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
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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. -
Aircraft Engine Performance Study Using Flight Data Recorder Archives
Aircraft Engine Performance Study Using Flight Data Recorder Archives Yashovardhan S. Chati∗ and Hamsa Balakrishnan y Massachusetts Institute of Technology, Cambridge, Massachusetts, 02139, USA Aircraft emissions are a significant source of pollution and are closely related to engine fuel burn. The onboard Flight Data Recorder (FDR) is an accurate source of information as it logs operational aircraft data in situ. The main objective of this paper is the visualization and exploration of data from the FDR. The Airbus A330 - 223 is used to study the variation of normalized engine performance parameters with the altitude profile in all the phases of flight. A turbofan performance analysis model is employed to calculate the theoretical thrust and it is shown to be a good qualitative match to the FDR reported thrust. The operational thrust settings and the times in mode are found to differ significantly from the ICAO standard values in the LTO cycle. This difference can lead to errors in the calculation of aircraft emission inventories. This paper is the first step towards the accurate estimation of engine performance and emissions for different aircraft and engine types, given the trajectory of an aircraft. I. Introduction Aircraft emissions depend on engine characteristics, particularly on the fuel flow rate and the thrust. It is therefore, important to accurately assess engine performance and operational fuel burn. Traditionally, the estimation of fuel burn and emissions has been done using the ICAO Aircraft Engine Emissions Databank1. However, this method is approximate and the results have been shown to deviate from the measured values of emissions from aircraft in operation2,3. -
Stall/Surge Dynamics of a Multi-Stage Air Compressor in Response to a Load Transient of a Hybrid Solid Oxide Fuel Cell-Gas Turbine System
Journal of Power Sources 365 (2017) 408e418 Contents lists available at ScienceDirect Journal of Power Sources journal homepage: www.elsevier.com/locate/jpowsour Stall/surge dynamics of a multi-stage air compressor in response to a load transient of a hybrid solid oxide fuel cell-gas turbine system * Mohammad Ali Azizi, Jacob Brouwer Advanced Power and Energy Program, University of California, Irvine, USA highlights Dynamic operation of a hybrid solid oxide fuel cell gas turbine system was explored. Computational fluid dynamic simulations of a multi-stage compressor were accomplished. Stall/surge dynamics in response to a pressure perturbation were evaluated. The multi-stage radial compressor was found robust to the pressure dynamics studied. Air flow was maintained positive without entering into severe deep surge conditions. article info abstract Article history: A better understanding of turbulent unsteady flows in gas turbine systems is necessary to design and Received 14 August 2017 control compressors for hybrid fuel cell-gas turbine systems. Compressor stall/surge analysis for a 4 MW Accepted 4 September 2017 hybrid solid oxide fuel cell-gas turbine system for locomotive applications is performed based upon a 1.7 MW multi-stage air compressor. Control strategies are applied to prevent operation of the hybrid SOFC-GT beyond the stall/surge lines of the compressor. Computational fluid dynamics tools are used to Keywords: simulate the flow distribution and instabilities near the stall/surge line. The results show that a 1.7 MW Solid oxide fuel cell system compressor like that of a Kawasaki gas turbine is an appropriate choice among the industrial Hybrid fuel cell gas turbine Dynamic simulation compressors to be used in a 4 MW locomotive SOFC-GT with topping cycle design. -
Turbofan Engine Malfunction Recognition and Response Final Report
07/17/09 Turbofan Engine Malfunction Recognition and Response Final Report Foreword This document summarizes the work done to develop generic text and video training material on the recognition and appropriate response to turbofan engine malfunctions, and to develop a simulator upgrade package improving the realism of engine malfunction simulation. This work was undertaken as a follow-on to the AIA/AECMA report on Propulsion System Malfunction Plus Inappropriate Crew Response (PSM+ICR), published in 1998, and implements some of the recommendations made in the PSM+ICR report. The material developed is closely based upon the PSM+ICR recommendations. The work was sponsored and co-chaired by the ATA and FAA. The organizations involved in preparation and review of the material included regulatory authorities, accident investigation authorities, pilot associations, airline associations, airline operators, training companies and airplane and engine manufacturers. The FAA is publishing the text and video material, and will make the simulator upgrade package available to interested parties. Reproduction and adaptation of the text and video material to meet the needs of individual operators is anticipated and encouraged. Copies may be obtained by contacting: FAA Engine & Propeller Directorate ANE-110 12 New England Executive Park Burlington, MA 01803 1 07/17/09 Contributing Organizations and Individuals Note: in order to expedite progress and maximize the participation of US airlines, it was decided to hold all meetings in North America. European regulators, manufacturers and operators were both invited to attend and informed of the progress of the work. Air Canada Capt. E Jokinen ATA Jim Mckie AirTran Capt. Robert Stienke Boeing Commercial Aircraft Van Winters CAE/ Flight Safety Boeing Capt. -
Using an Autothrottle to Compare Techniques for Saving Fuel on A
Iowa State University Capstones, Theses and Graduate Theses and Dissertations Dissertations 2010 Using an autothrottle ot compare techniques for saving fuel on a regional jet aircraft Rebecca Marie Johnson Iowa State University Follow this and additional works at: https://lib.dr.iastate.edu/etd Part of the Electrical and Computer Engineering Commons Recommended Citation Johnson, Rebecca Marie, "Using an autothrottle ot compare techniques for saving fuel on a regional jet aircraft" (2010). Graduate Theses and Dissertations. 11358. https://lib.dr.iastate.edu/etd/11358 This Thesis is brought to you for free and open access by the Iowa State University Capstones, Theses and Dissertations at Iowa State University Digital Repository. It has been accepted for inclusion in Graduate Theses and Dissertations by an authorized administrator of Iowa State University Digital Repository. For more information, please contact [email protected]. Using an autothrottle to compare techniques for saving fuel on A regional jet aircraft by Rebecca Marie Johnson A thesis submitted to the graduate faculty in partial fulfillment of the requirements for the degree of MASTER OF SCIENCE Major: Electrical Engineering Program of Study Committee: Umesh Vaidya, Major Professor Qingze Zou Baskar Ganapathayasubramanian Iowa State University Ames, Iowa 2010 Copyright c Rebecca Marie Johnson, 2010. All rights reserved. ii DEDICATION I gratefully acknowledge everyone who contributed to the successful completion of this research. Bill Piche, my supervisor at Rockwell Collins, was supportive from day one, as were many of my colleagues. I also appreciate the efforts of my thesis committee, Drs. Umesh Vaidya, Qingze Zou, and Baskar Ganapathayasubramanian. I would also like to thank Dr. -
Axial Compressor Stall and Surge Prediction by Measurements
International Journal of Rotating Machinery (C) 1999 OPA (Overseas Publishers Association) N.V. 1999, Vol. 5, No. 2, pp. 77-87 Published by license under Reprints available directly from the publisher the Gordon and Breach Science Photocopying permitted by license only Publishers imprint. Printed in Malaysia. Axial Compressor Stall and Surge Prediction by Measurements H. HONEN * Institut jFtr Strahlantriebe und Turboarbeitsmaschinen, RWTH Aachen /Aachen University of Technology), 52062 Aachen, Germany (Received 3 April 1997;In final form 10 July 1997) The paper deals with experimental investigations and analyses of unsteady pressure dis- tributions in different axial compressors. Based on measurements in a single stage research compressor the influence of increasing aerodynamic load onto the pressure and velocity fluctuations is demonstrated. Detailed measurements in a 14-stage and a 17-stage gas turbine compressor are reported. For both compressors parameters could be found which are clearly influenced by the aerodynamic load. For the 14-stage compressor the principles for the monitoring of aerodynamic load and stall are reported. Results derived from a monitoring system for multi stage compressors based on these principles are demonstrated. For the 17-stage compressor the data enhance- ment of the measuring signals is shown. The parameters derived from these results provide a good base for the development of another prediction method for the compressor stability limit. In order design an on-line system the classification of the operating and load conditions is provided by a neural net. The training results of the net show a good agreement with different experiments. Keywords." Stall and surge monitoring, Unsteady pressure measurements, Compressor load analysis, Load parameters, Neural nets 1. -
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. -
The Predicted Performance of a Two-Spool Turbofan Engine in Rainstorms
THE PREDICTED PERFORMANCE OF A TWO-SPOOL TURBOFAN ENGINE IN RAINSTORMS By Tarik Baki Thesis presented for the degree of Masters of Science MSc to the faculty of Engineering Department of Mechanical Engineering Glasgow University April 1993. © Tarik Baki. ProQuest Number: 11007734 All rights reserved INFORMATION TO ALL USERS The quality of this reproduction is dependent upon the quality of the copy submitted. In the unlikely event that the author did not send a com plete manuscript and there are missing pages, these will be noted. Also, if material had to be removed, a note will indicate the deletion. uest ProQuest 11007734 Published by ProQuest LLC(2018). Copyright of the Dissertation is held by the Author. All rights reserved. This work is protected against unauthorized copying under Title 17, United States C ode Microform Edition © ProQuest LLC. ProQuest LLC. 789 East Eisenhower Parkway P.O. Box 1346 Ann Arbor, Ml 48106- 1346 ^1581 GLASGOW 1 UNIVERSITY LIBRARY f This thesis is dedicated to the memory of my kind and loving grand-mother Mama Hadja and my dear grand-father Hadj Tahar. You will always be present in our hearts. CONTENTS ACKNOWLEDGEMENTS NOMENCLATURE STATION NUMBERING SUMMARY PAGE CHAPTER I : GENERAL INTRODUCTION AND BACKGROUND 1.1. Introduction 4 1.1.1. Contribution made in the presentinvestigation 6 1.2. Historical development of gas turbines 7 1.3. Modem developments 9 1.4. Turbojet engine development 10 1.5. Transient behaviour of aircraft gas turbine 11 CHAPTER II : PERFORMANCE PREDICTION PROGRAM FOR TWO-SPOOL TURBOFAN ENGINE 2.1. Modelling of gas turbines 13 2.1.1. -
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 .................................... -
Performance Prediction of Gas Turbines by Solving a System of Non-Linear Equations
Tt qn> u Yf9 i-7tZ - 7J - - &s I I I I I I I I Lappeenrannan teknillinen korkeakoulu Lappeenranta University of Technology SEP itm I 1 I OSTI Juha Kaikko PERFORMANCE PREDICTION OF GAS TURBINES BY SOLVING A SYSTEM OF NON-LINEAR EQUATIONS Tieteellisia julkaisuja Research papers 68 DISCLAIMER Portions of this document may be illegible electronic image products. Images are produced from the best available original document. Lappeenrannan teknillinen korkeakoulu Lappeenranta University of Technology PERFORMANCE PREDICTION OF GAS TURBINES BY SOLVING A SYSTEM OF NON-LINEAR EQUATIONS Thesis for the degree of Doctor ofTechnotogy to be presented with due permission for public examination and criticism in the Auditorium in the Students ’ Union Building at Lappeenranta University of Technology, Lappeenranta, Finland on the 6th of March, 1998, at noon. Heteeilisia julkaisuja Research papers 68 ISBN 951-764-142-7 ISSN 0356-8210 Lappeenrannan teknillinen korkeakoulu Monistamo 1998 1 ABSTRACT Lappeenranta University of Technology Research papers 68 Juha Kaikko Performance Prediction of Gas Turbines by Solving a System of Non-Linear Equations Lappeenranta, 1998 91 pages, 27 figures, 10 tables ISBN 951-764-142-7, ISSN 0356-8210 UDK 621.438 : 519.6 Key words: gas turbine, performance, design, off-design, part-load, mathematical models This study presents a novel method for implementing the performance prediction of gas turbines from the component models. It is based on solving the non-linear set of equations that corresponds to the process equations, and the mass and energy balances for the engine. General models have been presented for determining the steady state operation of single components. -
Nasa Tm X-71633 Prediction of Compressor Stall For
NASA TECHN ICAL NASA TM X-71633 MEMORANDUM C,- PREDICTION OF COMPRESSOR STALL FOR DISTORTED AND UNDISTORTED FLOW BY USE OF A MULTISTAGE COMPRESSOR SIMULATION ON THE DIGITAL COMPUTER by Carl Jo Daniele and Fred Teren Lewis Research Center Cleveland, Ohio 44135 TECHNICAL PAPER to be presented at Thirteenth Aerospace Sciences Meeting sponsored by American Institute of Aeronautics and Astronautics Pasadena, California, January 20-22, 1975 (NASA-TM-X-71633) PREDICTION OF N75- 13190 COMPRESSOR STALL FOR DISTORTED AND UNDISTORTED FLOW BY USE OF A MULTISTAGE COMPRESSOR SIMULATION ON THE DIGITAL Unclas COMPUTER (NASA) 12 p HC $3.25 CSCL 20D G3/34 03669 PREDICTION OF COMPRESSOR STALL FOR DISTORTED AND UNDISTORTED FLOW BY USE OF A MULTISTAGE COMPRESSOR SIMULATION ON THE DIGITAL COMPUTER Carl J. Daniele and Fred Teren National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio Abstract 6 ratio of total pressure to sea level pressure A simulation technique is presented for the prediction of compressor stall for axial-flow com- a ratio of total temperature to sea level pressors for clean and distorted inlet flow. The temperature simulation is implemented on the digital computer and uses stage stacking and lumped-volume gas dy- p weight density, kg/m 3 ; ibm/ft 3 namics. The resulting nonlinear differential equations are linearized about a steady-state op- O flow coefficient erating point, and a Routh-Hurwitz stability test is performed on the linear system matrix. Par- pressure coefficient S allel compressor theory is utilized to extend the 0 technique to the distorted inlet flow problem. T temperature coefficient L The method is applied to the eight-stage J85-13 compressor. -
Preliminary Design and Optimization of Axial Turbines Accounting for Diffuser Performance
International Journal of Turbomachinery Propulsion and Power Article Preliminary Design and Optimization of Axial Turbines Accounting for Diffuser Performance Roberto Agromayor * and Lars O. Nord Department of Energy and Process Engineering, NTNU—The Norwegian University of Science and Technology, Kolbj. Hejes v. 1B, NO-7491 Trondheim, Norway; [email protected] * Correspondence: [email protected] Received: 19 May 2019; Accepted: 11 September 2019; Published: 18 September 2019 Abstract: Axial turbines are the most common turbine configuration for electric power generation and propulsion systems due to their versatility in terms of power capacity and range of operating conditions. Mean-line models are essential for the preliminary design of axial turbines and, despite being covered to some extent in turbomachinery textbooks, only some scientific publications present a comprehensive formulation of the preliminary design problem. In this context, a mean-line model and optimization methodology for the preliminary design of axial turbines with any number of stages is proposed. The model is formulated to use arbitrary equations of state and empirical loss models and it accounts for the influence of the diffuser on turbine performance using a one-dimensional flow model. The mathematical problem was formulated as a constrained, optimization problem, and solved using gradient-based algorithms. In addition, the model was validated against two test cases from the literature and it was found that the deviation between experimental data and model prediction in terms of mass flow rate and power output was less than 1.2% for both cases and that the deviation of the total-to-static efficiency was within the uncertainty of the empirical loss models.