Runway Excursion After Loss of Thrust at Low Speed Runway Excursion After Loss of Thrust at Low Speed
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
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. -
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. -
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. -
What Is Quality? FOD &
What is Quality? FOD & ESD Presented by Janey Diogo 1 Agenda • Quality – Aerospace and Aviation • Foreign Object Debris (FOD) • Electrostatic Discharge (ESD) 2 What is Quality? • Quality is conformance to requirements. – For the product and the customer's requirements. – The system of quality is prevention. – The performance standard is zero defects (relative to requirements). – The measurement of quality is the price of nonconconformance. • Philip Crosby, a well known guru of Quality Management said “It is less expensive to do it right the first time than to pay for rework & repairs. • 3 Quality Assurance • A systematic process of checking to see whether a product or service being developed is meeting specified requirements. – Quality Assurance is a monitoring process. 4 Quality Control • A measure of excellence or a state of being free from defects, deficiencies and significant variations. – Quality Control is an evaluation process. 5 Quality History 1901 - Sir John Wolfe-Barry (the man who designed London's Tower Bridge) instigated the Council of the Institution of Civil Engineers to form a committee to consider standardizing iron and steel sections 1937 - Joseph Juran Introduced the Pareto principle (80/20 rule) 1937 - Hindenburg explosion 36 lives lost (ESD) 1946 - International Organization for Standardization founded in Geneva, Switzerland and the American Society for Quality Control (ASQC) was formed 1960 - First Quality Control Circles formed in Japan 1967 - Apollo 1 fire (ESD) 3 lives lost 1967 1970 - Apollo 13 Oxygen tank explosion (ESD) – No lives lost 6 Quality History 1977 - International Quality Control Circles formed 1979 - British Standard BS 5750 issued (replaced by ISO 9001 in 1987) 1980 - Aviation System Standards (AVN) focused on safety operations Managed by the FAA Safety and Quality Assurance Office 1986 - Six Sigma formulated by Bill Smith (Motorola) 1986 - Kaizen Institute established 1987 - Malcom Baldrige National Quality Award established 1988 - European Foundation for Quality management established by 14 European countries. -
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 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 .................................... -
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. -
Composites Fact Sheet
COMPOSITES FACT SHEET Composites Fact sheet Introduction to Composites Composites are lighter, stronger and have more design shape freedom than aluminium.1 These advantages are reasons why aircraft manufacturers use more composite materials in their aircraft nowadays. Composites increase the design shape freedom. For example, the Boeing 787 Dreamliner weight consists of 50% composite materials2 and is more aerodynamic than previous models due to more design flexibility of composites in comparison with metals. Low weight and better aerodynamics contribute to 20 – 30% less fuel consumption than today’s similarly sized aircraft.2 However composite material has a few disadvantages as well. Composites are susceptible to different kinds of damage than metal structures such as micro-cracking and delamination.3 Conventional damage detection methods are not optimized to detect these kind of damages. That is why additional structural weight is necessary to provide safety at all times.4 Furthermore, damage Figure 1: A Boeing 787 Dreamliner from Arkefly assessments of composites (Figure 1) take more time nowadays than traditional metal structures (Example 1) due to the lack of routine with the repair of these large structures. Example 1: WILLEMSTAD, September 25th, 2014 A Boeing 787 Dreamliner from Arkefly was involved in an incident with a ground vehicle. The aircraft was hit by a high-loader, which was supplying the aircraft at the time. Due to a thorough assessment by Arkefly in cooperation with Boeing the passengers were delayed for almost a day. After inspection it turned out the aircraft was not damaged by the ground vehicle and Arkefly received approval to fly to Amsterdam. -
Raspberry Pi Based Vision System for Foreign Object Debris (FOD) Detection
Bachelor Thesis Electrical Engineering June 2020 Raspberry Pi Based Vision System for Foreign Object Debris (FOD) Detection Sarfaraz Ahmad Mahammad Sushma Vendrapu Department of Mathematics and Nature Sciences Blekinge Institute of Technology SE–371 79 Karlskrona, Sweden This thesis is submitted to the Department of Mathematics and Nature Science at Blekinge Institute of Technology in partial fulfillment of the requirements for the degree of Bach- elor in Electrical Engineering with Emphasis on Telecommunication. Contact Information: Authors: Sarfaraz Ahmad Mahammad E-mail: [email protected] Sushma Vendrapu E-mail: [email protected] Supervisor: Prof. Wlodek J. Kulesza Industrial Supervisors: Dawid Gradolewski Damian M. Dziak Address: Bioseco Sp. z o. o. Budowlanych 68 Street 80-298 Gdansk´ Poland University Examiner: Irina Gertsovich Department of Mathematics and Nature Sci- Internet : www.bth.se ence Blekinge Institute of Technology Phone : +46 455 38 50 00 SE–371 79 Karlskrona, Sweden Fax : +46 455 38 50 57 Abstract Background: The main purpose of this research is to design and develop a cost-effective system for detection of Foreign Object Debris (FOD), dedicated to airports. FOD detection has been a significant problem at airports as it can cause damage to aircraft. Developing such a device to detect FOD may require complicated hardware and software structures. The proposed solution is based on a computer vision system, which comprises of flexible off the shelf components such as a Raspberry Pi and Camera Module, allowing the simplistic and efficient way to detect FOD. Methods: The solution to this research is achieved through User-centered design, which implies to design a system solution suitably and efficiently. -
Accident Prevention December 1993
F L I G H T S A F E T Y F O U N D A T I O N Accident Prevention Vol. 50 No. 12 For Everyone Concerned with the Safety of Flight December 1993 Training, Deicing and Emergency Checklist Linked in MD-81 Accident Following Clear-ice Ingestion by Engines While the crew of a Scandinavian Airlines System (SAS) jet transport was praised for its skill in executing an off-airport landing in an aircraft without operating engines, Swedish accident investigators found serious deficiencies in aircraft ground deicing procedures and no awareness of a throttle system that contributed to the severity of engine surges that destroyed both engines. Editorial Staff Report The crash of a Scandinavian Airlines System (SAS) McDonnell While the aircraft was being deiced on the ground, the Douglas DC-9-81 (MD-81) after clear ice was ingested by captain mentioned the procedure to follow in the event of the engines raises serious issues about training, quality an engine failure at Stockholm, saying (of the procedure), control and flight operations, an official Swedish aircraft “Engine failure follow … standard instrument departure accident investigation said. [SID] ... 2,000 ... that’s very general.” The aircraft’s right engine began to surge shortly after The aircraft took off at 0847 hours local time, the report takeoff from Stockholm/Arlanda Airport on Dec. 27, 1991, said. Sunrise was at 0848. Weather was reported at 0850 as according to a recent report by the Swedish Board of wind 360 degrees at 11 knots, visibility 6.2 miles (10 Accident Investigation (BAI). -
Mcdonnell Douglas DC 10-30, PP-VMD
McDonnell Douglas DC 10-30, PP-VMD AAIB Bulletin No: 7/97 Ref: EW/C97/2/1Category: 1.1 Aircraft Type and Registration: McDonnell Douglas DC 10-30, PP-VMD No & Type of Engines: 3 CF6 turbofan engines Year of Manufacture: 1975 Date & Time (UTC): 8 February 1997 at 2227 hrs Location: London Heathrow Airport Type of Flight: Scheduled Passenger Persons on Board: Crew - 18 - Passengers - 127 Injuries: Crew - None - Passengers - None Nature of Damage: No 7 and 8 wheels and tyres badly damaged Commander's Licence: Airline Transport Pilot's Licence Commander's Age: 50 years (approximately) Commander's Flying Experience: 14,000 hours (of which 4,500 were on type) Last 90 days - 60 hours Last 28 days - 20 hours Information Source: AAIB Field Investigation History of Flight The aircraft involved in this accident arrived at London HeathrowAirport from Rio de Janeiro earlier the same day at 1233 hrs. On arrival it was parked at Gate H30 and later towed to its departureGate H5 at 1945 hrs. At 2207 hrs the flight was cleared for enginestart and push-back and it commenced taxiing to Runway 27R nineminutes later. The taxi route to the runway took the aircraftdirectly onto the outer taxiway and then onto Runway 23 whichit backtracked. The total time spent taxiing was approximatelynine minutes. The flight destination was São Paulo, Brazil and, due tothe length of the flight, two flight deck crews were on board. The crew had arrived two days previously and, for the departure,consisted of a Captain in the left hand seat, who was undertakinga conversion from a different aircraft type, and a training Captainin the right hand seat who was the designated aircraft commander.