Turbofan Aero-Engine Efficiency Evaluation: an Integrated Approach Using VSBM Two-Stage Network DEA
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Conceptual Design and Structural Analysis of Ground Support Equipment for Handling and Maintenance of Turboshaft Engines•
Conceptual design and structural analysis of ground support equipment for handling and maintenance of Turboshaft engines• Iván Felipe Rodríguez-Barón a, Jaime Enrique Orduy-Rodríguez a, Brayan Alejandro Rosas-Bonilla b, Jhon b b Sebastián Merchán-Camelo & Edison Jair Bejarano-Sepúlveda a Programa de Ingeniería Aeronáutica, Fundación Universitaria los Libertadores, Bogotá, Colombia: Instituto Nacional de Pesquisas Espaciais, São José dos Campos, Brasil. [email protected], [email protected] b Programa de Ingeniería Aeronáutica, Fundación Universitaria los Libertadores, Bogotá, Colombia [email protected], [email protected], [email protected] Received: November 17th, 2020. Received in revised form: March 3rd, 2021. Accepted: April 6th, 2021. Abstract This paper describes the application of computational modeling and computer-aided design (CAD) for the conceptual design and structural analysis of the maintenance process of Klimov TV3-117 engines at an approved Maintenance, Repair and Overhaul (MRO) facility in Colombia. The main issue is that these engines are difficult to roll and manipulate due to their weight, which ranges between 250 and 350 kg, which causes time and cost overruns for the operator, and delays in the scheduled maintenance times. The solution proposed by this study is the conceptualization and structural feasibility of a prototype of ground support equipment for handling and maintenance of Turboshaft engines, implementation of which could save up to 100 person-hours, which translates into about USD 10,000, since the current process requires four specialists and two inspectors, whereas the modified process would only require one of each. Keywords: Computer-Aided Design (CAD); structural analysis; turboshaft engines; ground support equipment; aeronautical maintenance. -
Aerospace Engine Data
AEROSPACE ENGINE DATA Data for some concrete aerospace engines and their craft ................................................................................. 1 Data on rocket-engine types and comparison with large turbofans ................................................................... 1 Data on some large airliner engines ................................................................................................................... 2 Data on other aircraft engines and manufacturers .......................................................................................... 3 In this Appendix common to Aircraft propulsion and Space propulsion, data for thrust, weight, and specific fuel consumption, are presented for some different types of engines (Table 1), with some values of specific impulse and exit speed (Table 2), a plot of Mach number and specific impulse characteristic of different engine types (Fig. 1), and detailed characteristics of some modern turbofan engines, used in large airplanes (Table 3). DATA FOR SOME CONCRETE AEROSPACE ENGINES AND THEIR CRAFT Table 1. Thrust to weight ratio (F/W), for engines and their crafts, at take-off*, specific fuel consumption (TSFC), and initial and final mass of craft (intermediate values appear in [kN] when forces, and in tonnes [t] when masses). Engine Engine TSFC Whole craft Whole craft Whole craft mass, type thrust/weight (g/s)/kN type thrust/weight mini/mfin Trent 900 350/63=5.5 15.5 A380 4×350/5600=0.25 560/330=1.8 cruise 90/63=1.4 cruise 4×90/5000=0.1 CFM56-5A 110/23=4.8 16 -
Large Composite Fan Blade Development for Modern Aeroengines
Volume I: Composites Applications and Design LARGE COMPOSITE FAN BLADE DEVELOPMENT FOR MODERN AEROENGINES Keith T. Kedward University of California at Santa Barbara Department of Mechanical & Environmental Engineering Santa Barbara, California 93106-5070, USA SUMMARY: The state of maturity of contemporary PMC’s after almost 30 years of scientific and technology development has resulted in a capability that far exceeds that available in the late 1960’s, and which, in 1989, prompted General Electric to engage in the notably successful development and flight certification of large PMC fan blades for their GE90 engine. In this paper an accounting of the specific enhancements in (i) constituent (fiber and matrix) property characteristics, (ii) fabrication and processing options, and (iii) design analysis methods combined with computational capabilities will be discussed. However, an equally important aspect is the variation in the design options that has resulted from evolving high by-pass ratio engine technology, which will also be addressed. The GE90 fan blade represents one of these options, being a relatively large blade designed to operate at lower tip speeds, thereby reducing the severity of the impact threat represented by the ingestion of large birds. A comparison between various modern turbofan engine fan blades and other rotor blades serves to indicate the important parameters and the difficulty of establishing a composite threshold range for rotor blades in general. KEYWORDS: polymer matrix composite, composite fan blade, constituent properties, impact performance, textile reinforcement architectures, engine certification INTRODUCTION Since the ill-fated attempt by Rolls-Royce to develop large polymer matrix composite (PMC) fan blades for a large commercial turbofan engine in 1968, i.e., the RB211, this potential application had eluded the engine designer until the emergence of General Electric’s GE90 engine development. -
Comparison of Helicopter Turboshaft Engines
Comparison of Helicopter Turboshaft Engines John Schenderlein1, and Tyler Clayton2 University of Colorado, Boulder, CO, 80304 Although they garnish less attention than their flashy jet cousins, turboshaft engines hold a specialized niche in the aviation industry. Built to be compact, efficient, and powerful, turboshafts have made modern helicopters and the feats they accomplish possible. First implemented in the 1950s, turboshaft geometry has gone largely unchanged, but advances in materials and axial flow technology have continued to drive higher power and efficiency from today's turboshafts. Similarly to the turbojet and fan industry, there are only a handful of big players in the market. The usual suspects - Pratt & Whitney, General Electric, and Rolls-Royce - have taken over most of the industry, but lesser known companies like Lycoming and Turbomeca still hold a footing in the Turboshaft world. Nomenclature shp = Shaft Horsepower SFC = Specific Fuel Consumption FPT = Free Power Turbine HPT = High Power Turbine Introduction & Background Turboshaft engines are very similar to a turboprop engine; in fact many turboshaft engines were created by modifying existing turboprop engines to fit the needs of the rotorcraft they propel. The most common use of turboshaft engines is in scenarios where high power and reliability are required within a small envelope of requirements for size and weight. Most helicopter, marine, and auxiliary power units applications take advantage of turboshaft configurations. In fact, the turboshaft plays a workhorse role in the aviation industry as much as it is does for industrial power generation. While conventional turbine jet propulsion is achieved through thrust generated by a hot and fast exhaust stream, turboshaft engines creates shaft power that drives one or more rotors on the vehicle. -
6. Chemical-Nuclear Propulsion MAE 342 2016
2/12/20 Chemical/Nuclear Propulsion Space System Design, MAE 342, Princeton University Robert Stengel • Thermal rockets • Performance parameters • Propellants and propellant storage Copyright 2016 by Robert Stengel. All rights reserved. For educational use only. http://www.princeton.edu/~stengel/MAE342.html 1 1 Chemical (Thermal) Rockets • Liquid/Gas Propellant –Monopropellant • Cold gas • Catalytic decomposition –Bipropellant • Separate oxidizer and fuel • Hypergolic (spontaneous) • Solid Propellant ignition –Mixed oxidizer and fuel • External ignition –External ignition • Storage –Burn to completion – Ambient temperature and pressure • Hybrid Propellant – Cryogenic –Liquid oxidizer, solid fuel – Pressurized tank –Throttlable –Throttlable –Start/stop cycling –Start/stop cycling 2 2 1 2/12/20 Cold Gas Thruster (used with inert gas) Moog Divert/Attitude Thruster and Valve 3 3 Monopropellant Hydrazine Thruster Aerojet Rocketdyne • Catalytic decomposition produces thrust • Reliable • Low performance • Toxic 4 4 2 2/12/20 Bi-Propellant Rocket Motor Thrust / Motor Weight ~ 70:1 5 5 Hypergolic, Storable Liquid- Propellant Thruster Titan 2 • Spontaneous combustion • Reliable • Corrosive, toxic 6 6 3 2/12/20 Pressure-Fed and Turbopump Engine Cycles Pressure-Fed Gas-Generator Rocket Rocket Cycle Cycle, with Nozzle Cooling 7 7 Staged Combustion Engine Cycles Staged Combustion Full-Flow Staged Rocket Cycle Combustion Rocket Cycle 8 8 4 2/12/20 German V-2 Rocket Motor, Fuel Injectors, and Turbopump 9 9 Combustion Chamber Injectors 10 10 5 2/12/20 -
Avitrader Monthly MRO Magazine
July 2014 - www.avitrader.com FARNBOROUGH SPECIAL Airbus has a field day Company Profile Delta TechOps MRO News from around the world People on the Move latest appointments IBA Analysis Editor‘s Page 2 OEMs out in full force This year’s instalment of Farnborough will no- Al Baker told trade reporters that this trend company is also hoping to conclude a sale to a tably be remembered for the strong presence could lead to manufacturers losing business to Western airline “very soon.” of the aircraft manufacturers representing other OEMs and that airlines rather appreci- every sector from regional to long haul. They ated choice. And of course the mood at Farnborough was were all out to showcase new products and temporarily dampened as news of the Malay- highlight their programme updates. Airbus has responded by saying they (Airbus) sian Airlines MH17 777 trickled in. The whole has “taken the liberty to negotiate a good en- thing has an eerily resemblance to the Iran Air Clearly, Airbus was high on that list with the gine price with Rolls-Royce for all customers 655 incident back in the 1980s. No doubt it’s announcement of the A330neo and the selec- in advance.” another blow to the Malaysian carrier. tion of Rolls Royce as the sole engine supplier. However, not everyone welcomed the news Sukhoi, for the first time brought two SSJ 100 Keith Mwanalushi and the current trend by Airbus and Boeing aircraft as part of the static display. Sukhoi are Editor to offer a single power plant for their new hoping to capture a 20-25% share of the 90 to wide body planes. -
AED Fleet Contact List
AED Fleet Contact List September 2021 Make Model Primary Office Operations - Primary Operations - Secondary Avionics - Primary Avionics - Secondary Maintenance - Primary Maintenance - Secondary Air Tractor All Models MKC Persky, David (FAA) Hawkins, Kenneth (FAA) Marsh, Kenneth (FAA) Rockhill, Thane D (FAA) BadHorse, Jim (FAA) Airbus A300/310 SEA Hutton, Rick (FAA) Dunn, Stephen H (FAA) Gandy, Scott A (FAA) Watkins, Dale M (FAA) Patzke, Roy (FAA) Taylor, Joe (FAA) Airbus A318-321 CEO/NEO SEA Culet, James (FAA) Elovich, John D (FAA) Watkins, Dale M (FAA) Gandy, Scott A (FAA) Hunter, Milton C (FAA) Dodd, Mike B (FAA) Airbus A330/340 SEA Culet, James (FAA) Robinson, David L (FAA) Flores, John A (FAA) Watkins, Dale M (FAA) DiMarco, Joe (FAA) Johnson, Rocky (FAA) Airbus A350 All Series SEA Robinson, David L (FAA) Culet, James (FAA) Watkins, Dale M (FAA) Flores, John A (FAA) Dodd, Mike B (FAA) Johnson, Rocky (FAA) Airbus A380 All Series SEA Robinson, David L (FAA) Culet, James (FAA) Flores, John A (FAA) Watkins, Dale M (FAA) Patzke, Roy (FAA) DiMarco, Joe (FAA) Aircraft Industries All Models, L-410 etc. MKC Persky, David (FAA) McKee, Andrew S (FAA) Marsh, Kenneth (FAA) Pruneda, Jesse (FAA) Airships All Models MKC Thorstensen, Donald (FAA) Hawkins, Kenneth (FAA) Marsh, Kenneth (FAA) McVay, Chris (FAA) Alenia C-27J LGB Nash, Michael A (FAA) Lee, Derald R (FAA) Siegman, James E (FAA) Hayes, Lyle (FAA) McManaman, James M (FAA) Alexandria Aircraft/Eagle Aircraft All Models MKC Lott, Andrew D (FAA) Hawkins, Kenneth (FAA) Marsh, Kenneth (FAA) Pruneda, -
Helicopter Turboshafts
Helicopter Turboshafts Luke Stuyvenberg University of Colorado at Boulder Department of Aerospace Engineering The application of gas turbine engines in helicopters is discussed. The work- ings of turboshafts and the history of their use in helicopters is briefly described. Ideal cycle analyses of the Boeing 502-14 and of the General Electric T64 turboshaft engine are performed. I. Introduction to Turboshafts Turboshafts are an adaptation of gas turbine technology in which the principle output is shaft power from the expansion of hot gas through the turbine, rather than thrust from the exhaust of these gases. They have found a wide variety of applications ranging from air compression to auxiliary power generation to racing boat propulsion and more. This paper, however, will focus primarily on the application of turboshaft technology to providing main power for helicopters, to achieve extended vertical flight. II. Relationship to Turbojets As a variation of the gas turbine, turboshafts are very similar to turbojets. The operating principle is identical: atmospheric gases are ingested at the inlet, compressed, mixed with fuel and combusted, then expanded through a turbine which powers the compressor. There are two key diferences which separate turboshafts from turbojets, however. Figure 1. Basic Turboshaft Operation Note the absence of a mechanical connection between the HPT and LPT. An ideal turboshaft extracts with the HPT only the power necessary to turn the compressor, and with the LPT all remaining power from the expansion process. 1 of 10 American Institute of Aeronautics and Astronautics A. Emphasis on Shaft Power Unlike turbojets, the primary purpose of which is to produce thrust from the expanded gases, turboshafts are intended to extract shaft horsepower (shp). -
Los Motores Aeroespaciales, A-Z
Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 < aeroteca.com > Depósito Legal B 9066-2016 Título: Los Motores Aeroespaciales A-Z. © Parte/Vers: 1/12 Página: 1 Autor: Ricardo Miguel Vidal Edición 2018-V12 = Rev. 01 Los Motores Aeroespaciales, A-Z (The Aerospace En- gines, A-Z) Versión 12 2018 por Ricardo Miguel Vidal * * * -MOTOR: Máquina que transforma en movimiento la energía que recibe. (sea química, eléctrica, vapor...) Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 Este facsímil es < aeroteca.com > Depósito Legal B 9066-2016 ORIGINAL si la Título: Los Motores Aeroespaciales A-Z. © página anterior tiene Parte/Vers: 1/12 Página: 2 el sello con tinta Autor: Ricardo Miguel Vidal VERDE Edición: 2018-V12 = Rev. 01 Presentación de la edición 2018-V12 (Incluye todas las anteriores versiones y sus Apéndices) La edición 2003 era una publicación en partes que se archiva en Binders por el propio lector (2,3,4 anillas, etc), anchos o estrechos y del color que desease durante el acopio parcial de la edición. Se entregaba por grupos de hojas impresas a una cara (edición 2003), a incluir en los Binders (archivadores). Cada hoja era sustituíble en el futuro si aparecía una nueva misma hoja ampliada o corregida. Este sistema de anillas admitia nuevas páginas con información adicional. Una hoja con adhesivos para portada y lomo identifi caba cada volumen provisional. Las tapas defi nitivas fueron metálicas, y se entregaraban con el 4 º volumen. O con la publicación completa desde el año 2005 en adelante. -Las Publicaciones -parcial y completa- están protegidas legalmente y mediante un sello de tinta especial color VERDE se identifi can los originales. -
Session 6:Analytical Approximations for Low Thrust Maneuvers
Session 6: Analytical Approximations for Low Thrust Maneuvers As mentioned in the previous lecture, solving non-Keplerian problems in general requires the use of perturbation methods and many are only solvable through numerical integration. However, there are a few examples of low-thrust space propulsion maneuvers for which we can find approximate analytical expressions. In this lecture, we explore a couple of these maneuvers, both of which are useful because of their precision and practical value: i) climb or descent from a circular orbit with continuous thrust, and ii) in-orbit repositioning, or walking. Spiral Climb/Descent We start by writing the equations of motion in polar coordinates, 2 d2r �dθ � µ − r + = a (1) 2 2 r dt dt r 2 d θ 2 dr dθ aθ + = (2) 2 dt r dt dt r We assume continuous thrust in the angular direction, therefore ar = 0. If the acceleration force along θ is small, then we can safely assume the orbit will remain nearly circular and the semi-major axis will be just slightly different after one orbital period. Of course, small and slightly are vague words. To make the analysis rigorous, we need to be more precise. Let us say that for this approximation to be valid, the angular acceleration has to be much smaller than the corresponding centrifugal or gravitational forces (the last two terms in the LHS of Eq. (1)) and that the radial acceleration (the first term in the LHS in the same equation) is negligible. Given these assumptions, from Eq. (1), dθ r µ d2θ 3 r µ dr ≈ ! ≈ − (3) 3 2 5 dt r dt 2 r dt Substituting into Eq. -
An Investigation in Gold-Plating Scaled Turbofan Engine Simulators
An Investigation in Gold-Plating Scaled Turbofan Engine Simulators through Means of Aerodynamic and Load Cell Thrust Measurements with Comparisons to Full-Scale Engine Results A Thesis Presented in Partial Fulfillment of the Requirements for the Degree of Master of Science in the Graduate School of The Ohio State University By Jacob T. Allenstein, B. Sci. Graduate Program in Aeronautical and Astronautical Engineering The Ohio State University 2013 Thesis Committee: Dr. Richard J. Freuler, Advisor Dr. Clifford A. Whitfield, Co-Advisor Copyright by Jacob T. Allenstein © 2013 ABSTRACT Model testing offers investigators a useful tool that can provide good insight into the aerodynamics behind full-scale engines and test facilities. Understanding the aerodynamics of a full-scale engine can help investigators update old test facilities and help design new facilities and engines. Gold-plating an engine is a process that the industry uses to compare the performance of an engine from the same family or class of engines in various facilities. The gold-plated engine can be used to determine a correlation factor of a testing facility or to determine the similarities in performance between a new or old engine to the gold-plated engine. The use of a correlation or correction factor can be used to correct a deviation in a measurement made in a test facility to bring the engine’s performance back to readings performed in a “free-air” environment. Model testing consists of the use of a simulator or scaled version of an engine that generates performance close to full-scale operation conditions. The simulator used in this study was constructed to not have any moving parts but rather be driven by a high pressure air system, providing a safe alternative to testing the full-scale engine. -
ISSEK HSE) Role of Big Data Augmented Horizon Scanning in Strategic and Marketing Analytics
National Research University Higher School of Economics Institute for Statistical Studies and Economics of Knowledge Big Data Augmented Horizon Scanning: Combination of Quantitative and Qualitative Methods for Strategic and Marketing Analytics [email protected] [email protected] XIX April International Academic Conference on Economic and Social Development Moscow, 11 April 2018 Outline - Role of artificial intelligence and big data in modern analytics - System of Intelligent Foresight Analytics iFORA - Combined quantitative and qualitative analysis methodology and software solutions - Use cases - Conclusion and discussion 2 Growing interest in Artificial Intelligence, Big Data and Machine Learning International analytical reports & news feed 12000 10000 8000 Artificial Intelligence 6000 Big Data Machine Learning 4000 2000 0 2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 Russian analytical reports & news feed 800 700 600 500 Artificial Intelligence 400 Big Data 300 Machine Learning 200 100 0 2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010 2011 2012 2013 2014 2015 2016 3 Source: System of Intelligent Foresight Analytics iFORA™ (ISSEK HSE) Role of Big Data Augmented Horizon Scanning in Strategic and Marketing Analytics AI-related tasks Tracking latest and challenges trends, technologies, drivers, barriers Market forecasting Trend analysis Understanding S&T modern skills and Instruments for Customers Market Intelligence competences analysis feedback knowledge discovery HR policy Vacancy Feedback mining