, as well as generate pneumatic and electrical energy that could be used for a large variety of applications. The constant search for fuel burn savings and low pollutant emissions in aviation demands, along with new hardware and material technologies, highly complex engine control systems to optimize fuel consumption throughout the engine operating envelope, and consequently generate more efficient aircraft, in addition to meet the regulatory requirements in terms of safety and performance. These conflicting objectives normally lead to trade-off solutions which are difficult to precisely estimate given the large number of variables involved, including altitude, Mach number, ambient temperature, power and bleed extraction, among others. Therefore, some decisions to characterize the engine controller still reside on experience from previous designs and, as a result, add subjectivity and increase the potential for wrong parameter selection. These control systems significantly contribute to gas turbine performance increase. In this sense, this work proposes the study, design and analysis of multivariable robust controllers for a particular gas turbine engine. Firstly, an algorithmic approach is applied to design an aircraft gas turbine engine controller in a two-degree-of-freedom configuration, obtaining H-infinity robust stabilization. It introduces an optimized loop shape design procedure, with the use of the Genetic Algorithm (GA), to further improve the control system performance, as well as bring the experience applied by controller designers and engineers to an automated process, when setting the parameters to shape the frequency response of the engine control loops. Secondly, a Linear Quadratic Gaussian (LQG) controller, with the Loop Transfer Recovery (LTR) is developed to allow a comparative analysis. The resulting controllers are evaluated by computer simulations under typical operating conditions and compared against each other. Noise immunity is also verified. The complete system is also evaluated against requirements from the aviation industry for commercial aircraft engines. Finally, robustness is evaluated in a similar engine model by generating uncertain state space models based on the boundaries of its nominal model at extreme operating conditions.

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Books on the topic "Aircraft gas-turbines"

1

W, Niedzwiecki Richard, and United States. National Aeronautics and Space Administration., eds. Combustor technology for future small gas turbine aircraft. [Washington, DC: National Aeronautics and Space Administration, 1993.

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A, Snyder Christopher, and United States. National Aeronautics and Space Administration., eds. Analysis of gas turbine engines using water and oxygen injection to achieve high Mach numbers and high thrust. [Washington, DC: National Aeronautics and Space Administration, 1993.

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H, Heiser William, and Daley Daniel H, eds. Aircraft engine design. Washington, D.C: American Institute of Aeronautics and Astronautics, 1987.

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H, Heiser William, and Pratt David T, eds. Aircraft engine design. 2nd ed. Reston, Va: American Institute of Aeronautics and Astronautics, 2002.

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J, Glassman Arthur, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program, eds. Turbine design and application. Washington, DC: Scientific and Technical Information Program, National Aeronautics and Space Administration, 1994.

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C, Oates Gordon, ed. Aerothermodynamics of aircraft engine components. New York, N.Y: American Institute of Aeronautics and Astronautics, 1985.

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J, Follen Gregory, Putt Charles W, and United States. National Aeronautics and Space Administration., eds. Gas turbine system simulation: An object-oriented approach. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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F, Lorenzo Carl, Merrill Walter C, and United States. National Aeronautics and Space Administration., eds. Screening studies of advanced control concepts for airbreathing engines. [Washington, DC]: National Aeronautics and Space Administration, 1992.

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United States. National Aeronautics and Space Administration., ed. Structural analysis methods development for turbine hot section components. [Washington, DC]: National Aeronautics and Space Administration, 1988.

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Institution of Mechanical Engineers (Great Britain). Aerospace Industries Division., ed. Gas turbines: Reducing time and cost from concept to product : 13 November 1997. Bury St. Edmunds, UK: Mechanical Engineering Publications Ltd. for the Institution of Mechanical Engineers, 1997.

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Book chapters on the topic "Aircraft gas-turbines"

1

Bose, Tarit. "Off-Design Running of Aircraft Gas Turbines." In Airbreathing Propulsion, 217–32. New York, NY: Springer New York, 2012. http://dx.doi.org/10.1007/978-1-4614-3532-7_9.

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Jemmali, Mahdi, Loai Kayed B. Melhim, and Mafawez Alharbi. "Randomized-Variants Lower Bounds for Gas Turbines Aircraft Engines." In Advances in Intelligent Systems and Computing, 949–56. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-21803-4_94.

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Massini, M., and Francesco Montomoli. "Manufacturing/In-Service Uncertainty and Impact on Life and Performance of Gas Turbines/Aircraft Engines." In Uncertainty Quantification in Computational Fluid Dynamics and Aircraft Engines, 1–32. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-92943-9_1.

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"Aircraft Gas Turbines." In Handbook of Lubrication and Tribology, 135–56. CRC Press, 2006. http://dx.doi.org/10.1201/9781420003840-12.

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Hall, Andy. "Aircraft Gas Turbines." In Handbook of Lubrication and Tribology, 1–11. CRC Press, 2006. http://dx.doi.org/10.1201/9781420003840.ch6.

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Gudmundsson, Snorri. "Thrust Modeling for Gas Turbines." In General Aviation Aircraft Design, 573–95. Elsevier, 2022. http://dx.doi.org/10.1016/b978-0-12-818465-3.00014-8.

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"Aircraft Gas Turbine Engine." In Elements of Propulsion: Gas Turbines and Rockets, 233–60. Reston ,VA: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/5.9781600861789.0233.0260.

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"Aircraft Gas Turbine Engine." In Elements of Propulsion: Gas Turbines and Rockets, Second Edition, 245–80. Reston, VA: American Institute of Aeronautics and Astronautics, Inc., 2016. http://dx.doi.org/10.2514/5.9781624103711.0245.0280.

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Di Girolamo, Giovanni. "Current Challenges and Future Perspectives in the Field of Thermal Barrier Coatings." In Production, Properties, and Applications of High Temperature Coatings, 25–59. IGI Global, 2018. http://dx.doi.org/10.4018/978-1-5225-4194-3.ch002.

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This chapter describes how ceramic thermal barrier coatings (TBCs) are usually applied on metal components of aircraft engines and land-based gas turbines, with the purpose to extend their lifetime as well as to increase performance and durability, by increasing the operating temperature. The TBCs have to satisfy basic requirements in terms of low thermal conductivity, high stress compliance, high sintering resistance as well as high resistance to the environmental attack promoted by oxygen, molten salts and CMAS (calcium-magnesium-alumino-silicate) deposits. This chapter is aimed at analyzing the state-of-the-art, the recent developments and the future perspectives in the field of TBCs, focusing the attention on advanced materials and new architectures as well as explaining the mechanisms affecting the failure of TBC systems.

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Lawton, B., and G. Klingenberg. "Thermal Properties And Thermal Failure." In Transient Temperature in Engineering and Science, 505–73. Oxford University PressOxford, 1996. http://dx.doi.org/10.1093/oso/9780198562603.003.0010.

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Abstract In scientific work, transient temperatures and heat flows are measured because they may help to confirm or enlighten our understanding of the process being investigated. The is also true in engineering. However, engineers have an additional need for such data because they may have to ensure that the components they are designing are capable of withstanding high temperatures and heat flows. It is, in fact, the temperature and heat flux that often limit the performance of engineering equipment. For example, the boost pressure, and hence the power output, of turbocharged diesel engines could be increased to values three or more times higher than at present. However, if this were done the pistons, valves, and other combustion chamber components would certainly overheat and fail. Thus progress in developing more powerful engines is controlled by the rate at which the thermal design of such components develops. Similar comments might be applied to aircraft gas turbines, rockets and satellites, steam power plant, refrigeration, X-ray machines, and many other devices.

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Conference papers on the topic "Aircraft gas-turbines"

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Morquillas, Jose M., and Pericles Pilidis. "‘Recycling’ of Gas Turbines From Obsolete Aircraft." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-309.

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This paper examines the utilisation of aero gas turbines fitted to aircraft which are close to the end of their useful lives. When the aircraft are scrapped the engines can be removed, modified and employed for land or sea applications. The engine chosen as a possible candidate for ‘recycling’ is a two spool bypass engine. A performance analysis has been carried out, which indicates that this scheme can yield good levels of output and efficiency. Preliminary examinations indicate that there are economic advantages in converting these engines for other uses. Two possible conversions are examined: one for a pure industrial engine, and one as the gas side of a combined cycle power plant. The results obtained from this feasibility analysis appear attractive; the anticipated cost of purchasing and conversion is predicted to be significantly lower than purchasing new equipment.

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Boyce, Meherwan P. "The Testing of Gas Turbines." In ASME 2007 Power Conference. ASMEDC, 2007. http://dx.doi.org/10.1115/power2007-22126.

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ASME codes cover testing of all types of gas turbines between the ASME PTC 22 and ASME PTC 55, which will be available by 2008. The testing of gas turbines in land-based units is handled in PTC 22, while the testing of Aircraft gas turbines is handled in PTC 55. The paper addresses the development of ASME Test Codes, and the testing of gas turbines for aircraft, power generation and mechanical drive gas turbines highlighting some of the many differences in the characteristics of both engines.

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Gallops, G. W., F. D. Gass, and M. H. Kennedy. "On-Board Condition Management for Aircraft Gas Turbines." 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-416.

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A revolutionary approach to gas turbine condition monitoring is made possible by the recent development of accurate real-time gas turbine performance models. This paper describes an approach for an integrated condition management system operating concurrently with the gas turbine control system for improved availability, safety and economy. This paper considers the system subject to the requirements and constraints of aircraft gas turbines. A system architecture is described based on a primary, gas path performance model with supplementary models representing the secondary air, fuel and lubrication systems and the rotor system dynamics. Measurement and processing requirements for the system are defined. Preflight, in-flight and postflight application and analysis by the gas turbine operator are discussed.

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Scotti Del Greco, Alberto, Vittorio Michelassi, Stefano Francini, Daniele Di Benedetto, and Mahendran Manoharan. "Aero Derivative Mechanical Drive Gas Turbines: The Design of Intermediate Pressure Turbines." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76036.

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Gas turbines engine designers are leaning towards aircraft engine architectures due to their footprint, weight, and performance advantages. Such engines need some modifications to both the combustion system, to comply with emission limits, and turbine rotational speed. Aero derivative engines maintain the same legacy aircraft engine architecture, and replace the fan and booster with higher speed compressor booster driven by a single stage intermediate turbine. A multistage free power turbine (FPT) sits on a separate shaft to drive compressors for Liquefied Natural Gas (LNG) applications or generators. The intermediate power turbine (IPT) design is important for the engine performance as it drives the booster compressor and sets the inlet boundary conditions to the downstream power turbine. This paper describes the experience of Baker Hughes, a GE company (BHGE) in the design of the intermediate turbine that sits in between a GE legacy aircraft engine core exhaust and the downstream power turbine. This paper focuses on the flow path of the TCF/intermediate turbine and the associated design, as well as on the 3D steady and unsteady CFD assisted design of the IPT stage to control secondary flows in presence of through flow curvature induced by the upstream TCF.

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Hajmrle, K., P. Fiala, A. P. Chilkowich, and L. Shiembob. "New Abradable Seals for Industrial Gas Turbines." In ITSC2003, edited by Basil R. Marple and Christian Moreau. ASM International, 2003. http://dx.doi.org/10.31399/asm.cp.itsc2003p0735.

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Abstract Abradable seals are used in compressors of aircraft and industrial gas turbines to decrease clearance between the stator casing and rotor blade tips and hence to increase compressor efficiency and decrease fuel consumption. The main interest of abradable materials producers has been concentrated on abradable seals for aircraft engines, and special requirements of industrial gas turbine manufacturers have not been met so far. The most significant requirement in industrial gas turbines is durability. This is driven by the need for several times longer periods between overhauls in industrial gas turbines compared to aircraft engines. Westaim Ambeon has developed a new composite powder, Durabrade2413, that meets these requirements. The new abradable seals fabricated by using this powder have been extensively tested over a prolonged period of time. This paper will present the results of an intensive development, evaluation and abradability testing of seal properties. This paper will also show that Durabrade2413 series coating properties can be altered in a broad range by changing spray parameters to tailor the coating to a particular application. The abradable seals are suitable to rub against steel and Ni alloy blades. The abradability results of Durabrade2413 are compared to Durabrade2222 (the Metco 307-NS equivalent), the well known 75Ni25 Graphite abradable that has been on the market for the last 30 years.

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Evans, C. "Testing and modelling aircraft gas turbines: an introduction and overview." In UKACC International Conference on Control (CONTROL '98). IEE, 1998. http://dx.doi.org/10.1049/cp:19980428.

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Alonso, Jacinto J. "Economic Considerations of Aircraft Turbines Manufacturing." In ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1990. http://dx.doi.org/10.1115/90-gt-278.

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Abstract:

Aircraft gas turbines manufacturing started just fifty years ago; its production experienced one of the fastest evolutions of the world manufacturing industry. The purpose of this paper is to briefly describe some of the most important factors that currently affect the economic production of aircraft turbines. Lead time for design and development of new turbines has increased with size and complexity, which makes the start of new projects much more difficult where a close liason is necessary between design and manufacturing departments. Interaction of so many activities will require a considerable coordination effort. Estimating production costs and labour time standards will be also key factors for economic production of aircraft turbines. The effect of production quantity will be analysed using the learning curve approach which can be applied for direct and indirect labour time, material costs and material and labour burdens.

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Wilson, David Gordon, P. K. Poole, L. D. Owens, and J. Baglione. "Conversion of Decommissioned Aircraft Gas Turbines to High-Efficiency Marine Units." In ASME 1985 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-gt-169.

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Abstract:

Some helicopter and other engines have been shown in studies to be amenable to conversion to a low-pressure-ratio highly regenerated cycle. Typically the high-pressure compressor and high-pressure turbine would be removed, and shaft and ducting modifications would be made to introduce high-effectiveness rotary ceramic-honeycomb regenerators. In one case examined the low-pressure turbine could be used with slight modification; in others there would have to be reblading of the turbine stages and the manufacture of new shrouds. In another case the existing combustor could be used with little modification; in others new combustors would be required. Despite the extent of the modifications, the resulting high-efficiency performance over a large part of the power range and presumably relatively low capital and development costs could make this an attractive concept.

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Hartranft, John, Bruce Thompson, and Dan Groghan. "The United States Navy “Standard Day” for Marine Gas Turbines." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-64048.

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Following the successful development of aircraft jet engines during World War II (WWII), the United States Navy began exploring the advantages of gas turbine engines for ship and boat propulsion. Early development soon focused on aircraft derivative (aero derivative) gas turbines for use in the United States Navy (USN) Fleet rather than engines developed specifically for marine and industrial applications due to poor results from a few of the early marine and industrial developments. Some of the new commercial jet engine powered aircraft that had emerged at the time were the Boeing 707 and the Douglas DC-8. It was from these early aircraft engine successes (both commercial and military) that engine cores such as the JT4-FT4 and others became available for USN ship and boat programs. The task of adapting the jet engine to the marine environment turned out to be a substantial task because USN ships were operated in a completely different environment than that of aircraft which caused different forms of turbine corrosion than that seen in aircraft jet engines. Furthermore, shipboard engines were expected to perform tens of thousands of hours before overhaul compared with a few thousand hours mean time between overhaul usually experienced in aircraft applications. To address the concerns of shipboard applications, standards were created for marine gas turbine shipboard qualification and installation. One of those standards was the development of a USN Standard Day for gas turbines. This paper addresses the topic of a Navy Standard Day as it relates to the introduction of marine gas turbines into the United States Navy Fleet and why it differs from other rating approaches. Lastly, this paper will address examples of issues encountered with early requirements and whether current requirements for the Navy Standard Day should be changed. Concerning other rating approaches, the paper will also address the issue of using an International Organization for Standardization, that is, an International Standard Day. It is important to address an ISO STD DAY because many original equipment manufacturers and commercial operators prefer to rate their aero derivative gas turbines based on an ISO STD DAY with no losses. The argument is that the ISO approach fully utilizes the power capability of the engine. This paper will discuss the advantages and disadvantages of the ISO STD DAY approach and how the USN STD DAY approach has benefitted the USN. For the future, with the advance of engine controllers and electronics, utilizing some of the features of an ISO STD DAY approach may be possible while maintaining the advantages of the USN STD DAY.

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Visser, W. P. J., and I. D. Dountchev. "Modeling Thermal Effects on Performance of Small Gas Turbines." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42744.

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Gas turbines are applied at increasingly smaller scales for both aircraft propulsion and power generation. Recuperated turboshaft micro turbines below 30 kW are being developed at efficiencies competitive with other heat engines. The rapidly increasing number of unmanned aircraft applications requires the development of small efficient aircraft propulsion gas turbines. Thermal effects such as steady-state heat losses and transient heat soakage on large engine performance are relatively small and therefore often neglected in performance simulations. At small scales however, these become very significant due to the much higher heat transfer area-to-volume ratios in the gas path components. Recuperators often have high heat capacity and therefore affect transient performance significantly, also with large engine scales. As a result, for accurate steady-state and transient performance prediction of micro and recuperated gas turbines, thermal effects need to be included with sufficient fidelity. In the paper, a thermal network model functionality is presented that can be integrated in a gas turbine system simulation environment such as the Gas turbine Simulation Program GSP [1]. In addition, a 1-dimensional thermal effects model for recuperators is described. With these two elements, thermal effects in small recuperated gas turbines can be accurately predicted. Application examples are added demonstrating and validating the methods with models of a recuperated micro turbine. Simulation results are given predicting effects of heat transfer and heat loss on steady-state and transient performance.

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Reports on the topic "Aircraft gas-turbines"

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Reed, Aaaron T. Bayesian Belief Networks for Fault Identification in Aircraft Gas Turbines. Fort Belvoir, VA: Defense Technical Information Center, June 2000. http://dx.doi.org/10.21236/ada378859.

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