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Easy Access Rules for Auxiliary Power Units (CS-APU)
APU - CS Easy Access Rules for Auxiliary Power Units (CS-APU) EASA eRules: aviation rules for the 21st century Rules and regulations are the core of the European Union civil aviation system. The aim of the EASA eRules project is to make them accessible in an efficient and reliable way to stakeholders. EASA eRules will be a comprehensive, single system for the drafting, sharing and storing of rules. It will be the single source for all aviation safety rules applicable to European airspace users. It will offer easy (online) access to all rules and regulations as well as new and innovative applications such as rulemaking process automation, stakeholder consultation, cross-referencing, and comparison with ICAO and third countries’ standards. To achieve these ambitious objectives, the EASA eRules project is structured in ten modules to cover all aviation rules and innovative functionalities. The EASA eRules system is developed and implemented in close cooperation with Member States and aviation industry to ensure that all its capabilities are relevant and effective. Published February 20181 1 The published date represents the date when the consolidated version of the document was generated. Powered by EASA eRules Page 2 of 37| Feb 2018 Easy Access Rules for Auxiliary Power Units Disclaimer (CS-APU) DISCLAIMER This version is issued by the European Aviation Safety Agency (EASA) in order to provide its stakeholders with an updated and easy-to-read publication. It has been prepared by putting together the certification specifications with the related acceptable means of compliance. However, this is not an official publication and EASA accepts no liability for damage of any kind resulting from the risks inherent in the use of this document. -
2.0 Axial-Flow Compressors 2.0-1 Introduction the Compressors in Most Gas Turbine Applications, Especially Units Over 5MW, Use Axial fl Ow Compressors
2.0 Axial-Flow Compressors 2.0-1 Introduction The compressors in most gas turbine applications, especially units over 5MW, use axial fl ow compressors. An axial fl ow compressor is one in which the fl ow enters the compressor in an axial direction (parallel with the axis of rotation), and exits from the gas turbine, also in an axial direction. The axial-fl ow compressor compresses its working fl uid by fi rst accelerating the fl uid and then diffusing it to obtain a pressure increase. The fl uid is accelerated by a row of rotating airfoils (blades) called the rotor, and then diffused in a row of stationary blades (the stator). The diffusion in the stator converts the velocity increase gained in the rotor to a pressure increase. A compressor consists of several stages: 1) A combination of a rotor followed by a stator make-up a stage in a compressor; 2) An additional row of stationary blades are frequently used at the compressor inlet and are known as Inlet Guide Vanes (IGV) to ensue that air enters the fi rst-stage rotors at the desired fl ow angle, these vanes are also pitch variable thus can be adjusted to the varying fl ow requirements of the engine; and 3) In addition to the stators, another diffuser at the exit of the compressor consisting of another set of vanes further diffuses the fl uid and controls its velocity entering the combustors and is often known as the Exit Guide Vanes (EGV). In an axial fl ow compressor, air passes from one stage to the next, each stage raising the pressure slightly. -
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 -
High Pressure Ratio Intercooled Turboprop Study
E AMEICA SOCIEY O MECAICA EGIEES 92-GT-405 4 E. 4 S., ew Yok, .Y. 00 h St hll nt b rpnbl fr ttnt r pnn dvnd In ppr r n d n t tn f th St r f t vn r Stn, r prntd In t pbltn. n rnt nl f th ppr pblhd n n ASME rnl. pr r vlbl fr ASME fr fftn nth ftr th tn. rntd n USA Copyright © 1992 by ASME ig essue aio Iecooe uoo Suy C. OGES Downloaded from http://asmedigitalcollection.asme.org/GT/proceedings-pdf/GT1992/78941/V002T02A028/2401669/v002t02a028-92-gt-405.pdf by guest on 23 September 2021 Sundstrand Power Systems San Diego, CA ASAC NOMENCLATURE High altitude long endurance unmanned aircraft impose KFT Altitude Thousands Feet unique contraints on candidate engine propulsion systems and HP Horsepower types. Piston, rotary and gas turbine engines have been proposed for such special applications. Of prime importance is the HIPIT High Pressure Intercooled Turbine requirement for maximum thermal efficiency (minimum specific Mn Flight Mach Number fuel consumption) with minimum waste heat rejection. Engine weight, although secondary to fuel economy, must be evaluated Mls Inducer Mach Number when comparing various engine candidates. Weight can be Specific Speed (Dimensionless) minimized by either high degrees of turbocharging with the Ns piston and rotary engines, or by the high power density Exponent capabilities of the gas turbine. pps Airflow The design characteristics and features of a conceptual high SFC Specific Fuel Consumption pressure ratio intercooled turboprop are discussed. The intended application would be for long endurance aircraft flying TIT Turbine Inlet Temperature °F at an altitude of 60,000 ft.(18,300 m). -
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). -
SP's Aviation June 2011
SP’s AN SP GUIDE PUBLICATION ED BUYER ONLY) ED BUYER AS -B A NDI I News Flies. We Gather Intelligence. Every Month. From India. 75.00 ( ` Aviationwww.spsaviation.net JUNE • 2011 ENGINE POWERPAGE 18 Regional Aviation FBO Services in India Interview with CAS No Slowdown in Indo-US Relationship LENG/2008/24199 Interview: Pratt & Whitney EBACE 2011 RNI NUMBER: DELENG/2008/24199 DE Show Report Our jets aren’t built tO airline standards. FOr which Our custOmers thank us daily. some manufacturers tout the merits of building business jets to airline standards. we build to an even higher standard: our own. consider the citation mustang. its airframe service life is rated at 37,500 cycles, exceeding that of competing airframes built to “airline standards.” in fact, it’s equivalent to 140 years of typical use. excessive? no. just one of the many ways we go beyond what’s required to do what’s expected of the world’s leading maker of business aircraft. CALL US TODAY. DEMO A CITATION MUSTANG TOMORROW. 000-800-100-3829 | WWW.AvIATOR.CESSNA.COM The Citation MUSTANG Cessna102804 Mustang Airline SP Av.indd 1 12/22/10 12:57 PM BAILEY LAUERMAN Cessna Cessna102804 Mustang Airline SP Av Cessna102804 Pub: SP’s Aviation Color: 4-color Size: Trim 210mm x 267mm, Bleed 277mm x 220mm SP’s AN SP GUIDE PUBLICATION TABLE of CONTENTS News Flies. We Gather Intelligence. Every Month. From India. AviationIssue 6 • 2011 Dassault Rafale along with EurofighterT yphoon were found 25 Indo-US Relationship compliant with the IAF requirements of a medium multi-role No Slowdown -
Improving Engine Efficiency Through Core Developments
IMPROVING ENGINE EFFICIENCY THROUGH CORE DEVELOPMENTS Brief summary: The NASA Environmentally Responsible Aviation (ERA) Project and Fundamental Aeronautics Projects are supporting compressor and turbine research with the goal of reducing aircraft engine fuel burn and greenhouse gas emissions. The primary goals of this work are to increase aircraft propulsion system fuel efficiency for a given mission by increasing the overall pressure ratio (OPR) of the engine while maintaining or improving aerodynamic efficiency of these components. An additional area of work involves reducing the amount of cooling air required to cool the turbine blades while increasing the turbine inlet temperature. This is complicated by the fact that the cooling air is becoming hotter due to the increases in OPR. Various methods are being investigated to achieve these goals, ranging from improved compressor three-dimensional blade designs to improved turbine cooling hole shapes and methods. Finally, a complementary effort in improving the accuracy, range, and speed of computational fluid mechanics (CFD) methods is proceeding to better capture the physical mechanisms underlying all these problems, for the purpose of improving understanding and future designs. National Aeronautics and Space Administration Improving Engine Efficiency Through Core Developments Dr. James Heidmann Project Engineer for Propulsion Technology (acting) Environmentally Responsible Aviation Integrated Systems Research Program AIAA Aero Sciences Meeting January 6, 2011 www.nasa.gov NASA’s Subsonic -
A Study on the Stall Detection of an Axial Compressor Through Pressure Analysis
applied sciences Article A Study on the Stall Detection of an Axial Compressor through Pressure Analysis Haoying Chen 1,† ID , Fengyong Sun 2,†, Haibo Zhang 2,* and Wei Luo 1,† 1 Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, No. 29 Yudao Street, Nanjing 210016, China; [email protected] (H.C.); [email protected] (W.L.) 2 AVIC Aero-engine Control System Institute, No. 792 Liangxi Road, Wuxi 214000, China; [email protected] * Correspondence: [email protected] † These authors contributed equally to this work. Received: 5 June 2017; Accepted: 22 July 2017; Published: 28 July 2017 Abstract: In order to research the inherent working laws of compressors nearing stall state, a series of compressor experiments are conducted. With the help of fast Fourier transform, the amplitude–frequency characteristics of pressures at the compressor inlet, outlet and blade tip region outlet are analyzed. Meanwhile, devices imitating inlet distortion were applied in the compressor inlet distortion disturbance. The experimental results indicated that compressor blade tip region pressure showed a better performance than the compressor’s inlet and outlet pressures in regards to describing compressor characteristics. What’s more, compressor inlet distortion always disturbed the compressor pressure characteristics. Whether with inlet distortion or not, the pressure characteristics of pressure periodicity and amplitude frequency could always be maintained in compressor blade tip pressure. For the sake of compressor real-time stall detection application, a compressor stall detection algorithm is proposed to calculate the compressor pressure correlation coefficient. The algorithm also showed a good monotonicity in describing the relationship between the compressor surge margin and the pressure correlation coefficient. -
Proyecto Fin De Carrera Ingeniería Aeronáutica Desarrollo De Un
Proyecto Fin de Carrera Ingeniería Aeronáutica Desarrollo de un modelo de turbohélice de tres ejes. Análisis y evaluación de prestaciones en diferentes aplicaciones. Autor: Luca García Hernández Tutor: Francisco J. Jiménez-Espadafor Aguilar Dep. Ingeniería Energética Escuela Técnica Superior de Ingeniería Universidad de Sevilla Sevilla, 2017 Proyecto Fin de Carrera Ingeniería Aeronáutica Desarrollo de un modelo de turbohélice de tres ejes. Análisis y evaluación de prestaciones en diferentes aplicaciones. Autor: Luca García Hernández Tutor: Francisco J. Jiménez-Espadafor Aguilar Catedrático Dep. Ingeniería Energética Escuela Técnica Superior de Ingeniería Universidad de Sevilla Sevilla, 2017 Proyecto Fin de Carrera: Desarrollo de un modelo de turbohélice de tres ejes. Análisis y evaluación de prestaciones en diferentes aplicaciones. Autor: Luca García Hernández Tutor: Francisco J. Jiménez-Espadafor Aguilar El tribunal nombrado para juzgar el trabajo arriba indicado, compuesto por los siguientes profesores: Presidente: Vocal/es: Secretario: acuerdan otorgarle la calificación de: El Secretario del Tribunal Fecha: Agradecimientos Los proyectos finales de carrera encierran muchas historias de constancia y superación a lo largo del tiempo. Con este proyecto, pongo fin a una etapa muy importante de mi vida. Escribir estas palabras supone una gran satisfacción por la meta alcanzada y una gran alegría, pues supone el inicio de la etapa como ingeniero, en la que aplicar todo lo aprendido a lo largo de la carrera. Este proyecto me ha hecho profundizar considerablemente en el campo de los motores aeronáuticos y las herramientas para su modelado matemático. Ha sido muy enriquecedor para mí y seguro que los conocimientos aquí adquiridos, me serán de gran utilidad. Este logro no es sólo personal, pues sin la ayuda y el acompañamiento de muchas personas no podría haberlo conseguido. -
The Power for Flight: NASA's Contributions To
The Power Power The forFlight NASA’s Contributions to Aircraft Propulsion for for Flight Jeremy R. Kinney ThePower for NASA’s Contributions to Aircraft Propulsion Flight Jeremy R. Kinney Library of Congress Cataloging-in-Publication Data Names: Kinney, Jeremy R., author. Title: The power for flight : NASA’s contributions to aircraft propulsion / Jeremy R. Kinney. Description: Washington, DC : National Aeronautics and Space Administration, [2017] | Includes bibliographical references and index. Identifiers: LCCN 2017027182 (print) | LCCN 2017028761 (ebook) | ISBN 9781626830387 (Epub) | ISBN 9781626830370 (hardcover) ) | ISBN 9781626830394 (softcover) Subjects: LCSH: United States. National Aeronautics and Space Administration– Research–History. | Airplanes–Jet propulsion–Research–United States– History. | Airplanes–Motors–Research–United States–History. Classification: LCC TL521.312 (ebook) | LCC TL521.312 .K47 2017 (print) | DDC 629.134/35072073–dc23 LC record available at https://lccn.loc.gov/2017027182 Copyright © 2017 by the National Aeronautics and Space Administration. The opinions expressed in this volume are those of the authors and do not necessarily reflect the official positions of the United States Government or of the National Aeronautics and Space Administration. This publication is available as a free download at http://www.nasa.gov/ebooks National Aeronautics and Space Administration Washington, DC Table of Contents Dedication v Acknowledgments vi Foreword vii Chapter 1: The NACA and Aircraft Propulsion, 1915–1958.................................1 Chapter 2: NASA Gets to Work, 1958–1975 ..................................................... 49 Chapter 3: The Shift Toward Commercial Aviation, 1966–1975 ...................... 73 Chapter 4: The Quest for Propulsive Efficiency, 1976–1989 ......................... 103 Chapter 5: Propulsion Control Enters the Computer Era, 1976–1998 ........... 139 Chapter 6: Transiting to a New Century, 1990–2008 .................................... -
POLITECNICO DI MILANO Thermodynamic Analysis of A
POLITECNICO DI MILANO School of Industrial and Information Engineering Department of Aerospace Science and Technology Master of Science in Aeronautical Engineering Thermodynamic analysis of a turboprop engine with regeneration and intercooling Advisor: Prof. Roberto ANDRIANI M.Sc. Dissertation of: Rasheed Michael ISHOLA Matr. 895396 April 2020 Academic Year 2019-2020 Contents Introduction 1 1 Turbopropeller engines overview 2 1.1 Turbopropeller characteristics . .4 1.2 Comparison with turbojets and piston-powered engines . .4 1.3 Turbopropeller-powered aircrafts . .5 1.4 Turbopropeller manufacturers . .9 1.4.1 Pratt & Whitney Canada (PWC) [1] . .9 1.4.2 Rolls-Royce [2] . 17 1.4.3 General Electric Aviation [3] . 22 1.4.4 JSC Kuznetsov [4] . 26 1.4.5 JSC \UEC-Klimov" [5] . 27 1.4.6 Ivchenko-Progress ZMKB [6] . 28 1.4.7 Honeywell Aerospace [7] . 33 1.4.8 PBS Aerospace [8] . 34 2 Thermodynamics of a turbopropeller engine with heat exchange 36 2.1 Intercooling and regeneration . 36 2.2 Thermodynamic cycle . 39 2.2.1 Assumptions . 39 2.2.2 The cycle . 42 2.3 Performances . 48 3 The code 53 3.1 Assumptions and data used . 54 3.1.1 Efficiencies and pressure losses . 54 3.1.2 Fuel properties . 54 3.1.3 Specific heat values . 55 3.2 Code Structure . 57 3.2.1 Input file . 57 3.2.2 Output files . 58 3.2.3 Code details . 62 4 Numerical simulation 78 4.1 Results . 78 4.1.1 Determination of the best βn condition . 79 4.1.2 Performances vs βc .......................... -
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QTR_03 12 A QUARTERLY PUBLICATION BROUGHT TO YOU BY THE BOEING EDGE In-Service Supplier Support 787 Propulsion System Reducing Runway Landing Overruns New Process for Component Removal Reduction Securing Airline Information on the Ground and in the Air Cover photo: 737-800 Engine Fan Blades AERO Contents 03 E nhancing Suppliers’ In-Service Support to Airlines Airline assessments of supplier performance enhance airplane support. 05 787 Propulsion System The 787 Dreamliner is powered by new-generation engines that offer improvements in fuel consumption, 05 noise, and emissions. 15 Reducing Runway Landing Overruns A combination of procedural improvements, flight crew knowledge, and flight deck enhancements help mitigate runway overrun excursions during landing. 21 15 N ew Process for Component Removal Reduction Automating the component removal reduction process can save considerable time and help operators reduce main- tenance costs. 25 Securing Airline Information on the Ground and in the Air 21 Protecting information and technology has become an operational requirement for airlines. 25 01 WWW.BOEING.COM/BOEINGEDGE/AEROMAGAZINE I ssue 47 _Quarter 03 | 2012 AERO Publisher Design Cover photography Editorial Board Shannon Myers Methodologie Jeff Corwin Don Andersen, Gary Bartz, Richard Breuhaus, David Carbaugh, Justin Hale, Darrell Hokuf, Al John, Doug Lane, Jill Langer, Russell Lee, Duke McMillin, Editorial director Writer Printer Keith Otsuka, David Presuhn, Wade Price, Jerome Schmelzer, Jill Langer Jeff Fraga ColorGraphics Corky Townsend