Relevant bibliographies by topics / JT9D

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

Academic literature on the topic 'JT9D'

Author: Grafiati
Published: 4 June 2021
Last updated: 5 February 2022

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Journal articles on the topic "JT9D"

1

Langston, Lee S. "Mounting Troubles." Mechanical Engineering 133, no. 03 (March 1, 2011): 46–49. http://dx.doi.org/10.1115/1.2011-mar-6.

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This article analyzes the problems encountered in developing the first jumbo jet, the Boeing 747. In the 1960s, the jumbo jet—a wide-body aircraft with two aisles and up to 10 seats per row—was the logical next step in the progression of the airliner. For the Pratt & Whitney JT9D, which was causing the 747 trouble, the engine skin casing was both bending and ovalizing—exhibiting non-circular distortion—under thrust loading that could be as high as 43,500 pounds on takeoff. The ovalizing distortion resulted in turbine and compressor blade rubbing against the interior of the engine case and necessitated power-robbing increases in blade tip clearance gaps. The result was a serious reduction in thrust, and increased fuel consumption as much as 7 percent above guaranteed rates. Boeing chose to mount the JT9D engines well forward of the 747 wing leading edges. The successful resolution of ovalization problems encountered in mounting the JT9D to the first Boeing 747s has provided guidance for future installations of large fan commercial jet engines.
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2

Oruc, Ridvan, and Tolga Baklacioglu. "Propulsive modelling for JT9D-3, JT15D-4C and TF-30 turbofan engines using particle swarm optimization." Aircraft Engineering and Aerospace Technology 92, no. 6 (May 21, 2020): 939–46. http://dx.doi.org/10.1108/aeat-02-2020-0031.

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Purpose The purpose of this paper is to create high-accuracy thrust modelling for cruise flight using particle swarm optimization (PSO) algorithm. Design/methodology/approach In this study, using PSO, new thrust models with high accuracy for the cruise flight stages of Pratt & Whitney JT9D-3, JT15D-4C and TF-30 engines were created. For this aim, real Mach number, flight altitude and thrust values taken from the engine manufacturers were used. In the model, thrust is given as a function of altitude and Mach number. The sensitivity of the results given by the PSO thrust model has been examined using several different error types. Finally, the effect of some PSO parameters on the created models is examined. Findings It was observed that the model created predicted real thrust values with high precision. Practical implications The PSO thrust model can be used in the trajectory estimates of today’s aircraft with the use of accurate scaling factors. In addition, using the developed PSO thrust model together with a correct aerodynamic model provides more effective management of air traffic flow in air traffic management applications. Combining the PSO model with fuel flow-rate models will significantly increase engine efficiency and performance; thus, making a major contribution to reducing engine emissions. Originality/value The originality of this study is that it is the first thrust modelling made with PSO in the literature for turbofan engines. The use of real data in the study and the creation of models for several different turbofan engines are important for the reliability of thrust models.
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Langston, Lee S. "Gems of Turbine Efficiency." Mechanical Engineering 136, no. 09 (September 1, 2014): 76–77. http://dx.doi.org/10.1115/9.2014-sep-9.

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This article discusses the use of turbine single-crystal blades in gas turbines. Single-crystal turbine blades were first used in military engines on Pratt’s F100 engine, which powered the F16 and F15 fighter aircrafts. Their first commercial use was on P&WA’s JT9D-7R4 engine, which received FAA certification in 1982, powering Boeing’s 767 and the Airbus A310. In jet engines, single-crystal turbine airfoils have proven to have as much as nine times more relative life in terms of creep strength and thermal fatigue resistance and over three times more relative life for corrosion resistance, when compared to equiaxed crystal counterparts. Modern high turbine inlet temperature jet engines with long life would not be possible without the use of single-crystal turbine airfoils. By eliminating grain boundaries, single-crystal airfoils have longer thermal and fatigue life, are more corrosion resistant, can be cast with thinner walls, and have a higher melting temperature. These improvements all contribute to higher gas turbine thermal efficiencies.
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Baklacioglu, Tolga. "Propulsive Modeling for TF-30 and JT9D-3 Turbofan Engines of Transport Aircraft by Using Genetic Algorithms and Neural Networks." Applied Mechanics and Materials 799-800 (October 2015): 885–89. http://dx.doi.org/10.4028/www.scientific.net/amm.799-800.885.

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Not only for aircraft performance calculations and trajectory predictions but also for air traffic management simulation tools and operational equipment, accomplishment of an accurate propulsive model for transport aircraft has a crucial priority and is a remarkable topic for aircraft industry. In the literature, there are very few propulsive modeling studies; furthermore, the demand for an accurate thrust model still remains unfulfilled. In this study, a new turbofan engine propulsive model determining the relationship between thrust, flight altitude, and Mach number was developed by using genetic algorithms (GAs) method and multilayer feed-forward neural networks (FNNs) utilizing Levenberg-Marquardt (LM), delta-bar-delta (DBD), and conjugate gradient (CG) learning algorithms. Estimated thrust values by the derived models showed a good fitting with actual thrust data for both models, which validated each model’s accuracy.
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Gede Suarna Apkara, Dewa Ngakan, and Lilis Esti riyanti. "RANCANGAN ALAT KHUSUS PELEPAS FRONT ACCESSORY SUPPORT ENGINE JT8D-15 DI PROGRAM STUDI TEKNIK PESAWAT UDARA SEKOLAH TINGGI PENERBANGAN INDONESIA." AIRMAN: Jurnal Teknik dan Keselamatan Transportasi 1, no. 2 (June 15, 2020): 90–104. http://dx.doi.org/10.46509/ajtkt.v1i2.22.

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Engine JT8D-15 merupakan gas turbine engine dengan tipe turbofan. sebagai media praktik taruna dalam melakukan pengecekan dan perawatan. Dikarenakan tidak adanya alat pelepas front accessory support untuk engine JT8D-15 di Hangar 01 Program Studi Teknik Pesawat Udara maka penulis membuat alat pelepas front accessory support untuk engine JT8D-15. Gambaran umum untuk melepas front accessory support pada engine JT8D-15 dengan metode penarikan memanfaatkan beban yang diaplikasikan oleh palu luncur. Pertama adalah memastikan bahwa rancangan alat mampu digunakan dalam pelepasan front accessory support engine JT8D-15, dilanjutkan dengan pemilihan material yang sesuai dalam perancangan. Tahapan ketiga dilakukan pemilihan ulir silinder dan poros palu luncur. Sehingga didapat dimensi rancangan yang diinginkan. Dan yang terakhir, memastikan bahwa sambungan las dapat menahan tegangan gunting yang terjadi pada rancangan alat khusus. Hasil rancangan ini diharapkan dapat membantu pelaksanaan praktik taruna pada praktik gasturbine engine saat pelepasan front accessory support engine JT8D-15. Dari hasil perancangan didapat rancangan yang kuat dan dapat melepas front accessory support engine JT8D-15.
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Ngakan Suara Apkara, Dewa, and Lilis Esti Riyanti. "Rancangan Alat Khusus Pelepas Front Accessory Support Engine Jt8d-15 di Program Studi Teknik Pesawat Udara." AIRMAN: Jurnal Teknik dan Keselamatan Transportasi 2, no. 1 (June 25, 2019): 96–112. http://dx.doi.org/10.46509/ajtk.v2i1.113.

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Engine JT8D-15 merupakan gas turbine engine dengan tipe turbofan. Sebagai media praktik taruna dalam melakukanpengecekan dan perawatan. Dikarenakan tidak adanya alat pelepas front accessory support untuk engine JT8D-15 diHangar 01 Program Studi Teknik Pesawat Udara maka penulis membuat alat pelepas front accessory support untuk engine JT8D-15. Gambaran umum untuk melepas front accessory support pada engine JT8D-15 dengan metode penarikanmemanfaatkan beban yang diaplikasikan oleh palu luncur. Pertama adalah memastikan bahwa rancangan alat mampudigunakan dalam pelepasan front accessory support engine JT8D-15, dilanjutkan dengan pemilihan material yang sesuai dalam perancangan. Tahapan ketiga dilakukan pemilihan ulir silinder dan poros palu luncur. Sehingga didapat dimensi rancanganyang diinginkan. Dan yang terakhir, memastikan bahwa sambungan las dapat menahan tegangan gunting yang terjadi padarancangan alat khusus. Hasil rancangan ini diharapkan dapat membantu pelaksanaan praktik taruna pada praktik gasturbineengine saat pelepasan front accessory support engine JT8D-15. Dari hasil perancangan didapat rancangan yang kuat dan dapatmelepas front accessory support engine JT8D-15.
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7

Kalbach, Jim. "Maximize business impact with JTBD." Interactions 26, no. 1 (December 21, 2018): 80–83. http://dx.doi.org/10.1145/3292021.

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8

Eayrs, Steve, Nguyen Phong Hai, and Janet Ley. "Assessment of a juvenile and trash excluder device in a Vietnamese shrimp trawl fishery." ICES Journal of Marine Science 64, no. 8 (October 8, 2007): 1598–602. http://dx.doi.org/10.1093/icesjms/fsm123.

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Abstract Eayrs, S., Hai, N. P., and Ley, J. 2007. Assessment of a juvenile and trash excluder device in a Vietnamese shrimp trawl fishery. – ICES Journal of Marine Science, 64: 1598–1602. In this study, we (i) identified why Vietnamese shrimp fishers land juvenile fish illegally; (ii) identified groups of fishers that would use a bycatch reduction device (BRD) to exclude these fish; (iii) studied the hydrodynamic performance of a juvenile and trash excluder device (JTED) in a flume tank; and (iv) assessed the performance of this device under commercial fishing conditions. Based on the responses of 65 fishers to a questionnaire, we found that juvenile fish are now an important economic component of the total catch, and that fishers operating larger boats were more willing to use a JTED to exclude these fish than fishers operating smaller boats. The hydrodynamic study of a JTED identified the location of low-velocity regions around the device and codend, and this information can be used to identify the location of a secondary BRD to allow more fish to escape. The at-sea assessment of this device found that 73% of juvenile fish, 16% of valuable fish, and 8% of shrimp were excluded by the JTED, although most valuable fish and shrimp were smaller than the minimum legal landing size. Overall, this loss represents a 9% reduction in revenue. Yield-per-recruit analysis indicated that this could be offset by not catching fish less than the minimum legal landing size.
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9

Vitale, Sergio, Giacomo Milisenda, Michele Gristina, Pasquale Baiata, Sara Bonanomi, Francesco Colloca, Vita Gancitano, Danilo Scannela, Fabio Fiorentino, and Antonello Sala. "Towards more selective Mediterranean trawl fisheries: are juveniles and trash excluder devices effective tools for reducing undersized catches?" Scientia Marina 82, S1 (December 20, 2018): 215. http://dx.doi.org/10.3989/scimar.04751.28a.

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Mediterranean trawl fisheries are characterized by a critical combination of high fishing effort and low size at first capture for most commercial species. In this study we tested the use of sorting grids installed on bottom trawl nets to minimize the catch of undersized deep-water rose shrimp (Parapenaeus longirostris, DPS) and European hake (Merluccius merluccius, HKE). The catch of a traditional trawl net was compared with that obtained with the same net equipped with ad hoc designed juveniles and trash excluder devices (JTEDs) during an experimental survey. Three different JTEDs were tested: the first (G1-SM40) was built with a net of 40-mm square mesh; the second (G2-ST20) and third (G3-ST25) with vertical steel bars spaced 20 and 25 mm, respectively. The probability of retaining DPS and HKE by length class in trawl nets with and without JTED was analysed using generalized additive mixed models. With G1-SM40, the reduction of undersized individuals in the cod-end was about 60% and 44% for DPS and HKE, respectively. With G2-ST20, a 34% catch decrease of HKE individuals smaller than 20 cm total length was observed. A loss of marketable fractions of DPS was recorded with G1-SM40 (–25%) and G2-ST20 (30%). Finally, JTD G3-ST25 was efficient at reducing the catch of undersized specimens of DPS and HKE, but showed a higher loss of marketable fractions than the other JTEDs. Although further fishing trials would be required to maximize the sorting efficiency of the grids, the results obtained clearly indicated that grids can substantially reduce unwanted catches of undersized DPS and HKE in Mediterranean bottom trawl fisheries.
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Dunn, M. G., A. J. Baran, and J. Miatech. "Operation of Gas Turbine Engines in Volcanic Ash Clouds." Journal of Engineering for Gas Turbines and Power 118, no. 4 (October 1, 1996): 724–31. http://dx.doi.org/10.1115/1.2816987.

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Results are reported for a technology program designed to determine the behavior of gas turbine engines when operating in particle-laden clouds. There are several ways that such clouds may be created, i.e., explosive volcanic eruption, sand storm, military conflict, etc. The response of several different engines, among them the Pratt & Whitney JT3D turbofan, the Pratt & Whitney J57 turbojet, a Pratt & Whitney engine of the JT9 vintage, and an engine of the General Electric CF6 vintage has been determined. The particular damage mode that will be dominant when an engine experiences a dust cloud depends upon the particular engine (the turbine inlet temperature at which the engine is operating when it encounters the dust cloud), the concentration of foreign material in the cloud, and the constituents of the foreign material (the respective melting temperature of the various constituents). Further, the rate at which engine damage will occur depends upon all of the factors given above, and the damage is cumulative with continued exposure. An important part of the Calspan effort has been to identify environmental warning signs and to determine which of the engine parameters available for monitoring by the flight crew can provide an early indication of impending difficulty. On the basis of current knowledge, if one knows the location of a particle-laden cloud, then that region should be avoided. However, if the cloud location is unknown, which is generally the case, then it is important to know how to recognize when an encounter has occurred and to understand how to operate safely, which is another part of the Calspan effort.
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Dissertations / Theses on the topic "JT9D"

1

Boiani, Davide. "Finite element structural and thermal analysis of JT9D turbofan engine first stage turbine blade." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2017. http://amslaurea.unibo.it/12566/.

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The objective of this work was to conduct a preliminary finite element static structural and transient thermal analyses of a first stage turbine blade which was previously assembled on a Pratt & Whitney JT9D-7A turbofan engine. This turbine blade was obtained from a collector of aircraft scrap parts. After an extensive theoretical background on airbreathing jet engines and materials used for such components, the process behind the creation of a 3D model was explained. The laser scanning technique and a piezoeletric digitizer were employed to recreate the blade inside a 3D modelling software. The model was then imported into the finite element analysis software ANSYS; the analyses were performed, and the most interesting results were evaluated. The structural and thermal results were found to be congruous with the literature on similar applications of components with the same material, and appear to be a realistic representation of the blade behaviour inside the first stage turbine environment.
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Maresi, Michele. "Installazione motore FIAT 1300cc jtd per uso aeronautico." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2012. http://amslaurea.unibo.it/3957/.

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Paganelli, Alex. "Studio dell'installazione del motore 1.3 JTD su velivolo Cessna 172." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2012. http://amslaurea.unibo.it/3440/.

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Angelini, Fabio. "Studio e ottimizzazione per l'installazione del 1300 jtd su un velivolo stratosferico." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2013. http://amslaurea.unibo.it/5153/.

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Casadei, Stefano. "Studio e progettazione di un riduttore per velivolo leggero a motore 1.3 jtd." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2012. http://amslaurea.unibo.it/4197/.

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Огурцов, В. В., and V. V. Ogurtcov. "Управление разработкой и выведением на рынок нового продукта с учетом особенностей интернет-среды : магистерская диссертация." Master's thesis, б. и, 2020. http://hdl.handle.net/10995/93429.

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Разработать методические подходы и практический инструментарий для решения задач предприятий оказывающих информационно-консультационные услуги и управляющих разработкой продуктов. Методы исследования: В качестве методологического инструментария в данной работе были использованы: маркетинговые инструменты, в том числе традиционные подходы; инструменты проектного управления (Календарное планирование, методы оценки рисков, методы снижения рисков, метод структурной декомпозиция и т.д.); инструменты современных концепций интернет маркетинга Карта путешествия потребителя, метод JTBD, формула прибыли). Краткие выводы работы: В ходе работы разработан проект на основе нового метода «Карта путешествия потребителей», который будет использован при управлении процессом вывода на рынок нового продукта с сфере информационно-консультационных услуг. Данный проект может быть типовым для дальнейших новых проектов предприятия Деловой Квартал. Проект и его данные могут быть использованы другими компаниями, которые занимаются управленческой деятельностью по выводу на рынок новых продуктов в сфере информационно-консультационных услуг.
To develop methodological approaches and practical tools for solving the problems of enterprises providing information and consulting services and managing product development. Research methods: As the methodological tools in this work were used: - marketing tools, including traditional approaches; project management tools (scheduling, risk assessment methods, risk reduction methods, structural decomposition method, etc.); tools of modern concepts of internet marketing Consumer travel map, JTBD method, profit formula). Brief conclusions of the work: In the course of the work, a project was developed on the basis of the new method “Consumer Travel Map”, which will be used to manage the process of launching a new product on the market with information and consulting services. This project may be typical for further new projects of the Business Quarter enterprise. The project and its data can be used by other companies that are engaged in management activities to bring to the market new products in the field of information and consulting services.
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Wagner-Durand, Elisabeth [Verfasser], and Marlies [Akademischer Betreuer] Heinz. "Bilder im Kulturvergleich - Vorkommen und Verwendung von Bildern in verschiedenen Gesellschaften des Orients und Okzidents im 1. Jtd. v. Chr. (900-450 v. Chr.)." Freiburg : Universität, 2009. http://d-nb.info/1123480583/34.

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Books on the topic "JT9D"

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Vogt, Burkhard. Zur Chronologie und Entwicklung der Gräber des späten 4.-2. Jtsd. v. Chr. auf der Halbinsel Oman: Zusammenfassung, Analyse und Würdigung publizierter wie auch unveröffentlichter Grabungsergebnisse. Göttingen: [s.n.], 1985.

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Book chapters on the topic "JT9D"

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Schmitt, Rüdiger. "Magie in Syrien und Palästina/Israel im 2. und 1. Jtsd. v. Chr." In Ägyptische Magie und ihre Umwelt, 54–68. Harrassowitz, O, 2015. http://dx.doi.org/10.2307/j.ctvc2rjv4.6.

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Conference papers on the topic "JT9D"

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Irvine, Jeffrey D., Leonard M. Hampson, and Steven T. Rogers. "New Method for Turbine Blade Internal Cleaning." In ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/95-gt-426.

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A program was undertaken to develop an improved internal cleaning procedure for high pressure turbine blades. HP turbine blades, such as JT8D and JT9D 1st stage blades, experience a build up of Si-Ca rich dirt/debris during engine service that inhibits the flow of cooling air creating localized “hot spots”. These “hot spots” lead to accelerated internal corrosion that may cause through-wall material failure. Autoclave processes, utilizing heated, pressurized caustic, are ineffective at removing large amounts of internal debris. A new process, called the TURBO-CLEAN℠ process (patent pending), effectively removes large deposits of internal debris in as few as 2 hours. This process involves pumping heated caustic at pressures approaching 400psi through the internal cavities of turbine blades. The increased caustic flow from this process, compared to autoclave processes, improves cleaning effectiveness. This new process does not harm the parent material or damage protective aluminide coatings. The development of this process has led to reduced repair costs for JT8D 1st blades by improving part yield during repair.
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Eshraghi, Hamzeh, Ali Ghaseminezhad, Masoud Boroomand, and Abolghasem M. Tousi. "Thermodynamic Non-Dimensional Model to Estimate the Emitted Greenhouse Gases of a Turbofan Engine at Flight Altitude." In ASME 2014 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/imece2014-39748.

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Non-dimensional simulation models are often used to interpret experimental data in order to better understand the combustion processes. Recent investigation has presented a thermodynamic non-dimensional model which is used for evaluating the emitted greenhouse gases of a turbofan engine at flight altitude. Combustion chamber flow has been modeled as a non-dimensional flow in provided model. Required data for this model are combustion chamber inlet, turbine inlet and outlet together with exit nozzle pressure and temperature which are calculated by gas turbine non-dimensional modeling software. In this regard mass flow and rotational speed compatibility, conservation of mass and energy equations have been solved. (GSP and KineTechs software (chemical kinetic solving software) have been used for solving the mentioned equations as well as modeling the non-dimensional flow in the combustion chamber, respectively.) This paper investigates the JT9D engine. The results have been validated with experimental data published by International Civil Aviation Organization (ICAO). Noteworthy is that the obtained experimental data have been considered for low flight altitude phases and therefore the presented model takes into account the Greenhouse Gases estimation values for the mentioned phases. After result validation and conformity of experimental data, engine cruise altitude conditions have been modeled. Subsequently, New York – London airway has been studied and emitted Greenhouse gases quantity at cruise altitude has been calculated in one year while verified with published official Statistical data.
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Kennedy, Jan B., and Anthony J. Fiorentino. "Atomization and Combustion Characteristics of Antimisting Fuels Using JT8D and Air-Boost Injectors." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-223.

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An experimental evaluation of a bill-of-material JT8D injector, a low emission airblast JT8D injector, and an air-boost injector has been conducted at United Technologies Research Center to determine the atomization levels of antimisting fuels at operating conditions simulating engine conditions. In addition, Pratt & Whitney has evaluated the effects of using antimisting kerosene (AMK) on the performance of the components from the fuel system and the combustor of the current in-service JT8D aircraft engine. Spray characterization tests were conducted at ambient conditions using six different fuels, i.e. Jet A, one and three-pass JT8D fuel pump degraded, one and two-pass Gaulin degraded, and undegraded AMK fuels. The results of the tests indicated that the use of AMK fuel causes a noticeable decline in the quality of the spray and specifically a large increase in the Sauter Mean Diameter (SMD) for all three injectors. The undegraded AMK fuel resulted in a grossly incomplete atomization of the fuel with the spray being characterized by ligaments of fluid rather than droplets. In addition, the idle patternation data indicated that the low emission injector fuel distribution changed from a hollow cone Jet A spray with no fuel in the center to a semi-hollow spray cone using the 1- and 3-pass AMK, and this change could disrupt the primary zone recirculation pattern. Processing the AMK using the JT8D fuel pump as the degrader enhanced the atomization and spray quality, but combustion tests at P&WA using the JT8D degraded fuel indicated that the emissions levels produced were excessive and the lean blowout, relight and starting characteristics were somewhat deficient. The results from the spray quality and combustor performance tests coupled with the P&WA fuel component laboratory evaluations pointed out the need for extensive AMK degradation. Based on the levels of degradation required for successful cold filter tests and the transition velocities measured with Jet A fuel, AMK was processed with a Gaulin homogenizer to transition velocities of 5 and 9 cm/sec. Subsequent spray quality evaluations with these two levels of degraded fuels and Jet A using the JT8D airblast low emission fuel injector indicated that the gross characteristics of the Jet A and the degraded AMK fuels were similar. Perhaps even more important was the distribution data at idle, where the highly degraded fuels were almost indistinguishable from Jet A. Based on the early combustion results, it is implied that low power emissions might be very close to Jet A using the Gaulin degraded fuels.
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Dunn, Michael G., Adam J. Baran, and Jerry Miatech. "Operation of Gas Turbine Engines in Volcanic Ash Clouds." In ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1994. http://dx.doi.org/10.1115/94-gt-170.

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Results are reported for a technology program designed to determine the behavior of gas turbine engines when operating in particle-laden clouds. There are several ways that such clouds may be created, i.e., explosive volcanic eruption, sand storm, military conflict, etc. The response of several different engines, among them the Pratt & Whitney JT3D turbofan, the Pratt & Whitney J57 turbojet, a Pratt & Whitney engine of the JT9 vintage, and an engine of the General Electric CF6 vintage has been determined. The particular damage mode that will be dominant when an engine experiences a dust cloud depends upon the particular engine (the turbine inlet temperature at which the engine is operating when it encounters the dust cloud), the concentration of foreign material in the cloud, and the constituents of the foreign material (the respective melting temperature of the various constituents). Further, the rate at which engine damage will occur depends upon all of the factors given above and the damage is cumulative with continued exposure. An important part of the Calspan effort has been to identify environmental warning signs and to determine which of the engine parameters available for monitoring by the flight crew can provide an early indication of impending difficulty. On the basis of current knowledge, if one knows the location of a particle-laden cloud, then that region should be avoided. However, if the cloud location is unknown, which is generally the case, then it is important to know how to recognize when an encounter has occurred and to understand how to safely operate, which is another part of the Calspan effort.
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5

Monhardt, R. J., J. H. Richardson, and J. M. Boettcher. "Design and Test of the FT8 Gas Turbine Low Pressure Compressor." In ASME 1989 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1989. http://dx.doi.org/10.1115/89-gt-295.

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This paper presents a discussion of the design and test phases of the Low Pressure Compressor (LPC) used in the FT8 Gas Turbine. Design objectives, including efficiency, durability and stall margin goals are covered along with actual test results indicating successful accomplishment of these objectives. Unique features of the test program and an overview of the FT8 Gas Generator in comparison to the JT8D Aircraft Engine are also presented.
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Day, William H. "FT8: A High Performance Industrial and Marine Gas Turbine Derived From the JT8D Aircraft Engine." In ASME 1987 International Gas Turbine Conference and Exhibition. American Society of Mechanical Engineers, 1987. http://dx.doi.org/10.1115/87-gt-242.

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This paper describes the FT8 gas turbine, which has been introduced by Turbo Power and Marine Systems (TPM). The FT8 is derived from the Pratt & Whitney JT8D aircraft engine and the TPM FT4 industrial gas turbine. The FT8 has been launched with a collaboration program between TPM and the China National Aerotechnology Import-Export Corporation (CATIC) of the People’s Republic of China. The collaboration program includes co-production of certain components and a 37-unit order from CATIC over a 10-year period for marine and industrial applications.
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Ghenaiet, A. "An Approximate Method for Jet Engines Flight Performances Prediction." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0149.

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This paper describes a fast simulation procedure to predict airbreathing engines steady state flight performances. This procedure uses an alternate method that works without the need of component maps and the corresponding matching. This method operates on simplified assumptions, such as constant power setting, without air bleed or power extraction. This approximate method for flight performance prediction is validated for three types of jet engines such as the P&W JT8D mixed flows turbofan, the GE CF6-80 high bypass turbofan. and the Russian double spool turbojet R11F-300.
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8

Prario, Aldo, and Heinrich Voss. "FT8A, a New High Performance 25 MW Mechanical Drive Aero Derivative Gas Turbine." 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-287.

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This paper describes the FT8A, an advanced state of the art, high performance aeroderivative gas turbine under development for variable speed mechanical drive industrial applications. The gas generator, common to the recently developed FT8, is derived from the Pratt & Whitney JT8D-200 series aircraft engine. The power turbine is being designed and developed by Turbo Power and Marine Systems, Inc. (TPM) and MAN Gutehoffnungshütte AG (MAN GHH) under a joint collaboration program. The power turbine features a three stage rotor simply supported between antifriction bearings, advanced aerodynamics, and a low loss exhaust diffuser/collector system. Design features, performance and typical applications of the FT8A are presented.
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Boley, Warren M., and Thomas W. Prete. "FT8 Phase II Reliability Improvement Program." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-417.

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This paper describes the FT8 gas generator (GG8) development history, including required design modifications to the JT8D aircraft engine, initial field experience and the latest reliability improvements incorporated into the GG8. The modifications include improvements to bearing compartment operating temperature, bearing compartment seals, and increases to bearing life. Turbine durability improvements are also discussed. The incorporation and control of a cold air buffer system to control bearing compartment oil coke formation is provided. Improvements to bearing compartment carbon seals are reviewed and the benefits of this design are discussed. Rotor system thrust bearing life improvements are achieved through the incorporation of modified compressor seals and turbine aerodynamics.
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Kamachi, Masafumi, Yoichi Ishikawa, Nikolai Maximenko, Jan Hafner, Hideyuki Kawamura, and Amy MacFadyen. "Modeling the drift of Japan Tsunami Marine Debris (JTMD): An application of high computing simulation and data assimilation." In 2016 Techno-Ocean (Techno-Ocean). IEEE, 2016. http://dx.doi.org/10.1109/techno-ocean.2016.7890726.

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Reports on the topic "JT9D"

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Blaisdell, Robert P. System Specification (Type A) for the Joint Tactical Information Distribution System (JTIDS) Test Device (JTD). Fort Belvoir, VA: Defense Technical Information Center, April 1995. http://dx.doi.org/10.21236/ada293600.

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