Log in

Relevant bibliographies by topics / Turboprop engines

Contents

Journal articles
Dissertations / Theses
Books
Book chapters
Conference papers

Academic literature on the topic 'Turboprop engines'

Author: Grafiati

Published: 4 June 2021

Last updated: 7 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Turboprop engines.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Turboprop engines"

1

Filippone, A., and Z. Mohamed-Kassim. "Multi-disciplinary simulation of propeller-turboprop aircraft flight." Aeronautical Journal 116, no. 1184 (2012): 985–1014. http://dx.doi.org/10.1017/s0001924000007454.

Full text

Abstract:

Abstract This contribution presents a novel simulation for a fixed-wing aircraft powered by gas turbine engines and advanced propellers (turboprops). The work is part of a large framework for the simulation of aircraft flight through a multi-disciplinary approach. Novel numerical methods are presented for flight mechanics, turboprop engine simulation (in direct and inverse mode), and propeller dynamics. We present in detail the integration of the propeller with the airframe, aircraft and tonal noise model. At the basic level, we address a shortfall in multi-disciplinary integration in turboprop-powered aircraft, including economical operations and environmental emissions (exhausts and noise). The models introduced are based on first principles, supplied with semi-empirical correlations, if required. Validation strategies are presented for component-level analysis and system integration. Results are presented for aerodynamics, specific air range, optimal cruise conditions, payload-range performance, and propeller noise. Selected results are shown for the ATR 72-500, powered by PW127M turboprop engines and F568-1 propellers.

APA, Harvard, Vancouver, ISO, and other styles

2

Saravanamuttoo, H. I. H. "Modern turboprop engines." Progress in Aerospace Sciences 24, no. 3 (1987): 225–48. http://dx.doi.org/10.1016/0376-0421(87)90008-x.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Nicolosi, Fabrizio, Salvatore Corcione, Vittorio Trifari, and Agostino De Marco. "Design and Optimization of a Large Turboprop Aircraft." Aerospace 8, no. 5 (2021): 132. http://dx.doi.org/10.3390/aerospace8050132.

Full text

Abstract:

This paper proposes a feasibility study concerning a large turboprop aircraft to be used as a lower environmental impact solution to current regional jets operated on short/medium hauls. An overview of this market scenario highlights that this segment is evenly shared between regional turboprop and jet aircraft. Although regional jets ensure a large operative flexibility, they are usually not optimized for short missions with a negative effect on block fuel and environmental impact. Conversely, turboprops represent a greener solution but with reduced passenger capacity and speed. Those aspects highlight a slot for a new turboprop platform coupling higher seat capacity, cruise speed and design range with a reduced fuel consumption. This platform should operate on those ranges where neither jet aircraft nor existing turboprops are optimized. This work compares three different solutions: a high-wing layout with under-wing engines installation and both two- and three-lifting-surface configurations with low-wing and tail tips-mounted engines. For each concept, a multi-disciplinary optimization was performed targeting the minimum block fuel on a 1600 NM mission. Optimum solutions were compared with both a regional jet such as the Airbus A220-300 operated on 1600 NM and with a jet aircraft specifically designed for this range.

APA, Harvard, Vancouver, ISO, and other styles

4

Skliros, Christos. "A CASE STUDY OF VIBRATION FAULT DIAGNOSIS APPLIED AT ROLLS-ROYCE T-56 TURBOPROP ENGINE." Aviation 23, no. 3 (2020): 78–82. http://dx.doi.org/10.3846/aviation.2019.11900.

Full text

Abstract:

Gas turbine engines include a plethora of rotating modules, and each module consists of numerous components. A component’s mechanical fault can result in excessive engine vibrations. Identification of the root cause of a vibration fault is a significant challenge for both engine manufacturers and operators. This paper presents a case study of vibration fault detection and isolation applied at a Rolls-Royce T-56 turboprop engine. In this paper, the end-to-end fault diagnosis process from starting system faults to the isolation of the engine’s shaft that caused excessive vibrations is described. This work contributes to enhancing the understanding of turboprop engine behaviour under vibration conditions and highlights the merit of combing information from technical logs, maintenance manuals and engineering judgment in successful fault diagnosis.

APA, Harvard, Vancouver, ISO, and other styles

5

GĘCA, Michał, Zbigniew CZYŻ, and Mariusz SUŁEK. "Diesel engine for aircraft propulsion system." Combustion Engines 169, no. 2 (2017): 7–13. http://dx.doi.org/10.19206/ce-2017-202.

Full text

Abstract:

Stricter requirements for power in engines and difficulties in fueling gasoline engines at the airport make aircraft engine manufac-turers design new engines capable of combusting fuel derived from JET-A1. New materials used in compression-ignition engines enable weight reduction, whereas the technologies of a Common Rail system, supercharging and 2-stroke working cycle enable us to increasethe power generated by an engine of a given displacement. The paper discusses the parameters of about 40 types of aircraft compression ignition engines. The parameters of these engines are compared to the spark-ignition Rotax 912 and the turboprop. The paper also shows trends in developing aircraft compression-ignition engines.

APA, Harvard, Vancouver, ISO, and other styles

6

Rabeta, Bismil, Mohammad A.F Ulhaq, Aswan Tajuddin, and Agus Sugiharto. "Simulasi Graphical User Interface Analisis Termodinamika Mesin Turboprop Menggunakan Perangkat Lunak Matlab R2020a." Jurnal Teknologi Kedirgantaraan 6, no. 2 (2021): 31–50. http://dx.doi.org/10.35894/jtk.v6i2.44.

Full text

Abstract:

A turboprop engine is a hybrid engine that delivers thrust or jet thrust and also drives the propeller. This is basically similar to a turbojet except the turbine works through the main shaft which is connected to the reduction gear to rotate the propeller in front of the engine. This research was conducted to determine the development of engine performance in thermodynamic analysis so as to know the value of each parameter on a engine that has been developing for 20 to 50 years with different engine manufacturing. So that in this study a comparison of the thermodynamic analysis of the TPE-331, PT6A-42 and H85-200 engines was carried out. In the TPE331-10, PT6A-42, and H85-200 turboprop engines the value of fuel to air ratio and shaft work increases with increasing altitude while compressor work, fuel flow rate, shaft power, propeller thrust, jet thrust, total thrust, equivalent engine power and ESFC decrease with increasing altitude. Furthermore, the turbine's working value is relatively stable as the altitude increases. After that, the value of compressor work and turbine work on the PT6A-42 engine was greater than that of the TPE331-10, and H85-200 engines. However, the value of the fuel to air ratio, fuel flow rate, shaft power, jet thrust, equivalent engine power and ESFC on the H85-200 engine was greater than the TPE331-10 and PT6A engines. Furthermore, at sea level, the value of the axle, propeller thrust, and total thrust on the H85-200 engine is greater than that of the TPE331-10 and PT6A-42 engines but at an altitude of 25,000 ft, the PT6A-4 engine has a greater value than that of the TPE331-10 and PT6A-42 engines. TPE331-10, and H85-200 engines.

APA, Harvard, Vancouver, ISO, and other styles

7

Spychała, Jarosław, Paweł Majewski, and Mariusz Żokowski. "The Use of the Vibroacoustic Method for Monitoring the Technical Condition of Aero Engines with Extended Time between Overhauls." Solid State Phenomena 220-221 (January 2015): 283–88. http://dx.doi.org/10.4028/www.scientific.net/ssp.220-221.283.

Full text

Abstract:

The article presents some aspects of several years of work on the use of the vibroacoustic method (Non-Destructive Testing) for assessing a turboprop engine from a trainer aircraft. The functioning engine does not have an operating system for measuring vibration, and therefore the current levels of vibrations and its changes in trends are not known. In order to extend its service life, performing a number of works was required. On the basis of assessing the current state of the engine, opportunities for further exploitation were identified thus developing methodology for evaluating technical condition regarding the whole population. The paper shortly describes the object and equivalent tests on the engine. The article focuses on the methods prepared for extending life between overhauls required for turboprop engines and discusses the results received during their implementation.

APA, Harvard, Vancouver, ISO, and other styles

8

Langston, Lee S. "Not So Simple Machines." Mechanical Engineering 135, no. 01 (2013): 30–35. http://dx.doi.org/10.1115/1.2013-jan-3.

Full text

Abstract:

This article talks about evolving technologies in making efficient gears for different auto engines. Gears are integral to a new engine that has the potential to change commercial aviation. Pratt & Whitney’s geared turbofan (GTF) jet engine will have significantly better fuel economy and much quieter operation. The P&W GTF combines existing jet engine technology with the well-established mechanical engineering technology of gears. Due to its high bypass ratio, the geared turbofan engine is 16% more efficient than standard jet engines. A key facility for developing the GTF gearbox has been a specially designed four-square gear test rig at P&W’s Middletown plant. The orientation of the GTF test gearboxes can be adjusted with respect to gravity to simulate different flight conditions. After an extensive program using a four-square rig and a long history of gearbox experience associated with their very popular turboprop gas turbines at Pratt & Whitney Canada, P&W engineers are convinced their new GTF engines will have a bright future.

APA, Harvard, Vancouver, ISO, and other styles

9

Wandini, Ratna Ayu, Taufiq Mulyanto, and Hari Muhammad. "Estimation of Lateral/Directional Static Stability Characteristics of a Turboprop Aircraft at one Engine Inoperative Condition." Applied Mechanics and Materials 842 (June 2016): 208–16. http://dx.doi.org/10.4028/www.scientific.net/amm.842.208.

Full text

Abstract:

Twin engines turboprop aircraft provides the most beneficial solution to meet the needs of short distance flight due to high fuel efficiency [1]. One of the emergency conditions which has to be considered for this type of the aircraft when one engine is out operating or one engine inoperative because it involves the safety of flight. Furthermore, a safe flight with one engine inoperative is regulated by FAR/CASR Part 25 and has to be complied during certification .Stability and control characteristics of a turboprop aircraft will change significantly if one engine inoperative condition occurs during cruise phase. The rudder and/or aileron deflections to counter the yawing and rolling moments due to the thrust of the operating engine must satisfy. Recognizing the importance of that consideration, this research will estimate the stability and control characteristics of lateral/directional in one engine inoperative condition on new turboprop 80-pax aircraft design concept.This paper presents procedures for estimating the lateral/directional static stability characteristics of a 80-pax turboprop aircraft during the conceptual design phase. The size of the rudder and aileron have to be iterated to fullfil the requirements at a condition when one engine is not operative. The rudder and the aileron deflections are estimated as functions of airspeed, roll angle, side slip angle and thrust setting. It will be shown in this paper that the required rudder deflection as well as aileron deflection can satisfy to balance the forces and moments due to asymmetrical thrust condition and the minimum control speed of the aircraft can be maintained as well.

APA, Harvard, Vancouver, ISO, and other styles

10

Ранченко, Геннадий Степанович, Анна Григорьевна Буряченко, Вячеслав Михайлович Грудинкин та Всеволод Владимирович Данилов. "БАЗОВОЕ ИСПОЛНЕНИЕ РЕГУЛЯТОРА АВИАДВИГАТЕЛЯ И ЕГО МОДИФИКАЦИИ". Aerospace technic and technology, № 8 (31 серпня 2020): 160–65. http://dx.doi.org/10.32620/aktt.2020.8.21.

Full text

Abstract:

It is shown that the creation of a unified electronic control and control equipment for aircraft gas turbine engines is one of the determining trends in the experimental design work of enterprises developing components of aircraft equipment. The results of the creation of some helicopter and aircraft engine controllers (turboshaft and turboprops) in JSC Element are presented. The basic model for them was the regulator RDC-450М (category A component product according to AP-21 classification), which was developed for the AI-450M family of turboshaft engines of Мi-2M and Mi-2MSB and in 2014 received the APPLIANCE DESIGN APPROVAL. There is given information concerning the mass-produced regulator RDTs-450M rework to meet the new requirements specified by the engine designer as the results of certification tests of the AI-450M engine and state tests of the Mi-2M and Mi-2MSB helicopters. It is shown that the rework was carried out taking into account the maximum possible “modifiability” of the regulator, which is the maximum ease of its adaptation in the future to new requirements, including requirements for working with other types of engines, including turboprops. The modular principle of constructing the functional structure and design of the regulator is described; its structural scheme is given. Data are given on the results of equivalent cyclic tests of the regulator RDTs-450M, which was modified to meet the new requirements, and on subsequent work on its adaptation to monitor and regulate the modes of turboprop aircraft engines AI-450C (including its modifications) and MS-500V-02S. Information is given on the newly developed regulators RDTs-450M-S, RDTs-450M-S-1, RDTs-450M-S-T-P, RDTs-450S-500, among which there is an engine regulator designed for an unmanned aerial vehicle. It is noted that the modular design assumes the presence of a significant number of board-to-board connections, and the prospects of increasing the reliability of regulator having a modular design by using the technology of flexible-rigid boards are described.

APA, Harvard, Vancouver, ISO, and other styles

Dissertations / Theses on the topic "Turboprop engines"

1

Jamonet, Laurent 1978. "Testing of a microrocket engine turbopump." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/8129.

Full text

Abstract:

Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2002.<br>Includes bibliographical references (p. 191-194).<br>Advances in microfabrication suggest its application to rocket engines. A MEMS thrust chamber producing 50 N of thrust at design point was previously developed that requires propellants pressurized as high as 300 atmospheres. Hence the need for turbopumps at the MEMS scale. A demonstration microturbopump approximately 20x20x6mm in size was designed and built using silicon microfabrication technology. Nitrogen and deionized water are used as operating fluids in the turbine and in the pump respectively. The design speed is 750,000 RPM, with a 23 atmospheres pump pressure rise, and an overall 30% turbomachinery efficiency. This thesis addresses the key points of the turbopump design, modelling, fabrication, and testing. A 3D CFD simulation of the pump was run and performance predicted. Cavitation risk was shown to be small. A fabrication process flow was set up and continuously improved using the feedback from experiments. Non-destructive fabrication inspection methods were introduced. A test rig and a packaging were built, on which 13 turbopumps have been tested, 8 of them spinning. The maximum speed reached was 100,000 RPM without pump loading, and 65,000 RPM with pump loading. Structural concerns have been addressed. Rotordynamics issues have been investigated. Pumping tests were performed and have paved the way toward an effective pressure rise. The innovative rotor arrangement with coplanar pump and turbine was validated. Dual phase operation involving water and nitrogen as running fluids was achieved successfully.<br>by Laurent Jamonet.<br>S.M.

APA, Harvard, Vancouver, ISO, and other styles

2

Deux, Antoine 1975. "Design of a silicon microfabricated rocket engine turbopump." Thesis, Massachusetts Institute of Technology, 2001. http://hdl.handle.net/1721.1/8714.

Full text

Abstract:

Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2001.<br>Includes bibliographical references (p. 175-178).<br>The advances in silicon microfabrication technology suggest the feasibility of high-precision mechanical devices for power conversion. This thesis describes the design of a silicon demonstration turbopump for a micro-rocket engine, and the analysis and experimental investigation of liquid bearings that may be implemented in a future turbopump. Liquid micro-scale lubrication is investigated. Models are developed to predict the performance of hydrostatic liquid thrust bearings, and hydrostatic and hydrodynamic liquid journal bearings. These models suggest that liquid operation of the existing micro-bearing rig is feasible. This device was tested with water to assess the bearings performance. The maximum speed achieved was 21,000 revolutions per minute, and was limited by the drag in this device designed for gas operation. A micro-scale turbopump producing a pressure rise of 30 atm for water was designed, as a demonstration of this concept for fluid pressurization in the rocket engine system. This thesis addresses several of the key design trades and identifies the fundamental engineering issues. This micropump integrates high-speed turbomachinery and micro-gas bearings. An innovative arrangement is proposed with coplanar pump and turbine for ease of fabrication and reduction of imbalance.<br>by Antoine Deux.<br>S.M.

APA, Harvard, Vancouver, ISO, and other styles

3

Wang, Vincent S. M. Massachusetts Institute of Technology. "Characterization of cavitation instabilities in rocket engine turbopump inducers." Thesis, Massachusetts Institute of Technology, 2016. http://hdl.handle.net/1721.1/107057.

Full text

Abstract:

Thesis: S.M., Massachusetts Institute of Technology, Department of Aeronautics and Astronautics, 2016.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 135-138).<br>Characterized by super-synchronous rotation of cavities around the periphery of rocket engine turbopump inducers, rotating cavitation is the primary cavitation instability considered in this thesis. A recently developed hypothesis for rotating cavitation onset is assessed through novel experimental analysis and a previously developed body force modeling approach using the MIT inducer, representative of the design of the Space Shuttle main engine low-pressure oxidizer pump inducer. A previously developed temporal and spatial Fourier decomposition, known as Traveling Wave Energy (TWE) analysis, of experimental unsteady inlet pressure measurements of the cavitating MIT inducer is demonstrated. TWE analysis offers several advantages over the current experimental analysis methods, resolving frequency, spatial mode shapes, and rotation direction of cavitation phenomena. Cut-on/cut-off behavior between rotating cavitation and alternate blade cavitation is observed, supporting the hypothesis that alternate blade cavitation is a necessary precursor to rotating cavitation onset. TWE is adapted for use on high speed borescope video data taken in the same experimental campaign. The frequency content extracted is qualitatively correlated with the results from the pressure data, establishing TWE as a viable tool for quantitative analysis of optical data. The video TWE results indicate that cavitation instability signatures are uniform in the radial direction, suggesting that a pressure transducer array can be established as the primary detection method for rotating cavitation and thereby simplifying test setups. A body force based modeling approach typically used for aero-engine compressor stability prediction is assessed for use in predicting rotating cavitation. A previously developed inducer-specific body force model formulation is validated in a representative compressor geometry, capturing global performance across the characteristic within 7%. However, the model exhibits convergence issues when applied to the inducer, hypothesized to be due to sensitivity in the inducer's loss characteristics. The investigation suggests the low flow coefficient design of the inducer drives the loss sensitivity and is the root cause behind the model's convergence issues. The results indicate the body force model is valid for the higher flow coefficient designs and lower stagger angles typically found in aero-engine compressors and fans. Suggestions for desensitizing the model for the inducer as well as further diagnostics defining the limiting geometry case for body force modeling are made.<br>by Vincent Wang.<br>S.M.

APA, Harvard, Vancouver, ISO, and other styles

4

Kline, Sara E. "Investigation of the Fluid Flow Through the Oil Transfer Sleeve of the PT-06 Turboprop Engine." University of Akron / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=akron1341577847.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Rutkowski, Richard J. "Cold flow simulation of the alternate turbopump development turbine of the space shuttle main engine high pressure fuel turbopump." Thesis, Monterey, California. Naval Postgraduate School, 1994. http://hdl.handle.net/10945/28034.

Full text

Abstract:

Approved for public release; distribution is unlimited<br>Completion of the installation at the Naval Postgraduate School of a cold-flow test facility for the turbine of the Space Shuttle Main Engine High Pressure Fuel Turbopump is reported. The article to be tested is the first stage of the Alternate Turbopump Development model designed and manufactured by Pratt & Whitney. The purpose of the facility is to enable the development of non- intrusive flow measurements and comparison of those measurements with numerical simulations. Flow field characteristics of the turbine stator were predicted using a three-dimensional viscous flow code. A sensitivity study was conducted to determine the effect of inlet profile to flow field solution. Recommendations are made for future use of the test facility and validation of the numerical simulation scheme

APA, Harvard, Vancouver, ISO, and other styles

6

Brown, Joseph R. "Model Identification for the Space Shuttle Main Engine High Pressure Oxidizer Turbopump." Ohio University / OhioLINK, 1992. http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1239733713.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Southward, James D. "Laser doppler velocimetry in the space-shuttle main engine high-pressure fuel turbopump." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1998. http://handle.dtic.mil/100.2/ADA342224.

Full text

Abstract:

Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, March 1998.<br>Thesis advisor(s): Garth V. Hobson. "March 1998." Includes bibliographical references (p. 145-147). Also available online.

APA, Harvard, Vancouver, ISO, and other styles

8

Greco, Philip Andrew. "Turbine performance mapping of the space-shuttle main engine high-pressure fuel turbopump." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1995. http://handle.dtic.mil/100.2/ADA306473.

Full text

Abstract:

Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, September 1995.<br>Thesis advisor(s): Garth V. Hobson. "September 1995." Includes bibliographical references. Also available online.

APA, Harvard, Vancouver, ISO, and other styles

9

Cunha, Marco Antonio Hidalgo. "A computational tool for the design and optimization of supersonic turbines with application on turbopump rocket engines." Instituto Tecnológico de Aeronáutica, 2012. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=3218.

Full text

Abstract:

Turbo-machinery design is clearly about making many decisions often under uncertainty and with multiple conflicting objectives. In this work, a computational tool has been developed to assist in the preliminary design optimization of supersonic turbines with application on turbopump rocket engines. It was proposed an evolutive approach based on genetic algorithm to automatize the process of selecting values, based on hands-on experience, for decision variables and fulfill simultaneously decisive compromises faced by the designer. At design point, exploring multiple optima solutions, the tool allows to fast estimate in a robust and accurate manner, performance, main dimensions, mass of rotor-wheel and the lower possible flow rate of the turbine. Out of this point, performance maps can be calculated varying rotational speed and pressure ratio. Because, it is involved by many objectives, a Pareto-optimum set is found. The search ends when the relation power-to-weight converges. The power-to-weight ratio characterizes a good option to relate performance and weight among distinct turbopump turbines. The empirical loss models adopted as well as the recommended values in the selection of decision variables were obtained in the Russian literature. To demonstrate the functionalities of tool, the single-stage of the Soviet RD109 rocket turbine was redesigned. The results were validated from those found in the engine';s atlas of construction and also, by a statistical method of calculation defined from an experimental study that estimates the maximum turbine efficiency.

APA, Harvard, Vancouver, ISO, and other styles

10

Yoshida, Brian Richard. "Compuational analysis of boundary layer control by suction in a space transfer vehicle engine turbopump diffuser /." Online version of thesis, 1992. http://hdl.handle.net/1850/11058.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Books on the topic "Turboprop engines"

1

Hager, Roy D. Advanced turboprop project. Scientific and Technical Information Division, National Aeronautics and Space Administration, 1988.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

2

Hager, Roy D. Advanced turboprop project. Scientific and Technical Information Division, National Aeronautics and Space Administration, 1988.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

3

Pant, Rajkumar. GENENG: A generic turboprop engine model. Cranfield University, College of Aeronautics, 1996.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

4

Gentry, Garl L. Effect of solidity and inclination on propeller-nacelle force coefficients. Langley Research Center, 1991.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

5

Whitlow, John B. NASA advanced turboprop research and concept validation program. National Aeronautics and Space Administration, 1988.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

6

Heathcote, Roy. The Rolls-Royce Dart: Pioneering turboprop. Rolls-Royce Heritage Trust, 1992.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

7

Warsi, Saif A. User's guide to PMESH - a grid-generation program for single-rotation and counterrotation advanced turboprops. Lewis Research Center, 1989.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

8

Hanson, Donald B. Unified aeroacoustics analysis for high speed turboprop aerodynamics and noise. Volume 1 - Development of theory for blade loading, wakes and noise. Lewis Research Center, 1991.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

9

Gentry, Garl L. Aerodynamic characteristics of a propeller-powered high-lift semispan wing. Langley Research Center, 1994.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

10

Metzger, F. B. Benefits of blade sweep for advanced turboprops. AIAA, 1985.

Find full text

APA, Harvard, Vancouver, ISO, and other styles

Book chapters on the topic "Turboprop engines"

1

Greatrix, David R. "Turboprop and Turboshaft Engines." In Powered Flight. Springer London, 2012. http://dx.doi.org/10.1007/978-1-4471-2485-6_8.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

El-Sayed, Ahmed F. "Shaft Engines Turboprop, Turboshaft, and Propfan." In Fundamentals of Aircraft and Rocket Propulsion. Springer London, 2016. http://dx.doi.org/10.1007/978-1-4471-6796-9_7.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Greatrix, David R. "Erratum to: Turboprop and Turboshaft Engines." In Powered Flight. Springer London, 2012. http://dx.doi.org/10.1007/978-1-4471-2485-6_15.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Le Brun, Christophe, Emmanuel Godoy, Dominique Beauvois, Bogdan Liacu, and Ricardo Noguera. "Decentralized Control: Application to a Turboprop Engine." In Informatics in Control, Automation and Robotics 12th International Conference, ICINCO 2015 Colmar, France, July 21-23, 2015 Revised Selected Papers. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-31898-1_22.

Full text

APA, Harvard, Vancouver, ISO, and other styles

5

Şöhret, Yasin, M. Ziya Sogut, Onder Turan, and T. Hikmet Karakoc. "Sustainability Assessment of a Turboprop Engine: Exergy-Based Method." In Lecture Notes in Energy. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-26950-4_22.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Coban, Kahraman, Yasin Şöhret, M. Ziya Sogut, Onder Turan, and T. Hikmet Karakoc. "Exergy Approach to Evaluate Performance of a Mini Class Turboprop Engine." In Lecture Notes in Energy. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-26950-4_23.

Full text

APA, Harvard, Vancouver, ISO, and other styles

7

Vinay, C. A., and S. Bhaskar Chakravarthy. "Validation of Numerical Analysis Results for Pusher Configured Turboprop Engine Air Intake." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-9601-8_3.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Atilgan, Ramazan, Onder Turan, and Hakan Aydin. "Exergo-Economic Analysis of an Experimental Aircraft Turboprop Engine Under Low Torque Condition." In Springer Proceedings in Physics. Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-05521-3_42.

Full text

APA, Harvard, Vancouver, ISO, and other styles

9

Li, Cheng, Chen Lishun, Liang Tao, Guo Li, Cheng Ming, and Zeng Lin. "Features of Singular Value Decomposition and Its Application to the Vibration Monitoring of Turboprop Engine." In Lecture Notes in Electrical Engineering. Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-10-6571-2_181.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

"Appendix K: Turboprop Engine Cycle Analysis." In Aircraft Engine Design, Second Edition. American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/5.9781600861444.0589.0608.

Full text

APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Turboprop engines"

1

Pegors, Douglas E. "Advanced Allison Small Turboprop Engines." In General Aviation Aircraft Meeting and Exposition. SAE International, 1987. http://dx.doi.org/10.4271/871055.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

Agrawal, Rishabh, Deepanshu Singh, and PMV Subbarao. "Regenerative System for Turboprop Engines." In 15th International Energy Conversion Engineering Conference. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-4806.

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

Cook, David L. "Development of the PW100 Turboprop Engines." In General Aviation Aircraft Meeting and Exposition. SAE International, 1985. http://dx.doi.org/10.4271/850909.

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

Vogt, Robert L., and Arun Sehra. "Next Generation 2 MW Turboshaft and Turboprop Engines." In ASME 1993 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1993. http://dx.doi.org/10.1115/93-gt-046.

Full text

Abstract:

Textron Lycoming of Stratford, Connecticut is incorporating the latest in advanced technology into turboshaft and turboprop engines for near term commercial service. The level of cold section technology being incorporated is the already demonstrated next generation of axi-centrifugal compressor beyond that which was developed for the U.S. Army T800, 0.9 MW turboshaft engine in the late 1980s. The compressor evolution is given special emphasis. The hot section technology is a robust, simplified, low cost, commercial endurance derate of the tri-service; US Army, US Navy, US Air Force and Textron Lycoming joint core engine [1] now on test. The new 2 MW commercial engine has substantially reduced fuel consumption, is lighter, and is smaller than today’s best engines. Engineering development is now underway and certification is slated to be completed in 1996.

APA, Harvard, Vancouver, ISO, and other styles

5

Prevallet, L. C. "Single Lever Power Management of Turboprop Engines." In Aerospace Technology Conference and Exposition. SAE International, 1991. http://dx.doi.org/10.4271/912200.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Rodgers, C. "High Pressure Ratio Intercooled Turboprop Study." 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-405.

Full text

Abstract:

High altitude long endurance unmanned aircraft impose unique contraints on candidate engine propulsion systems and types. Piston, rotary and gas turbine engines have been proposed for such special applications. Of prime importance is the requirement for maximum thermal efficiency (minimum specific fuel consumption) with minimum waste heat rejection. Engine weight, although secondary to fuel economy, must be evaluated when comparing various engine candidates. Weight can be minimized by either high degrees of turbocharging with the piston and rotary engines, or by the high power density capabilities of the gas turbine. The design characteristics and features of a conceptual high pressure ratio intercooled turboprop are discussed. The intended application would be for long endurance aircraft flying at an altitude of 60,000 ft. (18,300 m). It is estimated that such a turboprop would be capable of thermal efficiencies exceeding 40% with current state-of-the-art component efficiency levels and an overall compressor pressure ratio of 66.0. Projected Power (at altitude) to weight ratio is comparable to that of competitive piston and rotary engines.

APA, Harvard, Vancouver, ISO, and other styles

7

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.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

8

Mainville, D., D. Melfi, and M. Whiting. "A Universal Turboprop Engine Dynamometer Test Cell." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-343.

Full text

Abstract:

Pratt & Whitney Canada produces a wide range of aircraft engines and this has led to a concerted effort to standardize and streamline its production engine test facilities. P&WC produce two very different series of turboprop engines, the PW100 with a conventional intake and exhaust arrangement and the PT6 with its reverse flow arrangement. A dynamometer test cell capable of testing both these engine series has been designed and built at Longueuil and is now in operation. The changeover from one model to the other can be carried out by an operator in less than two hours and requires no special tooling or manpower. This paper discusses the solutions developed to overcome the inherent problems of intake and exhaust arrangement, engine mounting, slave equipment requirements etc. generated by testing two very different families of engines in the same test cell coupled with the need to incorporate the efficiency and ease of operation required of a production facility.

APA, Harvard, Vancouver, ISO, and other styles

9

Lopez-Diez, Alfredo, Luis Ruiz-Calavera, Javier Castillo-Calvo, and Raul Prieto-Ibañez. "Front End Optimization of High Speed Turboprop Engines." In 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-4204.

Full text

APA, Harvard, Vancouver, ISO, and other styles

10

Faltot, Pierre-Jean, Daniela Pitel Welnitz, Philippe Vertenoeuil, Tomas Vlach, Luca Lombardi, and Michele D’Ercole. "Analysis and Testing of Aerobatic Turboprop Aircraft Inlet." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76398.

Full text

Abstract:

Aerobatic aircraft have become popular for the training of military pilots, and nowadays an increasing number of such airframes are being developed. Modern turboprop engines provide high performance allowing the pilots to get similar handling characteristics to military jet aircraft engines. Prior to the availability of high performance turboprops, the basic pilot training was conducted using jet aircraft. Furthermore, the introduction of electronic control systems on last-generation turboprop engines enables single lever control, making it an ideal candidate for this type of aerobatic and training airframes. This new type of engine operation is however accompanied by several challenges from the point of view of the engine design and installation aerodynamics. GEAC has gone through a complex design process, in cooperation with the airframer, to validate the design of a new aerobatic aircraft inlet in the context of developing an aerobatic version of the H80 engine. In order to ensure a) surge-free operation, b) optimal engine performance and c) effective ice/FOD separation in inclement weather conditions and during any kind of aerobatic maneuver, the team has done extensive CFD predictions of the flow behaviour, performance/operability studies and finally a ground test campaign. First, a back-to-back comparison of the aerobatic inlet geometry versus a reference commuter inlet geometry was conducted. Then, flight conditions were simulated in calm and crosswind environments. Distortion patterns were examined using in-house developed tools and the diverse sources of distortion were identified. One of the results is the introduction of geometry improvements to guarantee improved performance and extended engine operability range. Advanced propeller modeling techniques were introduced and benchmarked in order to have the most exact representation of the propeller aerodynamic effect on inlet flow. Finally, a test campaign was conducted for validation purposes. An exhaustive instrumentation, data acquisition system and detailed test program were developed to validate CFD methods and assumptions made during the design phase, and to raise our confidence in the flight conditions simulation results.

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!