Relevant bibliographies by topics / Turboprop transports

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

Academic literature on the topic 'Turboprop transports'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Turboprop transports"

1

Henderson, W. P. "Airframe/Propulsion Integration at Transonic Speeds." Journal of Engineering for Gas Turbines and Power 113, no. 1 (January 1, 1991): 51–59. http://dx.doi.org/10.1115/1.2906530.

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A significant level of research is ongoing at NASA’s Langley Research center on integrating the propulsion system with the aircraft. This program has included nacelle/pylon/wing integration for turbofan transports, propeller/nacelle/wing integration for turboprop transports, and nozzle/afterbody/empennage integration for high-performance aircraft. The studies included in this paper focus more specifically on pylon shaping and nacelle bypass ratio studies for turbofan transports, nacelle and wing contouring, and propeller location effects for turboprop transports, empennage effects, and thrust vectoring for high-performance aircraft. The studies were primarily conducted in NASA Langley’s 16-Foot Transonic Tunnel at Mach numbers up to 1.20.
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Čokorilo, Olja, Slobodan Gvozdenović, Petar Mirosavljević, and Ljubiša Vasov. "MULTI ATTRIBUTE DECISION MAKING: ASSESSING THE TECHNOLOGICAL AND OPERATIONAL PARAMETERS OF AN AIRCRAFT." TRANSPORT 25, no. 4 (December 31, 2010): 352–56. http://dx.doi.org/10.3846/transport.2010.43.

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Regional aircraft are playing a significant role in airline operations. This paper considers the problem of selecting an appropriate aircraft from the airline fleet for optimal regional air travel realization. Complexity balance between air travel demand (passengers, goods) and the proposed aircraft capacity presents the priority in airline operations. A principal feature of the methodology considered in this paper is a multi attribute analysis of technological and operational aircraft characteristics (turboprop and turbojet). A comparison of the presented regional aircraft parameters is based on the following criteria: technological (aerodynamic efficiency, structural efficiency, fuel flow at the optional FL, cruise endurance and requested trip fuel for the fixed cruise range), operational (max range with max payload, ground efficiency (aircraft maintainability based on external dimensions) and climb capability. With the aim of defining aircraft rank, the TOPSIS (Technique for Order Preference by Similarity to Ideal Solution) method was applied. Therefore, the Saaty scale was used for developing the weight of different criteria. The conducted research included a sample of four representative regional aircraft: Do328, CRJ100er, Saab2000 and ERJ145. The results obtained would help in determining the airline fleet or selecting the optional solution from the existing fleet.
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Lange, Roy H. "A review of advanced turboprop transport aircraft." Progress in Aerospace Sciences 23, no. 2 (January 1986): 151–66. http://dx.doi.org/10.1016/0376-0421(86)90003-5.

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Bakunowicz, Jerzy. "Single engine turboprop aeroplane class in small air transport." Aircraft Engineering and Aerospace Technology 90, no. 7 (October 1, 2018): 1033–41. http://dx.doi.org/10.1108/aeat-01-2017-0009.

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Purpose This paper aims to present the analysis of introduction of single engine turbo-prop aeroplane class in terms of certification specifications and flight crew licensing regulations. Design/methodology/approach Following the results of flight testing and additional performance and sizing calculations, the proposed class was placed among the existing aeroplane taxonomy in terms of performance, flight loads, mass penalty, fuel economy and several other factors. Concerning small air transport initiative, the new class was tried to be placed as a starting point in commercial pilot career. Findings The paper points the potential market for single engine turbopropeller aeroplanes and lists today obstacles in wider introduction. Therefore, remarks about required change of regulations and requirements for design process, as well as for crew licensing, are underlined. Practical implications The results of the study would be helpful in preliminary design of a new low-power turboprop aeroplane, as well as during tailoring the certification specifications. Originality/value The approach presented in this paper is a detailed extension of an original idea presented by author for the first time during Clean Sky/small air transport workshop.
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Жорник, Олег Володимирович, Ігор Федорович Кравченко, and Михайло Михайлович Мітрахович. "Удосконалення характеристик кільцевого вхідного пристрою авіаційної силової установки з гвинтовентилятором." Aerospace technic and technology, no. 4sup2 (August 27, 2021): 11–18. http://dx.doi.org/10.32620/aktt.2021.4sup2.02.

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The article considers the method of improving the characteristics of the ring inlet device, taking into account the influence of the propeller of an aircraft power plant with a turboprop engine. It is shown that increasing the total pressure loss in the inlet device by 5% increases, approximately, the specific fuel consumption by 3% and reduces engine thrust by 6%, and uneven flow at the inlet to the engine is the cause of unstable compressor of the turboprop engine. It is proposed to improve the characteristics of the input device by modifying the shape of its shell and channel. Evaluation of the influence of the shape of the shell and the channel of the annular axial VP on its main aerodynamic characteristics, taking into account the non-uniformity of the flow on the fan in the calculated mode of operation of the SU is carried out by calculating the full pressure recovery factor. The object of the study is an annular axial input device in front of which is a coaxial fan turboprop fan. The process of modeling the influence of the shape of the shell and the channel on the recovery factor of total pressure, circular and radial non-uniformity of the flow through the input device is implemented in the software system of finite element analysis ANSYS CFX. Geometric models of coaxial screw fan, fairing and inlet device are built in ANSYS SpaceClaim and transferred using the built-in import function in ANSYS Workbench. Block-structured grid models of air propellers of the first and second rows of the fan in the amount of 1.9 million, fairing and inlet device, in the amount of 3.9 million, are built in the ANSYS TurboGrid environment. The standard Stern (Shear Stress Transport) Gamma Theta Transition was used to close the Navier-Stokes equation system. Based on the results of mathematical modeling of flow in coaxial fans and subsonic ring inlet device on the maximum cruising mode of the turboprop engine, the full pressure recovery factor is calculated and it is established that the most influential factor that increases its full pressure recovery factor.
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MacLeod, J. D., and J. C. G. Laflamme. "Compressor Coating Effects on Gas Turbine Engine Performance." Journal of Engineering for Gas Turbines and Power 113, no. 4 (October 1, 1991): 530–34. http://dx.doi.org/10.1115/1.2906273.

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In an attempt to increase the time between maintenance actions and to improve performance retention of turboprop engines installed in transport and maritime patrol aircraft, the Canadian Department of National Defence is evaluating an erosion and corrosion-resistant blade coating, for use on compressors. As coatings could appreciably alter engine performance by virtue of their application thickness and surface quality, the National Research Council of Canada was asked to quantify any performance changes that could occur. A project was initiated, utilizing a new Allison T56 turboprop engine, to assess not only the performance changes resulting from the coating, but also those from dismantling and reassembling the compressor, since the compressor must be completely disassembled to apply the coating. This paper describes the project objectives, the experimental installation, and the measured effects of the coating application on compressor performance. Performance variations due to compressor rebuilds on both engine and compressor characteristics are discussed. As the performance changes were small, a rigorous measurement uncertainty analysis is included. The coating application process and the affected overhaul procedures are examined. The results of the pre- and postcoating compressor testing are presented, with a discussion of the impact on engine performance.
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PAČAIOVÁ, Hana, Marianna TOMAŠKOVÁ, Michaela BALÁŽIKOVÁ, and Jozef KRAJŇÁK. "Analysis of air-traffic threats." Scientific Journal of Silesian University of Technology. Series Transport 110 (March 1, 2021): 143–55. http://dx.doi.org/10.20858/sjsutst.2021.110.12.

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Globally, air transport has seen a greater increase in recent years. This manuscript is divided into three parts for analysing the negative effects of aviation. The first part is focused on the identification of sources of aircraft noise. While the second part of this article describes the basic principles of the construction and operation of an aircraft jet engine concerning the gaseous emissions produced by such an engine (Third part missing?). The main benefit of this article is the evaluation of the reliability of the human factor because the human factor is an integral part of technical systems and processes. Reliability assessment was performed using the TESEO method. The ergonomic parameter, that is, the cabin noise, was quantified in the given method. The measurement was performed on two types of aircraft, namely in the cabin of a transport jet aircraft and in the cabin of asmall transport aircraft equipped with turboprop engines.
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Nicolosi, Fabrizio, Danilo Ciliberti, Pierluigi Della Vecchia, Salvatore Corcione, and Vincenzo Cusati. "A comprehensive review of vertical tail design." Aircraft Engineering and Aerospace Technology 89, no. 4 (July 3, 2017): 547–57. http://dx.doi.org/10.1108/aeat-11-2016-0213.

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Purpose This work aims to deal with a comprehensive review of design methods for aircraft directional stability and vertical tail sizing. The focus on aircraft directional stability is due to the significant discrepancies that classical semi-empirical methods, as USAF DATCOM and ESDU, provide for some configurations because they are based on NACA wind tunnel (WT) tests about models not representative of an actual transport airplane. Design/methodology/approach The authors performed viscous numerical simulations to calculate the aerodynamic interference among aircraft parts on hundreds configurations of a generic regional turboprop aircraft, providing useful results that have been collected in a new vertical tail preliminary design method, named VeDSC. Findings The reviewed methods have been applied on a regional turboprop aircraft. The VeDSC method shows the closest agreement with numerical results. A WT test campaign involving more than 180 configurations has validated the numerical approach. Practical implications The investigation has covered both the linear and the non-linear range of the aerodynamic coefficients, including the mutual aerodynamic interference between the fuselage and the vertical stabilizer. Also, a preliminary investigation about rudder effectiveness, related to aircraft directional control, is presented. Originality/value In the final part of the paper, critical issues in vertical tail design are reviewed, highlighting the significance of a good estimation of aircraft directional stability and control derivatives.
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CHIESA, Sergio, Marco FIORITI, and Roberta FUSARO. "POSSIBLE HYBRID PROPULSION CONFIGURATION FOR TRANSPORT JET AIRCRAFT." Aviation 20, no. 3 (September 29, 2016): 145–54. http://dx.doi.org/10.3846/16487788.2016.1200849.

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This research is aimed at studying the possible advantages of installing, for a hybrid propulsion aircraft, electric motors and related propellers into the dedicated supplementary nacelles. This innovative solution is different from the configuration, already studied for a regional turboprop (Chiesa et al.2013), in which the electric motors are in the same nacelles of the internal combustion engines. As it has been expected, it offers the advantages of avoiding mechanical links between the two units and, more importantly, can also be applied to jet aircraft. In fact, the main contribution of electric motors is expected during ground operations, take-off and descent phases (i.e. at low speed), in which it can be useful to integrate the propellers or even substitute the jet engines with them. At high speed, the propellers, of course, are configured in order to reduce drag. When considering the design of a new airliner concept, a preliminary design study is necessary to optimize the location of the supplementary nacelles. The nacelles, which only hold the electrical motor, can also be considered retractable, as is usual for a RAT (Ram Air Turbine). Please note that in the hybrid propulsion context, the RAT function can be clearly allocated to the electric motor, with the advantages of optimizing drag at high speed, taking into account installation problems.
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Yoshikawa, Hiroyuki, Terukazu Ota, Kazuyuki Higashino, and Shunichiro Nakai. "Numerical Analysis on Dynamic Characteristics of Cryogenic Hydrostatic Journal Bearing." Journal of Tribology 121, no. 4 (October 1, 1999): 879–85. http://dx.doi.org/10.1115/1.2834150.

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Dynamic characteristics of a two row staggered recess cryogenic hydrostatic journal bearing used in the liquid hydrogen turbopump of rocket engines for space transport systems are numerically analyzed. Effects of the rotational speed and the shaft eccentricity are studied in the analysis. Their effects on the stiffness and damping coefficients and the whirl frequency ratio are clarified. Moreover, effects of the orifice parameter, the distance between two recess rows, and the number of recesses on these dynamic characteristics are investigated.
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Dissertations / Theses on the topic "Turboprop transports"

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Wilhelm, Jay Paul. "Aircraft intercom system design for Project Oculus." Morgantown, W. Va. : [West Virginia University Libraries], 2005. https://etd.wvu.edu/etd/controller.jsp?moduleName=documentdata&jsp%5FetdId=3841.

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Thesis (M.S.)--West Virginia University, 2005.
Title from document title page. Document formatted into pages; contains ix, 89 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 58-59).
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Duff, Jonathan B. "A service life analysis of U.S. Coast Guard C-130 aircraft." View report, 2003. http://handle.dtic.mil/100.2/ADA413132.

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Thesis (M.S.)--Air Force Institute of Technology, 2003.
Title from title screen (viewed May 10, 2004). "March 2003." Vita. "AFIT/GAQ/ENS/03-02." "ADA413132"--URL. Includes bibliographical references (leaves 132-135). Also issued in paper format.
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Wowczuk, Zenovy S. "Design validation methodology development for an aircraft sensor deployment system." Morgantown, W. Va. : [West Virginia University Libraries], 2008. http://hdl.handle.net/10450/5657.

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Thesis (Ph. D.)--West Virginia University, 2008.
Title from document title page. Document formatted into pages; contains xv, 294 p. : ill. (some col.). Includes abstract. Includes bibliographical references.
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Hayes, Robert Paul. "Control system design for a C-130 ro-ro sensor deployment platform." Morgantown, W. Va. : [West Virginia University Libraries], 2004. https://etd.wvu.edu/etd/controller.jsp?moduleName=documentdata&jsp%5FetdId=3611.

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Thesis (M.S.)--West Virginia University, 2004.
Title from document title page. Document formatted into pages; contains xi, 190 p. : ill. (some col.). Vita. Includes abstract. Includes bibliographical references (p. 116-119).
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Williams, Kenneth A. "A rotational arm connection point design for a C-130 aircraft standardized sensor platform." Morgantown, W. Va. : [West Virginia University Libraries], 2006. https://eidr.wvu.edu/etd/documentdata.eTD?documentid=4703.

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Thesis (M.S.)--West Virginia University, 2006.
Title from document title page. Document formatted into pages; contains viii, 77 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 58-59).
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Verlut, Grégoire [Verfasser]. "On-board Low-level Flight Planning for Turboprop Transport Aircraft / Grégoire Verlut." Aachen : Shaker, 2010. http://d-nb.info/112086402X/34.

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Hugo, David. "Olika motortypers påverkan på Sveriges transportflygskapacitet : En komparativ analys av Lockheed Martin C-130J Super Hercules och Embraer KC-390." Thesis, Försvarshögskolan, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:fhs:diva-7445.

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Sverige har idag några av Europas äldsta militära transportflygplan av typen TP 84 Lockheed Martin C-130H Hercules. Försvarsmakten har beslutat om att modifiera flygplanen så att de kan fortsätta att flyga fram till 2030 men på sikt måste ett nytt system köpas in. Uppsatsen avhandlar det beprövade flygplanet Lockheed Martin C-130J mot det nya Embraer KC-390. Analysen avhandlar en komparativ jämförelse mellan två olika transportflygplan samt systemens införande i Försvarsmakten. Fallet är en del av en jämförelse mellan flygplanen med turboprop-och turbofläktmotorer. Jämförelsen kommer att kopplas mot Andersson et al:s teori om militär nytta. Slutsatserna från analysen är att vid ett införande av C-130J kommer ett driftsäkert system med lång erfarenhet av att operera i konfliktzoner med provisoriska landningsbanor tillföras Försvarsmakten. Flygplanets prestanda och begränsningar är redan kända. Vid införandet av KC- 390 är uppgifterna om prestanda och begränsningar en osäkerhet då systemet ännu inte är i tjänst. Osäkerheter som förmågan att operera från provisoriska flygfält måste tas i beaktande. Dock är flygplanet bättre avseende räckvidd, lastkapacitet samt hastighet, detta på grund av flygplanets turbofläktmotorer.
This thesis considers the problem of Sweden currently having some of Europe's oldest military Hercules transport aircraft of the type TP 84 Lockheed Martin C-130H Hercules. The Swedish Armed Forces have decided to modify the aircraft to extend it to 2030, but in the long term a new system must be procured. This thesis deals with the proven aircraft Lockheed Martin C-130J compared to the new Embraer KC-390. The approach uses Andersson et al's theory of military utility to compare two different transport aircraft as well as the system's introduction into the Swedish Armed Forces. The case is part of a comparison of aircraft with turboprop against turbofan engines. The conclusions from the analysis are that the C-130J is an operational system with long experience of operating in conflict zones from provisional runways, and the aircraft's performance and limitations are already known. With the KC-390, performance and limit data are an uncertainty whilst the system is not yet in service; as is its ability to operate from temporary airports. However, this aircraft is better in terms of range, load capacity and speed, due to the aircraft's turbofan engines.
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Books on the topic "Turboprop transports"

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Workhorse props: Prop aircraft around the world. Osceola, WI: Motorbooks International, 1995.

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Conklin & deDecker Associates. The aircraft comparator: Turboprops. Orleans, Mass. (P.O. Box 1142, Orleans 02653): Conklin & deDecker Associates, 1996.

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Laming, Tim. Hercules: The C130 in action. Osceola, WI: Motorbooks International, 1992.

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Morris, M. E. C-130, the hercules. London: Arms and Armour, 1989.

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C-130, the Hercules. Novato, Calif: Presidio Press, 1989.

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Lockheed C-130 Hercules. Ramsbury, Marlborough, Wiltshire: Crowood Press, 1999.

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Mighty Hercules: The first four decades. Fairford: Royal Air Force Benevolent Fund Enterprises, 1994.

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Leader, Ray. Colors & markings of the C-130 Hercules. Blue Ridge Summit, PA: Tab Books, 1987.

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RAF Lyneham: Hercules super station in action. Sparkford, Nr Yeovil, Somerset: Haynes, 1990.

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Smith, Peter Charles. Lockheed C-130 Hercules: The world's favorite military transport. Shrewsbury: Airlife, 2001.

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Conference papers on the topic "Turboprop transports"

1

Henderson, William P. "Airframe/Propulsion Integration at Transonic Speeds." 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-338.

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A significant level of research is ongoing at NASA’s Langley Research center on integrating the propulsion system with the aircraft. This program has included nacelle/pylon/wing integration for turbofan transports, propeller/nacelle/wing integration for turboprop transports, and nozzle/afterbody/empennage integration for high performance aircraft. The studies included in this paper focus more specifically on pylon shaping and nacelle bypass ratio studies for turbofan transports, nacelle and wing contouring and propeller location effects for turboprop transports, empennage effects, and thrust vectoring for high performance aircraft. The studies were primarily conducted in NASA Langley’s 16-Foot Transonic Tunnel at Mach numbers up to 1.20.
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Marcellan, A., W. P. J. Visser, and P. Colonna. "Potential of Micro Turbine Based Propulsion Systems for Civil UAVs: A Case Study." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-57719.

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There is a high potential for civil applications of Unmanned Aerial Vehicles (UAV) in areas such as goods transport, telecommunication, remote monitoring and sensing, surveillance, search and rescue, and disaster management. Developments in areas such as telecommunication, control and information technology offer opportunities for long range remotely or automatically piloted missions. This requires efficient and light-weight small propulsion systems. The potential of turboprop propulsion for civil UAVs using micro turbine technology has been explored and compared with existing concepts, such as piston engine driven propellers. Different propulsion concepts have been analyzed and the application areas where advanced turboprops would be superior to other systems such as reciprocating engines and electric motors, identified. However, turboprop engines of the small power capacity required for the aircraft concepts and missions considered are not currently available with competitive performance. A conceptual design study of a micro turboprop engine has been performed by downscaling an existing reference engine. Scale effects on efficiency have been taken into account, as well as effects of technological progress. Engine cycle optimization has been carried out and the effects of turbine inlet temperature, compressor pressure ratio, engine size, and component efficiency have been investigated. An aerodynamic and flight performance model of a baseline UAV has been developed in order to predict mission performance. This model has been coupled to a turboprop model to evaluate system performance with different engine configurations for the selected mission. The outcome of the study provides information about the technological improvements in terms of cycle efficiency required to make the micro-turboprop a competitive solution. The Propulsion and Power group of Delft University of Technology will pursue these R&D goals in an attempt to contribute to the development of civil UAV technology.
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Lan, Chuan-Tau, and Michael Guan. "Flight Dynamic Analysis of a Turboprop Transport Airplane in Icing Accident." In AIAA Atmospheric Flight Mechanics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-5922.

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Sachau, Delf, Kay Kochan, and Harald Breitbach. "Active Noise Control inside the Loadmaster Area of a Turboprop Transport Aircraft." In 15th AIAA/CEAS Aeroacoustics Conference (30th AIAA Aeroacoustics Conference). Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-3244.

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Ibrahim, Kottakota. "Selecting Principal Parameters of Baseline Design Configuration for Twin Turboprop Transport Aircraft." In 22nd Applied Aerodynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-5069.

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Crider, Dennis, and John Foster. "Simulation Modeling Requirements for Loss-of-Control Accident Prevention Of Turboprop Transport Aircraft." In AIAA Modeling and Simulation Technologies Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-4569.

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Hui, Kenneth, Mengistu Wolde, Anthony Brown, George Isaac, and Stewart Cober. "Flight Dynamics Model of Turboprop Transport Aircraft Icing Effects Based on Preliminary Flight Data." In 43rd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-1068.

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Brown, Anthony. "An Investigation into the Identification of Net Installed Propulsive Efficiency on a Turboprop Transport Aeroplane." In AIAA Atmospheric Flight Mechanics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-4940.

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Brown, Anthony. "AIRS II Flight Determination of Turboprop Transport Aeroplane Lift, Drag, and Propulsive Effiency Effects in Freezing Drizzle Icing." In AIAA Atmospheric Flight Mechanics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-4949.

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BARLAND, E. "Reducing landing dispersions through flight control improvements on a turboprop-powered transport aircraft (The Lockheed High Technology Test Bed)." In Guidance, Navigation and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1850.

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