Browse Topic: Auxiliary power units

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DC-DC Converters for High Reliability eVTOL Auxiliary Power SystemsTBMG-5214712/01/2024
Virtual design of an opposed piston Range Extender engine2022-01-051603/29/2022
In the last decade, the 2-stroke opposed piston CI engines have demonstrated their potential as clean and efficient power-plants. However, most of the recent prototypes are relatively big, not suitable for a typical automobile range-extender, rated at 25-30 kW. The purpose of the paper is the virtual development an OP engine for this particular application. Generally speaking, an auxiliary power unit for an electric vehicle must be very compact, clean and efficient. Moreover, its operations should be as quiet as possible, with low vibrations A single cylinder, OP CI engine, coupled to two small electric motors (one for each crankshaft) can be a perfect candidate. First, the two-stroke cycle permits a reduction of load for the target power rate, enabling the implementation of a low temperature combustion mode (PCCI), that can provide ultra-low pollutant emissions and high thermal efficiencies. Second, the absence of poppet valves and camshafts is a fundamental advantage for reducing
Mattarelli, Enrico, Rinaldini, Carlo
Fluorescent Penetrant Inspection Aircraft Structures and Engine Component MaintenanceAMS2647G (Current)09/20/2021
This specification details requirements and procedures for the detection of defects in aircraft structural and engine components during maintenance and overhaul operations.
AMS K Non Destructive Methods and Processes Committee
Fluorescent Penetrant Inspection Aircraft Structures and Engine Component MaintenanceAMS2647G-TEST-REC (Historical)09/20/2021
This specification details requirements and procedures for the detection of defects in aircraft structural and engine components during maintenance and overhaul operations.
AMS K Non Destructive Methods and Processes Committee
Electronic Engine Control Hardware Change ManagementARP6109A (Current)06/22/2021
This document is intended for use by manufacturers of aircraft, engines and Electronic Engine Controls [EECs] as a component change process and evaluation guideline. Its purpose is to provide an effective means of managing the modification of electronic hardware. The process defined in this document is based upon: an understanding of the electronic component market evolution, e.g., obsolescence; lessons learned from the effects caused by the introduction of electrical component changes in a service fleet environment; industry best practice; and an understanding of the applicable regulations.
E-36 Electronic Engine Controls Committee
Procedure for the Continuous Sampling and Measurement of Non-Volatile Particulate Matter Emissions from Aircraft Turbine EnginesARP6320A (Historical)05/19/2021
This SAE Aerospace Recommended Practice (ARP) describes recommended sampling conditions, instrumentation, and procedures for the measurement of non-volatile particle number and mass concentrations from the exhaust of aircraft gas turbine engines. Procedures are included to estimate sampling system loss performance. This ARP is not intended for in-flight testing, nor does it apply to engines operating in the afterburning mode. This ARP is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances.
E-31P Particulate Matter Committee
Procedure for the Continuous Sampling and Measurement of Non-Volatile Particulate Matter Emissions from Aircraft Turbine EnginesARP6320A-TEST-REC (Historical)05/19/2021
This SAE Aerospace Recommended Practice (ARP) describes recommended sampling conditions, instrumentation, and procedures for the measurement of non-volatile particle number and mass concentrations from the exhaust of aircraft gas turbine engines. Procedures are included to estimate sampling system loss performance. This ARP is not intended for in-flight testing, nor does it apply to engines operating in the afterburning mode. This ARP is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances.
E-31P Particulate Matter Committee
Performance Testing of Lubricant Filter Elements Utilized in Aircraft Power and Propulsion Lubrication SystemsAIR1666C (Current)11/12/2020
This SAE Aerospace Information Report (AIR) reviews performance testing parameters for non-cleanable (often referred to as disposable) filter elements utilized in aircraft power and propulsion lubrication systems, including gas turbine engines and auxiliary power units (APUs), propulsion and transmission gear boxes, and constant speed drives and integrated drive generators (IDGs). This document is confined to laboratory testing of filter element performance to qualify the filtration medium and filter element construction as opposed to qualification of the complete filter assembly. The testing discussed here is usually followed by laboratory and on-engine testing of the entire lube filter assembly (including filter element, housing, valving, etc.), which is outside the scope of this AIR.
AE-5B Aircraft and Engine Fuel and Lubricant Sys Components
Performance Testing of Lubricant Filter Elements Utilized in Aircraft Power and Propulsion Lubrication SystemsAIR1666C-TEST-REC (Historical)11/12/2020
This SAE Aerospace Information Report (AIR) reviews performance testing parameters for non-cleanable (often referred to as disposable) filter elements utilized in aircraft power and propulsion lubrication systems, including gas turbine engines and auxiliary power units (APUs), propulsion and transmission gear boxes, and constant speed drives and integrated drive generators (IDGs). This document is confined to laboratory testing of filter element performance to qualify the filtration medium and filter element construction as opposed to qualification of the complete filter assembly. The testing discussed here is usually followed by laboratory and on-engine testing of the entire lube filter assembly (including filter element, housing, valving, etc.), which is outside the scope of this AIR.
AE-5B Aircraft and Engine Fuel and Lubricant Sys Components
Aircraft Thermal Management System EngineeringAIR5744 (Current)10/26/2020
The intent of this report is to encourage that the thermal management system architecture be designed from a global platform perspective. Separate procurements for air vehicle, propulsion system, and avionics have contributed to the development of aircraft that are sub-optimized from a thermal management viewpoint. In order to maximize the capabilities of the aircraft for mission performance and desired growth capability, overall system efficiency and effectiveness should be considered. This document provides general information about aircraft Thermal Management System Engineering (TMSE). The document also discusses approaches to processes and methodologies for validation and verification of thermal management system engineering. Thermal integration between the air vehicle, propulsion system, and avionics can be particularly important from a thermal management standpoint. Due to these factors, this report is written to encourage the development of a more comprehensive system
AC-9 Aircraft Environmental Systems Committee
Test Cell InstrumentationAIR5026B (Current)10/21/2020
This document discusses, in broad general terms, typical present instrumentation practice for post-overhaul gas turbine engine testing. Production engine testing and engine development work are outside the scope of this document as they will typically use many more channels of instrumentation, and in most cases will have requirements for measurements that are never made in post-overhaul testing, such as fan airflow measurements, or strain measurements on compressor blades. The specifications for each parameter to be measured, in terms of measurement range and measurement accuracy, are established by the engine manufacturers. Each test cell instrument system should meet or exceed those requirements. Furthermore, each instrument system should be recalibrated regularly, to ensure that it is still performing correctly.
EG-1E Gas Turbine Test Facilities and Equipment
Mathematical Modelling of Operating Processes in the Pneumatic Engine of the Car2020-01-222209/15/2020
The article presents studies of the operating process of the pneumatic engine, that can be installed on small vehicles as main or auxiliary power generating system. The aim is to assess the possibility of converting an internal combustion engine into a pneumatic engine capable of moving a vehicle with a small mass in urban settings with dense traffic flows using mathematical modelling. The behaviour in the operating processes of the engine under study has been performed by the computational method and verified experimentally at the installation created in the laboratory of the ICE department in Kharkiv National Automobile and Highway University. The computational technique in question differs from the existing ones because it is based on a dynamic model of an internal combustion engine. The developed pneumatic engine was mounted on the stand for determining its power, developed torque, compressed air consumption, pressure in its cylinders and the temperature of heating the engine. The
Leontiev, Dmitry Nikolaevich, Voronkov, Oleksandr, Korohodskyi, Volodymyr, Hlushkova, Diana, Nikitchenko, Igor, Teslenko, Eduard, Lykhodii, Oleksandr
Analytical Methodology to Derive a Rule-Based Energy Management System Enabling Fuel-Optimal Operation for a Series Hybrid2020-01-225709/15/2020
Due to the continuous electrification of vehicles, the variety of different hybrid topologies is expected to increase in the future. As the calibration of real-time capable energy management systems (EMS) is still challenging, a development framework for the EMS that is independent of the hybrid topology would simplify the overall development process of hybrid vehicles. In this paper an analytical methodology, which is used to derive a fuel-optimal, rule-based EMS for parallel hybrids, is transferred to a series topology. It is shown that the fundamental correlations can be applied universally to both parallel and series configurations. This enables the possibility to develop a real-time capable, rule-based controller for a series HEV based on maps that ensures a fuel-optimal operation. These maps provide the optimal power threshold for the activation of the auxiliary power unit and the optimal power output dependent on the driver’s power request. The implemented rule-based EMS
Jungen, Mario, Goerke, Daniel, Langwiesner, Morris, Schmiedler, Stefan, Geringer, Bernhard
Procedure for the Continuous Sampling and Measurement of Non-Volatile Particle Emissions from Aircraft Turbine EnginesAIR6241A (Current)07/28/2020
This Aerospace Information Report (AIR) is a historical technical record describing procedures, required continuous sampling conditions, and instrumentation for the measurement of non-volatile particle number and mass concentrations from the exhaust of aircraft gas turbine engines. Procedures are included to calculate sampling loss performance. This AIR is not intended for in-flight testing, nor does it apply to engine operating in the afterburning mode. This Aerospace Information Report is a historical technical record of the initial document detailing the measurement of non-volatile particle emissions at the exit plane of aircraft gas turbine engines. This methodology was adopted by ICAO into Annex 16 Vol II and updated into Aerospace Recommended Practice ARP6320. Future updates of this document may include explanations of the reasoning and assumptions used to develop this measurement methodology.
E-31P Particulate Matter Committee
Procedure for the Continuous Sampling and Measurement of Non-Volatile Particle Emissions from Aircraft Turbine EnginesAIR6241A-TEST-REC (Historical)07/28/2020
This Aerospace Information Report (AIR) is a historical technical record describing procedures, required continuous sampling conditions, and instrumentation for the measurement of non-volatile particle number and mass concentrations from the exhaust of aircraft gas turbine engines. Procedures are included to calculate sampling loss performance. This AIR is not intended for in-flight testing, nor does it apply to engine operating in the afterburning mode. This Aerospace Information Report is a historical technical record of the initial document detailing the measurement of non-volatile particle emissions at the exit plane of aircraft gas turbine engines. This methodology was adopted by ICAO into Annex 16 Vol II and updated into Aerospace Recommended Practice ARP6320. Future updates of this document may include explanations of the reasoning and assumptions used to develop this measurement methodology.
E-31P Particulate Matter Committee
A Power Split Hybrid Propulsion System for Vehicles with Gearbox2020-37-001406/23/2020
New internal combustion engines (ICE) are characterised by increasing maximum efficiency, thanks to the adoption of strategies like Atkinson cycle, downsizing, cylinder deactivation, waste heat recovery and so on. However, the best performance is confined to a limited portion of the engine map. Moreover, electric driving in urban areas is an increasingly pressing request, but battery electric vehicles use cannot be easily widespread due to limited vehicle autonomy and recharging issues. Therefore, in order to reduce ICE vehicle fuel consumption, by decoupling the ICE running from road load, as well as permit energy recovery and electric driving, hybrid propulsion systems are under development. This paper analyses a new patent solution for power split hybrid propulsion system with gearbox. The system comprises an auxiliary power unit, adapted to store and/or release energy, and a planetary gear set which is interposed between the ICE and the gearbox. The system is characterized by a
De Simio, Luigi, Gambino, Michele, Iannaccone, Sabato
Starting Process Control of a 2-Cylinder PFI Gasoline Engine for Range Extender2020-01-031504/14/2020
With the increasing worldwide concern on environmental pollution, battery electrical vehicles (BEV) have attracted a lot attention. However, it still couldn’t satisfy the market requirements because of the low battery power density, high cost and long charging time. The range-extended electrical vehicle (REEV) got more attention because it could avoid the mileage anxiety of the BEVs with lower cost and potentially higher efficiency. When internal combustion engine (ICE) works as the power source of range extender (RE) for REEV, its NVH, emissions in starting process need to be optimized. In this paper, a 2-cylinder PFI gasoline engine and a permanent magnet synchronous motor (PMSM) are coaxially connected. Meanwhile, batteries and load systems were equipped. The RE co-control system was developed based on Compact RIO (Compact Reconfigurable IO), Labview and motor control unit (MCU). Focused on the starting process, the effects of first firing speeds, throttle control strategies and
Li, Minglong, Zhang, Ran, Zeng, Xingyu, Ding, Weiqi, Mao, Weiang, Jin, Shaoye, Xu, Rufeng, Yuan, Dengke, Hu, Zongjie, Zhong, Zaimin, Li, Liguang
Real Time Energy Management Control Strategies for an Electrically Supercharged Gasoline Hybrid Vehicle2020-01-100904/14/2020
The high level of electric power available on a Hybrid Electric Vehicle (HEV) enables the introduction of electrical auxiliaries in addition or in substitution to the ones currently available on a conventional powertrain. Among these auxiliaries, electric Superchargers (eSC) for the improvement of the vehicle performance or electrically heated catalysts for the reduction of the light-off time of the after-treatment may dramatically affect the Energy Management System (EMS) of an HEV. Moreover, since these devices are only fluid-dynamically, but not mechanically, linked to the powertrain, they are traditionally neglected in the optimization of the powersplit between internal combustion engine and electric machines by the EMS. The aim of the current work is the development of an EMS that is able to consider in real time the overall electric energy consumption of the entire powertrain. More in detail, this activity focuses on the refinement of the Equivalent Consumption Minimization
Accurso, Francesco, Zanelli, Alessandro, Rolando, Luciano, Millo, Federico
Strategies to Gain the Loss in Power in a Military Diesel Engine Using JP-8 Instead of ULSD2020-01-080404/14/2020
The Department of Defense (DOD) has adopted the use of JP-8 under the “single battlefield fuel” policy. Fuel properties of JP-8 which are different from ULSD include cetane number, density, heating value and compressibility (Bulk modulus). While JP8 has advantages compared to ULSD, related to storage, combustion and lower soot emissions, its use cause a drop in the peak power in some military diesel engines. The engines that has loss in power use the Hydraulically actuated Electronic Unit Injection (HEUI) fuel system. The paper explains in details the operation of HEUI including fuel delivery into the injector and its compression to the high injection pressure before its delivery in the combustion chamber. The effect of fuel compressibility on the volume of the fuel that is injected into the combustion chamber is explained in details. A fuel such as JP-8 which has a lower Bulk modulus is compressed to a smaller volume than ULSD which has a higher Bulk modulus before its delivery in the
Raut, Prasad D., Atre, Omkar A., Trivedi, Manan, Henein, Naeim
Using Design of Experiments to Size and Calibrate the Powertrain of Range-Extended Electric Vehicle2020-01-084904/14/2020
A Range-Extended Electric Vehicle (REEV) usually has an auxiliary power source that can provide additional range when the main Rechargeable Energy Storage System (RESS) runs out. The range extender can be a fuel cell, a gas turbine, or an Internal Combustion Engine (ICE) bolted to a generator. Sizing the powertrain for a REEV is primarily to investigate the relationship between the capacity of the main RESS and the power rating of the range extender. Worldwide harmonized Light vehicles Test Procedures (WLTP) introduced a Utility Factor (UF) which is a curve used to calculate the weighted test results for the Off-Vehicle Charging-Hybrid Electric Vehicle (OVC-HEV) from the measured Charge Depleting (CD) mode range result, and the Charge Sustaining (CS) mode Fuel Consumption (FC). Therefore, the RESS capacity, the range extender power rating, the control strategy, and the UF are the key factors affecting the weighted FC of a REEV on the test cycle. The aim of this study is to demonstrate
Bao, Ran, Baxter, James, Revereault, Pascal
Aircraft Engine Technology Review - The Pathways for an Efficient, Cleaner and Quieter Aviation Industry2019-36-017501/13/2020
The aviation industry has been submitted to a set of environmental and commercial drivers that have led it to pursue engine technologies focused on the efficiency improvement, greenhouse (CO2) and pollutant (NOx and PM) emissions reductions, as well as noise abatement.The effort to comply with the ambitious long term environmental and efficiency targets set by the regulatory authorities has driven the aeronautic industry in a technological research effort. In the medium term, the aviation industry's strategy for commercial aviation is to focus on the advanced, but rather conventional propulsion systems (mainly turbofan engines). In this scenario, technological efforts have focused basically on enhancing thermal efficiency, through advanced core engines, as well as improving propulsive efficiency, through the use of low pressure systems (basically reduced pressure ratio and increased engine bypass ratio). To reach these objectives, a set of technological platforms has been proposed
Barbosa, Fábio Coelho
A Simulation Study for Hybrid Electric Vehicles with Gasoline Compression Ignition Technology2019-01-221812/19/2019
Strict pollutants regulations, real driving emissions compliance and CO2 reduction mandates are stretching the boundaries of traditional internal combustion engine (ICE) development. Despite major improvements in the last decade, car manufacturers still face challenges in simultaneous abatement of CO2 and local emissions of conventional diesel compression ignition and gasoline spark ignition powertrains. By combining a clean fuel like gasoline with a high efficiency thermodynamic cycle (compression ignition) it is possible to create a powertrain that is clean both globally and locally, and so breaking the historical trade-off between decreasing CO2 vs. pollutants criteria. The concept is known worldwide as Gasoline Compression Ignition (GCI). Very low vehicle out CO2 cannot be achieved if ICEs are not combined with a hybrid electric powertrain. Saudi Aramco also looks into the possibility of combining GCI with hybrid electric technologies. A 0D simulation of powertrain was performed
Won, Hyun-Woo
Auxiliary Power Take-off Drives for Agricultural TractorsJ717_201912 (Current)12/04/2019
This SAE Standard establishes specifications for mid- and side-power take-off drives that will be helpful in designing implements. Design of the implement attaching means must be tailored to each tractor, depending on attaching points available and the exact location of the auxiliary shaft.
Machine Technical Steering Committee
Test Method for Measuring Performance of Engine Cooling FansJ1339_201909 (Current)09/30/2019
This SAE Recommended Practice is intended for use in testing and evaluating the approximate performance of engine-driven cooling fans. This performance would include flow, pressure, and power. This flow and pressure information is used to estimate the engine cooling performance. This power consumption is used to estimate net engine power per SAE J1349. The procedure also provides a general description of equipment necessary to measure the approximate fan performance. The test conditions in the procedure generally will not match those of the installation for which cooling and fuel consumption information is desired. The performance of a given fan depends on the geometric details of the installation, including the shroud and its clearance. These details should be duplicated in the test setup if accurate performance measurement is expected. The performance at a given air density and speed also depends on the volumetric flow rate, or the pressure rise across the fan, since these two
Cooling Systems Standards Committee
Flight Deck Lighting for Commercial Transport AircraftARP4103A (Current)09/17/2019
This document recommends design and performance criteria for aircraft lighting systems used to illuminate flight deck controls, luminous visual displays used for transfer of information, and flight deck background and instrument surfaces that form the flight deck visual environment. This document is for commercial transport aircraft except for applications requiring night vision compatibility.
A-20A Crew Station Lighting
Safety Assessment of General Aviation Airplanes and Rotorcraft in Commercial ServiceARP5151A (Current)08/20/2019
This document describes a process that may be used to perform the ongoing safety assessment for (1) GAR aircraft and components (hereafter, aircraft), and (2) commercial operators of GAR aircraft. The process described herein is intended to support an overall safety management program. It is to help a company establish and meet its own internal standards. The process described herein identifies a systematic means, but not the only means, to assess continuing airworthiness. Ongoing safety management is an activity dedicated to assuring that risk is identified and properly eliminated or controlled. The safety management process includes both safety assessment and economic decision-making. While economic decision-making (factors related to scheduling, parts, and cost) is an integral part of the safety management process, this document addresses only the ongoing safety assessment process. This ongoing safety assessment process includes safety problem identification and corrective action
S-18C ARP5150A and ARP5151A Working Group
Response Surface Methodology (RSM) in Optimization of Performance and Exhaust Emissions of RON 97, RON 98, and RON 100 (Motor Gasoline) and AVGAS 100LL (Aviation Gasoline) in Lycoming O-320 Engine03-12-04-002908/19/2019
Federal Aviation Administration (FAA)’s 20 years of research and development with 200 unleaded blends and full-scale engine tests on 45 high-octane unleaded blends has not found a “drop-in” unleaded replacement for aviation gasoline (AVGAS) 100 low lead (100LL) fuel. In this study, analysis of compatibility via optimization of Lycoming O-320 engine fuelled with RON 97, RON 98, RON 100, and AVGAS was conducted using the Response Surface Methodology (RSM). Test fuels were compositionally characterized based on Gas Chromatography (GC) analysis and were categorized based on types of Hydrocarbon (HC). Basic fuel properties of fuels in this research were analyzed and recorded. For optimization analysis, engine speed and fuel were considered as the input parameters. The output responses were Brake Horsepower (BHP), Brake Thermal Efficiency (BTHE), Brake-Specific Fuel Consumption (BSFC), Exhaust Gas Temperature (EGT), Carbon Dioxide (CO2), Carbon Monoxide (CO), HC, and Nitrogen Oxides (NOx
Kumar, Thanikasalam, Mohsin, Rahmat, Majid, Zulkifli Abd., Ghafir, Muhammad Fahmi Abdul, Kim, Je Young, Wash, Ananth Manickam
Analysis of the Effect of Vehicle Platooning on the Optimal Control of a Heavy Duty Engine Thermal System2019-01-125904/02/2019
One promising method for reducing fuel consumption and emissions, particularly in heavy duty trucks, is platooning. As the distance between vehicles decreases, the following vehicles will experience less aerodynamic drag on the front of the vehicle. However, reducing the velocity of the air contacting the front of the vehicle could have adverse effects on the temperature of the engine. To compensate for this effect, the energy consumption of the engine cooling system might increase, ultimately limiting the overall improvements obtained with platooning. Understanding the coupling between drag reduction and engine cooling load requirement is key for successfully implementing platooning strategies. Additionally, in a Connected and Automated Vehicle (CAV) environment, where information of the future engine load becomes available, the operation of the cooling system can be optimized in order to achieve the maximum fuel consumption reduction. In this paper, a control-oriented physics-based
Block, Brian, Huynh, Brian, Boyle, Stephen, Stockar, Stephanie, Geyer, Stephen, Li, Jian, Huber, Jeffrey
Equivalent Consumption Minimization Strategy for a Power Split Supercharger2019-01-120704/02/2019
Low voltage hybridization (<60 V) supports engine start/stop, regenerative braking, and constrained torque assist/regeneration at a low cost. This work studies the potential benefits of a novel hybrid system, called a power split supercharger (PSS). A 9 kW motor is shared between boosting the engine or providing hybrid functionalities, allowing it to couple with a small engine and still support good acceleration. However, the PSS operation is limited to only one of the parallel hybrid or boosting modes at each time instance. In this work an equivalent consumption minimization strategy (ECMS) is developed to select the PSS mode and the motor torque during hybrid mode. The PSS operation is simulated over standard EPA drive cycles with an engine mean value model that captures detailed air path and PSS dynamics. The results show that on the combined cycle the PSS improves the vehicle fuel economy by around 20% compared to a vehicle with a turbocharged engine, which is more than 90% of the
Nazari, Shima, Middleton, Robert, Siegel, Jason, Stefanopoulou, Anna
VW's MEB platform: a modularity enabler19AUTP04_1204/01/2019
Volkswagen's MEB, an in-development chassis designed strictly for electric propulsion, enables a modular battery layout that can provide a Volkswagen Group electric vehicle (EV) with an estimated 200-mile to 300-mile (322-km to 483-km) driving range. Slated to debut in 2022 as the underpinnings for EVs produced in North America at the automaker's Chattanooga, Tennessee assembly plant, VW's MEB is intended for compact to midsize A- and B-class vehicles. “What we're investing in with MEB is a dedicated platform for electric vehicles to achieve packaging efficiency, more cabin space and more energy,” Matthew Renna, Vice President of the E-Mobility Product Line for Volkswagen North American Region, said during a recent MEB workshop for media in Chicago.
Buchholz, Kami
Thermal Analysis of Aircraft Auxiliary Power Unit: Application of Chemical Looping Combustion2019-01-139003/19/2019
An “APU” (Auxiliary Power Unit) is a small gas turbine engine to provide supplementary power to an aircraft and is located at the tails of larger jets. APU generators provide auxiliary electrical power for running aircraft systems on the ground. Applications include powering environmental systems for pre-cooling or preheating the cabin, and providing power for crew functions such as preflight, cabin cleanup, and galley (kitchen) operation and long-haul airliners must be started using pneumatic power of APU compressor. The Honeywell 131-9A gas turbine APU has 440 kW shaft power and 90 kW electric generator consuming 120 kg fuel/hour. Here the traditional combustor of the APU is proposed to be replaced by a chemical-looping-combustion (CLC) system. CLC system consist of two reactor one is oxidation reactor (air reactor) and the other is reduction reactor (fuel reactor).The system is fluidized bed system in which activated metal-oxide(MeO) participates and circulates between the reactors
Kumar, Prashant, AKRAM, MD, Singh, Anand Shankar, S, Sanjay
Thermal Analysis of Aircraft Auxiliary Power Unit: Potential of Super-Critical CO 2 Brayton Cycle2019-01-139103/19/2019
An “APU” (Auxiliary Power Unit) is a small gas turbine engine to provide supplementary power to an aircraft and is located at the tails of larger jets. APU generators provide auxiliary electrical power for running aircraft systems on the ground. Applications include powering environmental systems for pre-cooling or preheating the cabin, and providing power for crew functions such as preflight, cabin cleanup, and galley (kitchen) operation and long-haul airliners must be started using pneumatic power of APU compressor. The Honeywell 131-9A gas turbine APU has 440 kW shaft power and 90 kW electric generator consuming 120 kg fuel/hour. Hybrid power systems based on fuel cells are promising technology for the forthcoming power generation market. A solid oxide fuel cell (SOFC) is the perfect candidate for utilizing waste heat recovery. This case deals with waste heat recovery from fuel cell exhaust using Brayton cycle as bottoming cycle for additional power production. Here in this paper
Singh, Anand Shankar, Choudhary, Tushar, S, Sanjay
Procedure for the Calculation of Non-Volatile Particulate Matter Sampling and Measurement System Losses and System Loss Correction FactorsARP6481-TEST-REC (Historical)02/25/2019
This SAE Aerospace Recommended Practice (ARP) details the recommended process for correcting measured non-volatile Particulate Matter (nvPM) mass and number data for particle losses in the sampling and measurement system specified in ARP6320. This technique is only recommended for conditions where both nvPM mass and number concentration measurements are in the valid measurement ranges of the instruments which are discussed in the tool limitations section. This ARP also supplies an Excel® software tool with documentation to automate the process. The body of the ARP details the recommended calculation method, uncertainties and limitations of the system loss correction factors. It explains, in detail, the required inputs and outputs from the supplied Excel® software tool (developed on Windows 7, Excel® 2016). Also included are: The Excel® correction tools (Attachments I and V). Installation instructions for a Windows based computer (Attachment II). A user technical manual (Attachment III
E-31P Particulate Matter Committee
Procedure for the Calculation of Non-Volatile Particulate Matter Sampling and Measurement System Losses and System Loss Correction FactorsARP6481 (Historical)02/25/2019
This SAE Aerospace Recommended Practice (ARP) details the recommended process for correcting measured non-volatile Particulate Matter (nvPM) mass and number data for particle losses in the sampling and measurement system specified in ARP6320. This technique is only recommended for conditions where both nvPM mass and number concentration measurements are in the valid measurement ranges of the instruments which are discussed in the tool limitations section. This ARP also supplies an Excel® software tool with documentation to automate the process. The body of the ARP details the recommended calculation method, uncertainties and limitations of the system loss correction factors. It explains, in detail, the required inputs and outputs from the supplied Excel® software tool (developed on Windows 7, Excel® 2016). Also included are: The Excel® correction tools (Attachments I and V). Installation instructions for a Windows based computer (Attachment II). A user technical manual (Attachment III
E-31P Particulate Matter Committee
Aircraft Exhaust Nonvolatile Particle Matter Measurement Method DevelopmentAIR6037A (Current)11/20/2018
This report provides current practice measurement methods for quantifying nonvolatile particle matter at the exit plane of aircraft gas turbine engines. This document contains detailed information for many instruments and techniques, described in AIR5892A, that have been applied in aircraft engine field tests since AIR5892A was first issued in April 2003. There are four sections, identified as Technical Appendices (TA), presenting measurement techniques, sampling, and quantification of nonvolatile particles. The sections are written in the format of Aerospace Recommended Practice (ARP) documents and intended to progress to recommended practices upon overcoming existing technical challenges. Many important technical advances have been accomplished that comprise the Aircraft Engine Exhaust Nonvolatile Particle Matter Measurement Method Development techniques described in TA A: Particle Mass,TA B: particle Number and Size,TA C: Particle Sampling, and TA D: Calculation of Particle Number
E-31P Particulate Matter Committee
Environmental and Sustainability Aspects of an Aviation Auxiliary Power Unit Analyzed with the Aid of Exergy2018-32-007110/30/2018
During the past decade environmental and sustainability issues have become major problems to overcome since they have caused regional and global consequences. This paper discusses the environmental and sustainability aspects of Gas Turbine (GT) based aviation Auxiliary Power Unit (APU) analyzed with the aid of exergy. Exergy analysis is a potential tool to determine exergy destructions and losses and their true magnitudes and exact locations. In this study some exergy based parameters such as: exergetic efficiency, waste exergy ratio, exergy recoverability ratio, exergy destruction ratio, environmental impact factor, and exergetic sustainability index are proposed and investigated. Cycle operating parameters such as compressor-pressure-ratio (rp,c), Turbine Inlet Temperature (TIT) have been chosen for analysis of the gas turbine cycle based APU. Mathematical modeling of the cycle has been done and the same has been coded in MATLAB. Results show that increasing waste exergy ratio
Sahu, Aishi, Sahu, Mithilesh Kumar
Exhaust Energy Recovery with Variable Geometry Turbine to Reduce Fuel Consumption for Microcars2018-01-182509/10/2018
The objective proposed by EU to reduce by about 4%/year CO2 emission of internal combustion engines for the next years up to 2030, requires to increase the engine efficiency and accordingly improving the technology. In this framework, hybrid powertrains can have the possibility of a deep market penetration since they may recover energy during brake, allow the engine to operate in better efficiency conditions and with less transients, Moreover, they can recover a large amount of energy lost through the exhaust and use it to reduce fuel consumption. This paper concerns the modification of a conventional two in-line cylinders Diesel engine (440 cm3) adding a variable geometry turbine (VGT) coupled with a generator. The turbine is used to recover exhaust gas energy that otherwise would be lost. The generator, connected to the turbo shaft, converts mechanical energy into electrical energy and is used to charge the vehicle battery or the auxiliaries. The aim of this work is reducing fuel
Ortenzi, Fernando, Genovese, Antonino, Carrazza, Martina, Rispoli, Franco, Venturini, Paolo
Investigation of the Hybrid Operating Modes Regarding Efficiency, Emissions and Comfort for the Parallel-Series Hybrid Powertrain Concept DE-REX2018-01-182809/10/2018
The “Two-Drive-Transmission with Range-Extender” (called DE-REX) is an innovative hybrid powertrain concept using two electric motors and an internal combustion engine. The two electric motors are permanent magnet synchronous motors with a maximum power of 48 kW each. As combustion engine a 3 cylinder, turbocharged engine with a power of 65 kW is used. The aggregates are coupled to a transmission whose layout is characterized by consisting of two parallel 2-speed sub-transmissions. This layout offers a high flexibility and enables both parallel and series hybrid driving. The hybrid control unit (HCU) has to select the optimal driving mode and power distribution between the aggregates in regard to in some extend competing objectives like efficiency, emissions or driving comfort. In particular, the operation of the internal combustion engine with only two gear ratios is challenging. In the course of the publically funded DE-REX project, the DE-REX powertrain concept was designed
Fischer, S., Viehmann, A., Beidl, C., Rinderknecht, S.
Air Quality for Commercial Aircraft Cabin Particulate ContaminantsAIR4766/1 (Current)08/23/2018
This SAE Aerospace Information Report (AIR) covers airbone particulate contaminants that may be present in commercial aircraft cabin air during operation. Discussions cover sources of contaminants, methods of control and design recommendations. Air quality, ventilation requirements and standards are also discussed.
AC-9 Aircraft Environmental Systems Committee
Auxiliary Power Solutions for 1500 VDC Photovoltaic SystemsTBMG-3250608/01/2018
Photovoltaic systems are continually evolving to improve their efficiency and financial viability. One trend is to move to larger strings of cells giving higher dc voltages to be converted to ac voltage for the grid. Cost savings result, but auxiliary power supplies for monitoring and control need to accept these higher voltages as inputs.
Guide to Engine Lubrication System MonitoringAIR1828C-TEST-REC (Historical)04/10/2018
This SAE Aerospace Information Report (AIR) provides information and guidance for the selection and use of technologies and methods for lubrication system monitoring of gas turbine aircraft engines. This AIR describes technologies and methods covering oil system performance monitoring, oil debris monitoring, and oil condition monitoring. Both on-aircraft and off-aircraft applications are presented. A higher-level view of lubrication system monitoring as part of an overall engine monitoring system (EMS), is discussed in ARP1587. The scope of this document is limited to those lubrication system monitoring, inspection and analysis methods and devices that can be considered appropriate for health monitoring and routine maintenance. This AIR is intended to be used as a technical guide. It is not intended to be used as a legal document or standard.
E-32 Aerospace Propulsion Systems Health Management
Guide to Engine Lubrication System MonitoringAIR1828C (Current)04/10/2018
This SAE Aerospace Information Report (AIR) provides information and guidance for the selection and use of technologies and methods for lubrication system monitoring of gas turbine aircraft engines. This AIR describes technologies and methods covering oil system performance monitoring, oil debris monitoring, and oil condition monitoring. Both on-aircraft and off-aircraft applications are presented. A higher-level view of lubrication system monitoring as part of an overall engine monitoring system (EMS), is discussed in ARP1587. The scope of this document is limited to those lubrication system monitoring, inspection and analysis methods and devices that can be considered appropriate for health monitoring and routine maintenance. This AIR is intended to be used as a technical guide. It is not intended to be used as a legal document or standard.
E-32 Aerospace Propulsion Systems Health Management
Exergo-environmental Analysis of Basic and Intercooled-Recuperated Gas Turbine based Aviation Auxiliary Power Unit2018-01-137604/03/2018
This paper deals with the exergo-environmental analysis of gas turbine with possible application as aviation auxiliary-power-unit (APU). The present work reports a comparison of thermodynamic performance, NOx and CO emission for basic gas turbine cycle (BGT) and intercooled-recuperated gas turbine (IcRcGT) cycle based engines for possible use by the aviation industry as auxiliary power unit (APU). In addition to this environmental sustainability index of these two cycles is also presented. Various cycle operating parameters such as compressor-pressure-ratio (rp,c), combustor-primary-zone-temperature, equivalence-ratio, and residence time have been chosen for analysis of the cycles. Mathematical modeling of the cycles has been done and the same have been coded in MATLAB. Results show that IcRcGT cycle exhibits higher gas turbine power output and gas turbine efficiency in comparison to BGT cycle for the same rp,c and turbine inlet temperature (TIT). Percentage exergy destruction for
Sahu, Aishi, Sahu, Mithilesh Kumar, R, Sanjay
Comparison of 1-D Modelling Approaches for Wankel Engine Performance Simulation and Initial Study of the Direct Injection Limitations2018-01-145204/03/2018
Recent interest in the possible use of Wankel engines as range extenders for electric vehicles has prompted renewed investigations into the concept. While not presently used in the automotive industry, the type is well established in the unmanned aerial vehicles industry, and several innovative approaches to sealing and cooling have recently been developed which may result in improved performance for ground vehicle applications. One such UAV engine is the 225CS, a 225 cc/chamber single-rotor engine manufactured by Advanced Innovative Engineering (UK) Ltd. To be able to analyse the parameters, opportunities and limitations of this type of engine a model was created in the new dedicated Wankel modelling environment of AVL BOOST. For comparison a second model was created using the established method of modelling Wankel engines by specifying an ‘equivalent’ 3-cylinder 4-stroke reciprocating engine. The output from both of these models was evaluated using engine test data supplied by
Peden, Michael, Turner, Matthew, Turner, James W G, Bailey, Nathan
Review of Exhaust Gas Heat Recovery Mechanism for Internal Combustion Engine Using Thermoelectric Principle2018-01-136304/03/2018
Automotive power packs have been the focus of research over a long period of time. Among various power packs when we consider internal combustion engines, there is an ample opportunity in developing systems that can make optimal utilization of all the energy streams related to the automotive engine. In this regard utilization of internal combustion engine exhaust waste heat and environmental pollution have been the focus of research in the recent past. About 35% of the automotive input fuel energy is converted to useful crankshaft work and about 30% energy is expelled with exhaust. This leaves about one-third (35%) of the total energy that must be transmitted from the enclosed cylinder through the cylinder walls and head to the surrounding. The exhausted energy from engine results in entropy elevation and solemn environmental pollution. So it is desired to utilize waste heat to the extent possible. The recuperation and utilization of waste heat not only conserves fuel but also
Rathore, Souvik Singh, Singh, Anand, Kumar, Prashant, Alam, Nazish, Sahu, Mithilesh Kumar, R, Sanjay
Plain Bearings for Aerospace Applications18AERP02_0402/01/2018
Plain bearings are used across a wide range of aerospace applications to help achieve better fuel efficiency, extend maintenance intervals, and lower carbon emissions. These applications include installation in aircraft wing systems (flaps, spoilers, and slats), flight controls, cockpit controls, auxiliary power units, landing gear, door systems, and aircraft interiors (seats, bins, latches, and hinge points). “Our plain bearings even have a footprint on Mars,” said Brett Ricci, GGB Aerospace Strategic Account Manager for North America. “Operating in temperatures between −200°C to +280°C, our plain bearings have served as the primary suspension components in the robotic drilling arm of NASA's Curiosity Mars Rover since 2012.” Just as impressively, all of these applications are served by just two types of plain bearings: metal-polymer and fiber reinforced composite (FRC).
Plain Bearings for Aerospace ApplicationsTBMG-2839302/01/2018
Plain bearings are used across a wide range of aerospace applications to help achieve better fuel efficiency, extend maintenance intervals, and lower carbon emissions. These applications include installation in aircraft wing systems (flaps, spoilers, and slats), flight controls, cockpit controls, auxiliary power units, landing gear, door systems, and aircraft interiors (seats, bins, latches, and hinge points). “Our plain bearings even have a footprint on Mars,” said Brett Ricci, GGB Aerospace Strategic Account Manager for North America. “Operating in temperatures between -200°C to +280°C, our plain bearings have served as the primary suspension components in the robotic drilling arm of NASA’s Curiosity Mars Rover since 2012.”
Procedure for the Continuous Sampling and Measurement of Non-Volatile Particulate Matter Emissions from Aircraft Turbine EnginesARP6320-TEST-REC (Historical)01/05/2018
This SAE Aerospace Recommended Practice (ARP) describes recommended sampling conditions, instrumentation, and procedures for the measurement of non-volatile particle number and mass concentrations from the exhaust of aircraft gas turbine engines. Procedures are included to estimate sampling system loss performance. This ARP is not intended for in-flight testing, nor does it apply to engines operating in the afterburning mode. This ARP is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances.
E-31P Particulate Matter Committee
Procedure for the Continuous Sampling and Measurement of Non-Volatile Particulate Matter Emissions from Aircraft Turbine EnginesARP6320 (Historical)01/05/2018
This SAE Aerospace Recommended Practice (ARP) describes recommended sampling conditions, instrumentation, and procedures for the measurement of non-volatile particle number and mass concentrations from the exhaust of aircraft gas turbine engines. Procedures are included to estimate sampling system loss performance. This ARP is not intended for in-flight testing, nor does it apply to engines operating in the afterburning mode. This ARP is intended as a guide toward standard practice and is subject to change to keep pace with experience and technical advances.
E-31P Particulate Matter Committee
Penalties IN Performance of Three-Phase, Four-Wire, 400-Cycle Motors Caused by the Opening of One PhaseAIR34B (Current)11/30/2017
The scope of this SAE Aerospace Information Report (AIR) is to present a guide for the determination of probable power output and the effect on the aircraft system that will be experienced when operating three-phase motors with one phase open. Unfortunately, the above subject cannot be resolved by specific rules. Modern aircraft or missile electrical systems are composed of a wide variety of electrical and electronic components. These components react differently under identical impetus due to the latitude of their design. This latitude of design must be allowed wherever possible to the accessory designer due to the various specification requirements. Therefore, it cannot be over-emphasized that the effect on the airplane or missile system, as well as motor operation, of three-phase motors on two-phase power must be thoroughly investigated.
AE-7A Generators and Controls Motors and Magnetic Devices
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