NASA Guide to Engines a Guide for Educators and Students with Chemistry, Physics, and Math Activities
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
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. -
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 -
Spacecraft American Aerospace Controls
Spacecraft For More Than 50 Years, Our Experience Is Your Assurance™ AAC Manufactures high-reliability voltage and current sensors for: Satellites UAVs Commercial Aircraft Missiles Underwater Vehicles Military Aircraft Launch Systems Armored Vehicles Ships Helicopters Industrial Equipment Rail AAC is a Woman-Owned Business and all parts are manufactured at AAC’s Farmingdale, NY location. American Aerospace Controls 570 Smith Street, Farmingdale NY 11735 Phone: +1 (631) 694-5100 – Fax: +1 (631) 694-6739 http://a-a-c.com ©American Aerospace Controls 10-2016 Aircraft-UAVs Rail AAC Quality and Engineering Industrial Defense For More Than 50 Years, Our Experience is Your Assurance™ AAC Engineering and Quality Depart- Since 1965, American Aerospace Controls has been manufacturing high reliability ments are here to work with you on the AC & DC current, voltage and frequency sensors, transducers and detectors. With design and qualification of your parts. an emphasis on engineering solutions and customer support, AAC has developed Our vast experience in space flight app- long-term relationships with some of the largest aerospace, defense, transit and industrial companies around the globe. lications allows us to offer insight into the design and requirements of each unique Space Application. AAC main- AAC in Space tains the highest standards in Quality and Production. AAC sensors have been used on numerous manned and unmanned spacecraft, satellite, rocket and Unmanned Aerial Vehicle (UAV) programs. AAC has been involved with space flight applications since the mid-1960s. AAC’s extensive From the Mercury Program in the 1960’s to today’s international commercial and knowledge and decades of experience in designing and manufacturing defense satellite systems, AAC engineers have helped design current and voltage transducers and detectors capable of providing high reliability in harsh remote detectors and transducers that are the best available. -
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. -
Tethered Fixed-Wing Aircraft to Lift Payloads…
Tethered Fixed-Wing Aircraft to Lift Payloads: A Concept Enabled by Electric Propulsion David Rancourt Etienne Demers Bouchard Université de Sherbrooke Georgia Institute of Technology 3000 boul. Université – Pavillon P2 275 Ferst Drive NW Sherbrooke, QC Atlanta, GA CANADA USA [email protected] [email protected] Keywords: Electric propulsion, novel aircraft concept, VTOL, hybrid-electric powertrain ABSTRACT Helicopters have been essential to the military as they have been one of the only solutions for air-transporting substantial payloads with no need for complex mile-long runway infrastructures. However, they are fundamentally limited with high fuel consumption and reduced range. A disruptive concept to vertical lift uses tethered fixed-wing aircraft to lift a payload, where multiple aircraft collaborate and fly along a near circular flight path in hover. The Electric-Powered Reconfigurable Rotor concept (EPR2) leverages the recent progress in electric propulsion and modern controls to enable efficient load lifting using fixed-wing aircraft. The novel idea is to replace tethered manned aircraft (with onboard energy, fuel) with electric-powered fixed-wing aircraft with remote energy source to enable efficient collaborative load lifting. This paper presents the conceptual design of a heavy-lifting aircraft concept using electric-powered tethered fixed-wing aircraft for a ~30 metric ton lifting capability. A physics-based multidisciplinary design and simulation environment is used to predict the performance and optimize the aircraft flight path. It is demonstrated that this concept could hover with only 3.01 MW of power yet be able to translate to over 80 kts with minimal power increase by leveraging the benefits of complex non-circular flight paths. -
Wankel Powered Time to Climb World Record Attempt
Wankel powered time to climb world record attempt Presentation at Aero Expo, Friedrichshafen, Germany April 19th, 2018 by Paul Lamar Several years ago an American rotor head by the name of Russ MacFarlane living in Newcastle Australia decided to build a Mazda rotary powered world record attempt time to climb aircraft. Russ was a long time subscriber to the Rotary Engine News Letter. A used flying Harmon Rocket home built aircraft was purchased and the Lycoming engine and instruments were removed and sold. The aircraft is very similar to a Van's RV4 with longer landing gear and shorter wings. Dan Grey, owner of Aviation FX in Santa Paula California was chosen to finish the project and get it flying. I was the project engineer. Dan is a 787 captain for UAL. The Wankel rotary has a much better power to weight ratio and power to size ratio than any automotive piston engine. It is also far more robust and will withstand ungodly amounts of turbo boost with out structural failure. Up to 100 inches of Mercury manifold pressure is possible. That translates to almost 1000 HP for an all aluminum turbo two rotor weighing less than 200 pounds. That is about four HP per pound of engine weight. Most aircraft engines are about one HP per pound of weight or worse. Any piston engine operating at aircraft power levels has a limited life. That is the reason for a TBO. The moving parts are magnafluxed for cracks at TBO. The cracks are caused by reversing stress on the crankshaft, connecting rods, pistons and valve parts. -
2. Afterburners
2. AFTERBURNERS 2.1 Introduction The simple gas turbine cycle can be designed to have good performance characteristics at a particular operating or design point. However, a particu lar engine does not have the capability of producing a good performance for large ranges of thrust, an inflexibility that can lead to problems when the flight program for a particular vehicle is considered. For example, many airplanes require a larger thrust during takeoff and acceleration than they do at a cruise condition. Thus, if the engine is sized for takeoff and has its design point at this condition, the engine will be too large at cruise. The vehicle performance will be penalized at cruise for the poor off-design point operation of the engine components and for the larger weight of the engine. Similar problems arise when supersonic cruise vehicles are considered. The afterburning gas turbine cycle was an early attempt to avoid some of these problems. Afterburners or augmentation devices were first added to aircraft gas turbine engines to increase their thrust during takeoff or brief periods of acceleration and supersonic flight. The devices make use of the fact that, in a gas turbine engine, the maximum gas temperature at the turbine inlet is limited by structural considerations to values less than half the adiabatic flame temperature at the stoichiometric fuel-air ratio. As a result, the gas leaving the turbine contains most of its original concentration of oxygen. This oxygen can be burned with additional fuel in a secondary combustion chamber located downstream of the turbine where temperature constraints are relaxed. -
History of Solar Flight July 2008
History of Solar Flight July 2008 solar airplane aircraft continuous sustainable flight solar-powered solar cells mppt helios Sky-Sailor sun-powered HALE platform solaire avion vol continu dévelopement durable énergie solaire cellules plateforme History of Solar flight André Noth, [email protected] Autonomous Systems Lab, Swiss Federal Institute of Technology Zürich 1. The conjunction of two pioneer fields, electric flight and solar cells The use of electric power for flight vehicles propulsion is not new. The first one was the hydrogen- filled dirigible France in year 1884 that won a 10 km race around Villacoulbay and Medon. At this time, the electric system was superior to its only rival, the steam engine but then with the arrival of gasoline engines, work on electrical propulsion for air vehicles was abandoned and the field lay dormant for almost a century [2]. On the 30th June 1957, Colonel H. J. Taplin of the United Kingdom made the first officially recorded electric powered radio controlled flight with his model “Radio Queen”, which used a permanent-magnet motor and a silver-zinc battery. Unfortunately, he didn’t carry on these experiments. Further developments in the field came from the great German pioneer, Fred Militky, who first achieved a successful flight with a Radio Queen, 1957 free flight model in October 1957. Since this premises, electric flight continuously evolved with constant improvements in the fields of motors and batteries [12]. Three years before Taplin and Militky’s experiments, in 1954, photovoltaic technology was born at Bell Telephone Laboratories. Daryl Chapin, Calvin Fuller, and Gerald Pearson developed the first silicon photovoltaic cell capable of converting enough of the sun’s energy into power to run everyday electrical Gerald Pearson, Daryl Chapin equipment. -
Air-Breathing Engine Precooler Achieves Record-Breaking Mach 5 Performance 23 October 2019
Air-breathing engine precooler achieves record-breaking Mach 5 performance 23 October 2019 The Synergetic Air-Breathing Rocket Engine (SABRE) is uniquely designed to scoop up atmospheric air during the initial part of its ascent to space at up to five times the speed of sound. At about 25 km it would then switch to pure rocket mode for its final climb to orbit. In future SABRE could serve as the basis of a reusable launch vehicle that operates like an aircraft. Because the initial flight to Mach 5 uses the atmospheric air as one propellant it would carry much less heavy liquid oxygen on board. Such a system could deliver the same payload to orbit with a vehicle half the mass of current launchers, potentially offering a large reduction in cost and a higher launch rate. Reaction Engines' specially constructed facility at the Colorado Air and Space Port in the US, used for testing the innovative precooler of its air-breathing SABRE engine. Credit: Reaction Engines Ltd UK company Reaction Engines has tested its innovative precooler at airflow temperature conditions equivalent to Mach 5, or five times the speed of sound. This achievement marks a significant milestone in its ESA-supported Airflow through the precooler test item in the HTX heat exchanger test programme. UK company Reaction development of the air-breathing SABRE engine, Engines has tested its innovative precooler at airflow paving the way for a revolution in space access temperature conditions equivalent to Mach 5, or five and hypersonic flight. times the speed of sound. This achievement marks a significant milestone in the ESA-supported development The precooler heat exchanger is an essential of its air-breathing SABRE engine, paving the way for a SABRE element that cools the hot airstream revolution in hypersonic flight and space access. -
Design of a Micro-Aircraft Glider
Design of A Micro-Aircraft Glider Major Qualifying Project Report Submitted to the faculty of WORCESTER POLYTECHNIC INSTITUTE In partial fulfillment of the requirements for The Degree of Bachelor of Science Submitted by: ______________________ ______________________ Zaki Akhtar Ryan Fredette ___________________ ___________________ Phil O’Sullivan Daniel Rosado Approved by: ______________________ _____________________ Professor David Olinger Professor Simon Evans 2 Certain materials are included under the fair use exemption of the U.S. Copyright Law and have been prepared according to the fair use guidelines and are restricted from further use. 3 Abstract The goal of this project was to design an aircraft to compete in the micro-class of the 2013 SAE Aero Design West competition. The competition scores are based on empty weight and payload fraction. The team chose to construct a glider, which reduces empty weight by not employing a propulsion system. Thus, a launching system was designed to launch the micro- aircraft to a sufficient height to allow the aircraft to complete the required flight by gliding. The rules state that all parts of the aircraft and launcher must be contained in a 24” x 18” x 8” box. This glider concept was unique because the team implemented fabric wings to save substantial weight and integrated the launcher into the box to allow as much space as possible for the aircraft components. The empty weight of the aircraft is 0.35 lb, while also carrying a payload weight of about 0.35 lb. Ultimately, the aircraft was not able to complete the required flight because the team achieved 50% of its desired altitude during tests. -
Aerospace Manufacturing a Growth Leader in Georgia
Aerospace Manufacturing A Growth Leader in Georgia In this study: 9. Research Universities 10. GTRI and GTMI 1. Industry Snapshot 11. High-Tech Talent 3. A Top Growth Leader 12. Centers of Innovation 4. Industry Mix 13. World-Class Training Programs 6. Industry Wages and Occupational 15. Strong Partnerships and Ready Workforce Employment 16. Transportation Infrastructure 7. Pro-Business State 17. Powering Your Manufacturing Facility Community and Economic Development 8. Unionization 18. Aerospace Companies Aerospace Manufacturing A Growth Leader in Georgia Aerospace is defined as Aerospace Products and Parts Manufacturing as well as Other Support Activities for Air Transportation. Aerospace Georgia is the ideal home for aerospace include Pratt & Whitney’s expansion in companies with ¨¦§75 ¨¦§575 25+ employees companies. With the world’s most traveled Columbus in both 2016 and 2017, Meggitt «¬400 ¨¦§85 ¨¦§985 airport, eight regional airports, prominent Polymers & Composites’ expansion in military bases and accessibility to the Rockmart and MSB Group’s location in ¨¦§20 ¨¦§20 country’s fastest-growing major port, Savannah. For a complete list of new major ¨¦§85 Georgia’s aerospace industry serves a locations and expansions, see page 2. ¨¦§185 global marketplace. Georgia is also home to a highly-skilled workforce and world- ¨¦§16 Why Georgia for Aerospace? class technical expertise geared toward promoting the success of the aerospace • Highly skilled workers ¨¦§75 ¨¦§95 industry. Georgia’s business climate is • World-class technical expertise consistently ranked as one of the best • Renowned workforce training program in the country, with a business-friendly tax code and incentives that encourage • Increasing number of defense manufacturing growth for existing and personnel newly arriving companies. -
Micro-Jet Test Facility for Aerospace Propulsión Engineering Education*
Micro-Jet Test Facility for Aerospace Propulsión Engineering Education* G. L. JUSTE, J. L. MONTAÑÉS and A. VELAZQUEZ Universidad Politécnica de Madrid, School of Aeronautics, Aerospace Propulsión and Fluid Mechanics Department, Plaza del Cardenal Cisneros 3, 28040 Madrid, Spain. E-mail: [email protected] This paper describes the methodology that has been developed and implemented at the School of Aeronautics (ETSIA) of the Universidad Politécnica de Madrid (UPM) to familiarize aerospace engineering students with the operation ofreal complexjet engine systems. This methodology has a two-pronged approach: students carry out preparatory work by using, first, a gas turbine performance prediction numerical code; then they valídate their assumptions and results on an experimental test rig. When looking at the educational aspects, we have taken care that, apartfrom being sufficiently robust and flexible, the experimental set-up is similar to real jet engine rigs, so the students are not constrained to exploring a much too limited parametric space. Also, because a facility like this is usually subject to extensive and somewhat rugged use, we have focused on a low cosí design. Keywords: micro-jet engine test facility; aerospace propulsión INTRODUCTION should be considered: (1) a comprehensive under standing of these systems is based on acquiring AEROSPACE ENGINEERING EDUCATION theoretical, computational and experimental test in Europe is undergoing a significant change for knowledge, and (2) the cost of a jet engine experi two reasons: (1) the aerospace industry, which mental facility is too high for many public univer- used to be a mostly national concern, is now sities, not to mention the environmental aspects consolidating at the continental level, and (2) a associated with the fact that some of these institu- common frame of engineering education is devel- tions, like ours, are located in downtown áreas.