Browse Topic: Aviation fuels

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Aircraft and Aircraft Engine Fuel Pump Low Lubricity Fluid Endurance TestARP1797B (Current)11/26/2025
This procedure is intended to apply to fuel pumps. This procedure will be defined in terms of recommended test fluid, test setup, test conditions, and test method. This procedure may be used for other fuel system components, by testing in conjunction with the pump, which normally supplies the component inlet flow, or a substitute test pump of similar capacity. This procedure may be used, with variations in test conditions and test fluid for performing pump evaluation tests. Tests at progressively increasing pump speeds and pressures will provide design limitation data. Alternate test periods on a test pump and another pump, of a design for which actual service durability is known, will provide useful comparison data.
AE-5B Aircraft and Engine Fuel and Lubricant Sys Components
Aviation Lubricant Tribology Evaluator (ALTE) Method to Determine the Lubricating Quality of Gas Turbine LubricantsARP6255A (Current)11/26/2025
Employing ‘ball-on-cylinder’ philosophy, a non-rotating steel ball is held in a vertically mounted chuck and using an applied load is forced against an axially mounted steel cylinder. The test cylinder is rotated at a fixed speed while being partially immersed in a lubricant reservoir. This maintains the cylinder in a wet condition and continuously transports a lubricating film of test fluid to the ball and cylinder interface. The diameter of the wear scar generated on the test ball is used as a measure of the fluid’s lubricating properties. The apparatus can be used, by adjusting the operating conditions, to reproduce two different wear mechanisms; mild and severe wear, the ALTE therefore has the ability to assess a lubricant’s performance in that regard.
E-34 Propulsion Lubricants Committee
SAE TOMORROW TODAY: A Breakthrough in Sustainable Aviation Fuel135022/17/2025
We often hear about sustainable fuel options when it comes to vehicles, but what about aerospace? With aviation fuel demand expected to rise to 160 billion gallons per year by 2050, new and innovative Sustainable Aviation Fuel (SAF) pathways are certainly needed. In response, CleanJoule has developed a proprietary manufacturing process that produces SAF with 10% higher energy density than average Jet A fuel. This process utilizes abundant biomass residue to create a cost-effective, drop-in replacement for conventional jet fuel. To learn more, we sat down with Mukund Karanjikar CEO, to discuss CleanJoule's mission is to create accessible, affordable and abundant SAF and reduce the aerospace industry's reliance on fossil fuels. We'd love to hear from you. Share your comments, questions and ideas for future topics and guests to podcast@sae.org. Don't forget to take a moment to follow SAE Tomorrow Today--a podcast where we discuss emerging technology and trends in mobility with the leaders
Hineman, Marcie
On-Board Fuel Sensing for UAS and Ground Vehicle Applications2024-01-41289/16/2024
Abstract The variability in fuel, particularly for fuel blends containing sustainable aviation fuels (SAFs), emphasizes the importance of understanding fuel properties for optimizing engine performance. This paper introduces spectroscopic fuel sensors capable of real-time estimation of jet fuel properties, mainly derived cetane number (DCN). While initially developed for unmanned aircraft systems (UAS), the paper explores their potential in ground vehicle applications: enhancing engine performance through sensing for feed-forward control and fuel property monitoring at fuel depots. The fuel sensing technologies are based on spectroscopic techniques coupled with machine learning (ML) approaches. The combination of these techniques demonstrates a promising solution for a wide spectrum of fuel applications.
Patel, Dev B., Sutar, Ashish, Abraham, Abhinav, Ambre, Dhananjay, Brezinsky, Kenneth, Lynch, Patrick T., Okada, Haruna, Stafford, Jacob M., Miganakallu, Niranjan, Sanders, Scott, Rothamer, David, Mayhew, Eric, Kim, Kenneth S.
Experimental and Numerical Investigation of Combustion and Noise, Vibrations, and Harshness Emissions in a Drone Jet Engine Fueled with Synthetic Paraffinic Kerosene01-17-01-00068/14/2023
Emissions and effects of climate change have prompted study into fuels that reduce global dependence on traditional fuels. This study seeks to investigate engine performance, thermochemical properties, emissions, and perform NVH analysis of Jet-A and S8 using a single-stage turbojet engine at three engine speeds. Experimental Jet-A results were used to validate a CFX simulation of the engine. Engine performance was quantified using thermocouples, pressure sensors, tachometers, flow meters, and load cells fitted to the engine. Emissions results were collected using an MKS Multigas Emissions Analyzer that examined CO, CO₂, H₂O, NOx, and THC. NVH analysis was conducted using a multifield, free-field microphone, and triaxial accelerometer. This study found that Jet-A operates at higher temperatures and pressures than S8, and S8 requires higher fuel flow rates than Jet-A, leading to poorer efficiency and thrust. S8 produced stronger vibrations over 5 kHz compared to Jet-A. S8 showed a
Soloiu, Valentin, Mcafee, John, Ilie, Marcel, Rowell, Aidan, Willis, James, Dillon, Nicholas
USE OF FIBER OPTICS OXYGEN SENSOR FOR AIRCRAFT FUEL TANK INERTING APPLICATION 2022-26-11635/26/2022
Aircraft fuel tanks are high risk zones as the ullage volume contain highly flammable fuel-air mixture. In the past, efforts have been made by various agencies to reduce this risk by designing an inerting system which significantly reduces the flammability risks. Regulations are also in place in order to reduce the potential for flammable vapor spaces in fuel tanks for the passenger aircrafts. One of the ways to reduce this risk is to continuously supply the inert gas like nitrogen to the ullage volume so that oxygen concentration is always kept to a level well below the flammability limit. It is therefore essential to measure continuously and accurately the oxygen concentration in the ullage volume of the fuel tank during entire operation of the aircraft. Current technologies have serious limitations in terms of sensor placement inside or near fuel tank and also in terms of continuous operation. This paper studies the limitations of current technologies available on oxygen measurement
Jha, Rajesh Kumar
Reimagining Transportation: Bio-MobilityTM2021-26-05199/22/2021
India has huge an opportunity to set an example for its commitment towards global GHG emissions reduction by 30-35% and reduction in dependency on imported fossil fuel. This can be achieved by the adoption of sustainable solutions and focus on transportation sector (air, water, and surface), which currently enables mobility across the country by using fossil fuels in internal combustion engines (ICE), albeit with the high cost of GHG emissions. The need of the hour, therefore, is the utilization of indigenous alternative sources of energy & fuels that can only curtail FOREX outflow but also mitigate risk of climate change. Biofuels, as a renewable transportation fuels (gases/liquids) is the best alternate source that complements fossil fuels. Biofuels are environmental friendly; enhances rural economy, and offer energy self-reliance within existing infrastructure of ICE mobility. Praj offers Bio-MobilityTMplatform solution, which envision the use of renewable bio-based feedstock for
Utgikar, Ravindra, Deshpande cEng, Ghanshyam, Padmanabhan PhD, Sasisanker, Joshi, Chaitanya Prakash
Evaluation and Comparison of Performance, Combustion characteristic, NOx and Particle Emission of JP-8, Gasoline and Diesel fuels in a Military Heavy duty 38.8 liters Compression Ignition Diesel Injection Engine Applying with EGR2021-01-11839/21/2021
Global emissions and stringent emission legislations have compelled us to search for alternative fuels for heavy-duty diesel engines. Evaluating the effect of JP-8 and gasoline on heavy-duty diesel engine performance and emissions is important for military combat vehicles under the "multi-fuel strategy program". Performance and fuel economy penalties are well established with the operation of a heavy-duty diesel engine with JP-8 and gasoline. Experimental studies have also suggested that JP-8 and gasoline have great potential for lowering NOx emissions. In the presented experimental study, the impact of using JP-8 and gasoline was evaluated on a military heavy-duty diesel engine. Engine combustion characteristics, performance, and emissions, especially NOx and nanoparticle emissions, were evaluated. All these parameters were compared for diesel, JP-8 and gasoline fuels by applying 7% EGR with supercharging at different load conditions for a heavy-duty, 12-cylinder, 580 kW, and 38.8
Pandey, Anand, Nandgaonkar, Milankumar, Varghese, Anil, sambasivan, Suresh, sonawane, C
DRYING OF THERMOSETTING COMPOSITE MATERIALSARP4977 (Current)5/14/2021
This SAE Aerospace Recommended Practice (ARP) describes standard methods for drying commercial aircraft composite structures prior to repair and gives general guidelines on use and applicability. It addresses the removal of liquids that have collected inside the structures through open damage, microcracks, or porosity and the removal of absorbed moisture from the composite material. The methods described in this document shall only be used when specified in an approved repair document or with the agreement of the original equipment manufacturer (OEM) or regulatory authority. If this document is used for the drying of materials other than thermosetting composite materials, the fitness for this purpose must be determined by the user.
AMS CACRC Commercial Aircraft Composite Repair Committee
Carbon Neutrality, Reduction and Offset-Aviation Solutions in the 21st Century2021-01-00393/2/2021
Begun in 2016, the Carbon Offsetting and Reduction Scheme for International Aviation (CORSIA) was developed and agreed by International Civil Aviation Organization (ICAO) 191 Member States, while the Airport Carbon Accreditation was developed by the Airports, Council International Europe as a carbon management system and certification. The aviation industry has its own offsetting scheme to measure aviation emissions and carbon offsetting and it has become the first industry sector which leads the world making commitments to reduce emissions. CORSIA and the Airport Carbon Accreditation are programs that impose carbon management obligations on the aviation industry. The training product to be presented, will clarify for the first time how to go beyond mere compliance and exceed the carbon reduction requirements of these instruments by achieving carbon neutrality in operations, to decrease costs, boost revenue, productivity and customer experience for airlines, airports and ground service
Nyamdorj, Bolormaa, Anaka, Wayne, Stoica, Andrei, Sushant, Sushant, Ortega, Joshua, Helm, Brittney, Moreira, Paula
Thermodynamic and Emission Performance Analysis of CMC Bladed Gas Turbine2021-01-00303/2/2021
Increasing in the turbine rotor inlet temperature improves the aviation gas turbine efficiency, while on the other hand, but also leads to a higher requirement for blade cooling air, which in turn reduces the gain in efficiency achieved by increasing temperature. Turbine rotor inlet temperature has been increasing with the entry of highly-efficient gas turbines have been developed for the last decades for the aviation market. Around one fifth of the compressed air is extracted from the compressor and is used for blade cooling purposes and is thus not used in the actual power/thrust generation process, which has a negative impact on the engine efficiency. For this reason, new cooling methods and hot-gas path component materials that will be compatible with these high temperature’s gases are among the areas being analyzed. The ceramic-matrix-composite (CMC) material have the potential to reduce or eliminate the need of cooling of hot-gas - path component i.e. blades of turbine thereby
Kumari, Anupam, S, Sanjay
Jet Reference Fluid Study for Fuel Tank SealantsAIR4275B (Current)2/3/2021
This information report covers two distinct projects to formulate Jet Refrence Fluids (JRF) for testing of material compatibility. The first effort began in 1978 and focused on producing a formulation (JRF-2) that simulated JP-4 and included composition with metallic ions that reproduced chalking of fuel tank sealants. This effort resulted in the preparation of AMS2629 that defined the formulation of JRF-2 (Type 1) and the same formulation with metallic ions (Type 2). The second effort began in 2002 and focused on preparing a JRF that simulated Jet A, JP-5 and JP-8. This effort went through multiple iterations, but eventually resulted in a JRF-3 formulation composed of Jet A plus military additives spiked to 25% aromatic content and high levels of sulfur experienced in the global fuel supply. Since the metallic ions added to JRF-2 demonstrated their ability to simulate a chalking reaction, chalking was not tested with the ions added to JRF-3. AMS2629 was changed multiple times to
AMS G9 Aerospace Sealing Committee
Jet Reference Fluid Study for Fuel Tank SealantsAIR4275B-TEST-REC (Historical)2/3/2021
This information report covers two distinct projects to formulate Jet Refrence Fluids (JRF) for testing of material compatibility. The first effort began in 1978 and focused on producing a formulation (JRF-2) that simulated JP-4 and included composition with metallic ions that reproduced chalking of fuel tank sealants. This effort resulted in the preparation of AMS2629 that defined the formulation of JRF-2 (Type 1) and the same formulation with metallic ions (Type 2). The second effort began in 2002 and focused on preparing a JRF that simulated Jet A, JP-5 and JP-8. This effort went through multiple iterations, but eventually resulted in a JRF-3 formulation composed of Jet A plus military additives spiked to 25% aromatic content and high levels of sulfur experienced in the global fuel supply. Since the metallic ions added to JRF-2 demonstrated their ability to simulate a chalking reaction, chalking was not tested with the ions added to JRF-3. AMS2629 was changed multiple times to
AMS G9 Aerospace Sealing Committee
Q&A21TOFHP02_112/1/2021
Commercial vehicles run under a wide range of operating conditions and duty cycles - not all are well-suited for battery-electric propulsion, particularly in the near term. For those hard-to-electrify vehicles, renewable diesel is a viable option to reduce greenhouse-gas emissions “practically overnight,” according to Matt Leuck, technical manager for Renewable Road Transportation in North America for Neste, which claims to be the world's largest producer of renewable diesel and jet fuel. Preparing to participate in the “Low/Zero Carbon Fuels” technical session during the SAE Government/Industry Digital Summit on February 2-3, Leuck said that Neste sees strong, sustained growth for renewable diesel in medium- and heavy-duty road vehicles, as well as in other segments such as mobile machines used at mines and construction sites. “In fact, demand growth has the potential to increase fivefold in the decades ahead,” he shared. “This growth is driven by two key things: end-users are setting
Gehm, Ryan
Connectors, Fiber Optic, Advanced, Circular or Rectangular, Plug and Receptacle, Environment Resistant, Removable Termini/Contacts, General Specification ForAS5590B (Current)11/30/2020
This specification covers the performance requirements for a plug and receptacle. The connector inserts may contain multiple termini or multiple termini and electrical contacts. The connectors use removable termini, or removable termini and electrical contacts, and are capable of operating within a temperature range of −65 to +200 °C (see 1.2.1.1). These connectors are supplied under AS9100 reliability assurance program.
AS-3 Fiber Optics and Applied Photonics Committee
Connectors, Fiber Optic, Advanced, Circular or Rectangular, Plug and Receptacle, Environment Resistant, Removable Termini/Contacts, General Specification ForAS5590B-TEST-REC (Historical)11/30/2020
This specification covers the performance requirements for a plug and receptacle. The connector inserts may contain multiple termini or multiple termini and electrical contacts. The connectors use removable termini, or removable termini and electrical contacts, and are capable of operating within a temperature range of −65 to +200 °C (see 1.2.1.1). These connectors are supplied under AS9100 reliability assurance program.
AS-3 Fiber Optics and Applied Photonics Committee
Vehicle, Magnetic Particle Inspection Petroleum BaseAMS2641D (Current)10/9/2020
This specification covers two types of refined hydrocarbon compounds in the form of liquids. This specification only covers newly manufactured materials.
AMS K Non Destructive Methods and Processes Committee
Methodology and Results of Testing an Impact of F-34 Fuel on the Engine Reliability2020-01-21339/15/2020
An application of the new kind of the fuel for the diesel engine requires to conduct the qualification tests of the engines powered by this his fuel which allow assessing an impact of fuel on the engine reliability. Such a qualification test of the piston and turbine engines of the aircraft stationed on the ground and land vehicles is described in the NATO standardisation agreement (STANAG) 4195 as the AEP-5 test. The methodology and selected results of the qualification tests of the SW-680 turbocharged multi-purpose diesel engine fuelled with F-34 fuel have been presented in this paper. A dynamometric stand with the SW-680 engine has been described. Based on the preliminary results of the investigation it has been found that a change in a type of the fuel from IZ-40 diesel fuel into F-34 kerosene-type one has reduced a maximum engine torque by about 4%. This has been primarily due to a lower fuel density of F-34 by about 3%. Finally, it has been found that this does not require any
Walentynowicz, Jerzy
Methodology and Results of F-34 Fuel Impact on the Reliability of the Engine Injection System on the Non-Engine-Based Test Stand2020-01-22619/15/2020
The study of the F-34 aviation fuel used to power a diesel engine requires an extensive testing programme be carried out in the steady and transient states of the engine operation. The researches of the engines are expensive therefore, the tests can be also performed on the non-engine-based stand at a lower price. The design of the non-engine-based test stand and the methodology of the engine injection system testing follow the AEP-5 qualifying test has been described in the paper. The measurement methods used on the stand and the selected measurement results are presented. The tests have included checking the changes of three basic sets of the injection systems that may be subject to wear during the operation of the system. This applies to the following assemblies: jet needle - injection nozzle body, delivery valve plug - carrier, injection pump plunger and barrel. The non-disassembly measurement methods used to assess the state of wear of the injection system assemblies have been set
Walentynowicz, Jerzy
Fuel Dispensing Filter Test MethodsJ2793_202005 (Current)5/26/2020
This SAE Recommended Practice is applicable to gasoline and diesel fuel filters installed on fuel dispensing equipment, mobile or stationary. It describes a set of tests used to characterize the structural integrity, filtration performance, and reaction to water contaminant with fuel dispensing filters.
Filter Test Methods Standards Committee
Fuel Dispensing Filter Test MethodsJ2793_202005-TEST-REC (Historical)5/26/2020
This SAE Recommended Practice is applicable to gasoline and diesel fuel filters installed on fuel dispensing equipment, mobile or stationary. It describes a set of tests used to characterize the structural integrity, filtration performance, and reaction to water contaminant with fuel dispensing filters.
Filter Test Methods Standards Committee
Fluid, Jet ReferenceAMS2629F (Current)3/12/2020
This specification covers a mixture of liquid hydrocarbons and soluble additives.
AMS G9 Aerospace Sealing Committee
A MATLAB Simulink Based Co-Simulation Approach for a Vehicle Systems Model Integration Architecture2020-01-00053/10/2020
In this paper, a MATLAB-Simulink based general co-simulation approach is presented which supports multi-resolution simulation of distributed models in an integrated architecture. This approach was applied to simulating aircraft thermal performance in our Vehicle Systems Model Integration (VSMI) framework. A representative advanced aircraft thermal management system consisting of an engine, engine fuel thermal management system, aircraft fuel thermal management system and a power and thermal management system was used to evaluate the advantages and tradeoffs in using a co-simulation approach to system integration modeling. For a system constituting of multiple interacting sub-systems, an integrated model architecture can rapidly, and cost effectively address technology insertions and system evaluations. Utilizing standalone sub-system models with table-based boundary conditions often fails to effectively capture dynamic subsystem interactions that occurs in an integrated system
Raczkowski, Brian C., Jones, Nicholas, Deppen, Tim, Lucas, Charles, Yeu, Rodney, Walters, Eric, Donovan, Adam, Patnaik, Soumya, Bodie, Mark
A MATLAB Simulink Based Co-Simulation Approach for a Vehicle Systems Model Integration Architecture2020-01-00053/10/2020
In this paper, a MATLAB-Simulink based general co-simulation approach is presented which supports multi-resolution simulation of distributed models in an integrated architecture. This approach was applied to simulating aircraft thermal performance in our Vehicle Systems Model Integration (VSMI) framework. A representative advanced aircraft thermal management system consisting of an engine, engine fuel thermal management system, aircraft fuel thermal management system and a power and thermal management system was used to evaluate the advantages and tradeoffs in using a co-simulation approach to system integration modeling. For a system constituting of multiple interacting sub-systems, an integrated model architecture can rapidly, and cost effectively address technology insertions and system evaluations. Utilizing standalone sub-system models with table-based boundary conditions often fails to effectively capture dynamic subsystem interactions that occurs in an integrated system
Raczkowski, Brian C., Jones, Nicholas, Deppen, Tim, Lucas, Charles, Yeu, Rodney, Walters, Eric, Donovan, Adam, Patnaik, Soumya, Bodie, Mark
Green Jet Fuel Additive Made from Acetone Plus LightTBMG-361733/1/2020
A domestically generated additive was made by taking biomass-derived acetone — common nail polish remover — and using light to upgrade it to higher-mass hydrocarbons. It can be blended with conventional jet fuel to fly while providing environmental benefits.
O-Ring Machined from AMS3617 MaterialAS9772A (Current)1/13/2020
This standard establishes the dimensional and visual quality requirements, lot requirements, and packaging and labeling requirements for O-rings machined from AMS3617 polyamide material. It shall be used for procurement purposes.
A-6C2 Seals Committee
Engineered Solutions for Enclosure Sealing and InsulationTBMG-3566812/1/2019
In the aerospace and defense industries, enclosure sealing and insulation needs to meet challenging and complex requirements. For example, the EMI gaskets that are used in military touchscreens must shield sensitive electronics from electromagnetic interference (EMI) while providing electrical conductivity and ensuring environmental sealing. These enclosure gaskets must also cushion the unit from mechanical shock and avoid interfering with the display's touch function.
Considerations for Hydrogen Fuel Cells in Airborne ApplicationsAIR7765 (Current)11/18/2019
The scope of this joint EUROCAE/SAE report is to compile the considerations relating to airborne application of hydrogen fuel cells. This document provides a comprehensive analysis of the use of hydrogen as a fuel by describing its existing applications and the experience gained by exploiting fuel cells in sectors other than aviation. The use of hydrogen fuel cells in aircraft can help in meeting aviation environmental targets (including noise pollution) and can be vital to achieving efficient electrically propelled air vehicles. The experience gained with mature fuel cells in terrestrial applications and the handling of other gases in aviation, as presented herein, will help in alleviating safety concerns and in demystifying the usage of hydrogen in aviation.
AE-7F Hydrogen and Fuel Cells
Low- to High-Temperature Reaction Transition in a Small-Bore Optical Gasoline Compression Ignition (GCI) Engine03-12-05-00318/19/2019
Abstract This study shows the development of low-temperature and high-temperature reactions in a gasoline-fuelled compression ignition (GCI) engine realizing partially premixed combustion for high efficiency and low emissions. The focus is how the ignition occurs during the low- to high-temperature reaction transition and how it varies due to single- and double-injection strategies. In an optically accessible, single-cylinder small-bore diesel engine equipped with a common-rail fuel injection system, planar laser-induced fluorescence (PLIF) imaging of formaldehyde (HCHO-PLIF), hydroxyl (OH-PLIF), and fuel (fuel-PLIF) has been performed. This was complemented with high-speed imaging of combustion luminosity and chemiluminescence imaging of cool flame and OH*. The diagnostics were performed for two different fuels including conventional diesel as a reference case and then a kerosene-based jet fuel which is a low-ignition quality fuel with cetane number of 30, firstly with single near top
Goyal, Harsh, Zhang, Yilong, Kook, Sanghoon, Kim, Kenneth S., Kweon, Chol-Bum
Identification and Quantification of Phosphate Ester-Based Hydraulic Fluid in Jet Fuel04-12-01-00033/13/2019
Phosphate ester-based hydraulic fluids are commonly used in aviation, due to their fire-resistant properties. However, contamination of jet fuel with hydraulic fluid may cause serious engine failure, hot corrosion of metals, and swelling of elastomer and polymer seals. Identifying and quantifying hydraulic fluids in jet fuels using chromatography is challenging since common hydraulic fluids, such as ExxonMobil™ HyJet™ V and Skydrol™ LD-4, are composed of tri-butyl phosphate, the main peak of which overlaps with peaks from jet fuels in chromatograms. In this work, three techniques to separate and differentiate the jet fuel peaks from the tri-butyl phosphate peaks were developed. Two methods are based on a solid phase extraction (SPE) procedure followed by identification and quantification, which is carried out using a gas chromatograph equipped with a mass spectrometer or a flame ionization detector. The third technique is single-staged, where the separation and analysis are carried out
Stamker Gertopski, Diana, Tartakovsky, Konstantin, Rabaev, Moshe
Sleeve, Hose Assembly, Fire ProtectionAS1072F (Current)1/7/2019
This standard defines the requirements for bulk protective sleeve to provide fire resistance for aircraft hose assemblies, which will enable these assemblies to meet the requirements of AS1055. NOTE: Use of this sleeve does not eliminate the need to demonstrate that the sleeved assemblies will meet the applicable requirements of AS1055.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
Influences of Butanol Blends on Combustion and Emissions of a Small SI Engine2018-32-005810/30/2018
In the general efforts to replace the fossil fuels in transportation by renewable fuels the bioalcohols are an important alternative. The global share of Bioethanol used for transportation is continuously increasing. Butanol, a four-carbon alcohol, is considered in the last years as an interesting alternative fuel, both for Diesel and for Gasoline application. Its advantages for engine operation are: good miscibility with gasoline and diesel fuels, higher calorific value than Ethanol, lower hygroscopicity, lower corrosivity and possibility of replacing aviation fuels. In the present work research with different nButanol portions in gasoline (BuXX)* was performed on the 2-cylinder SI engine with variations of several parameters on engine dynamometer. At different steady state operating points were varied: spark timing (αz), air excess factor (λ) and EGR-rate. Furthermore, the conversion rates and light-off of a 3-way-catalyst were investigated. As research tools the combustion pressure
Czerwinski, Jan, Güdel, Martin, Engelmann, Danilo, Pechout, Martin
Novel Turboelectric Aircraft DesignTBMG-288615/1/2018
NASA Langley Research Center has developed a novel aircraft design that can carry 150+ passengers over a range of 3,500 nautical miles. Key features include a turboelectric propulsion system, twin underwing turbofans, and a rear-fuselage, electrically driven, boundary layer ingesting fan. The design is developed for single-aisle-class aircraft (the largest commercial transport class in the world) to significantly reduce fuel burn compared to current aircraft.
Guidance on the Impact of Fuel Properties on Fuel System Design and OperationAIR7484 (Current)2/24/2018
This document describes a number of jet fuel properties and where applicable gives the specification limits for Jet A and Jet A-1, though the properties are generally applicable to all turbine fuels. Later versions of this document will give more details on specification limits for other similar fuels, such as TS-1, where they differ from Jet A and Jet-A1. It gives details about the possible impact on airframe fuel system design.
AE-5A Aerospace Fuel, Inerting and Lubrication Sys Committee
The Application of New Approaches to the Analysis of Deposits from the Jet Fuel Thermal Oxidation Tester (JFTOT)2017-01-229310/8/2017
Studies of diesel system deposits continue to be the subject of interest and publications worldwide. The introduction of high pressure common rail systems resulting in high fuel temperatures in the system with the concomitant use of fuels of varying solubilizing ability (e.g. ULSD and FAME blends) have seen deposits formed at the tip of the injector and on various internal injector components. Though deposit control additives (DCAs) have been successfully deployed to mitigate the deposit formation, work is still required to understand the nature and composition of these deposits. The study of both tip and internal diesel injector deposits (IDID) has seen the development of a number of bench techniques in an attempt to mimic field injector deposits in the laboratory. One of the most used of these is the Jet Fuel Thermal Oxidation Tester or JFTOT (ASTM D3241). The tester was originally designed to assess the oxidation of jet fuel, based on the principle that low stability fuels produce
Barker, Jim, Reid, Jacqueline, Angel Smith, Sarah, Snape, Colin, Scurr, David, Langley, Graham, Patel, Krina, Carter, Anastarsia, Lapthorn, Cris, Pullen, Frank
Parametric Analysis of Aero-Derivative Gas Turbine: Effect of Radiative Heat Transfer on Blade Coolant Requirement2017-01-20459/19/2017
Air-film cooled gas turbine is widely used in aero-derivative gas turbines. The present paper reviews previously developed air-film blade cooling models. The article further proposes a new blade cooling model for estimating blade coolant mass fraction which takes into account the effect of radiative heat transfer from hot flue gases to aero-derivative gas turbine blade surface. Various possibilities to achieve enhanced performance from aero-derivative gas turbine have been enumerated namely effect of advanced design philosophies, thermal barrier coatings, advancement in blade material. Also adoption of advanced design philosophies such as 3-D CFD would lead to improved component design. Further use of advanced blade material specifically for gas turbine blade application including single-crystal blade, directionally solidified blade material being nickel-chrome-molybdenum alloys may be explored. Adoption of advanced thermal barrier coating material and latest technique for application
Mishra, Shivam, Y, Sanjay
Aircraft Fuel System Design Using 1D and 3D Methods: An Enabler for Thermal Management2017-01-20399/19/2017
Thermal management on aircraft has been an important discipline for several decades. However, with the recent generations of high performance aircraft, thermal management has evolved more and more into a critical performance and capability constraint on the whole aircraft level. Fuel continues to be the most important heat sink on high performance aircraft, and consequently the requirements on thermal models of fuel systems are expanding. As the scope of modeling and simulation is widened in general, it is not meaningful to introduce a new isolated modeling and simulation capability. Instead, thermal models must be derived from existing model assets and eventually enable integration across several physical domains. This paper describes such an integrated approach based on the Modelica Fuel System Library and the 3DExperience Platform. It combines 1D and 3D methodology and delivers capabilities normally limited to complex and time-consuming CFD computations at the speed and convenience
Sielemann, Michael, Lee, Changsoo, LeBrun, Victor-Marie, Ahn, Chiwoo, Colleoni, Arnaud, Lee, Dongkyu, Lee, JeongSeok, Nguyen, Anh, Proelss, Katrin, Yoon, Hyon Min
Self-Sealing Breakaway Valves for Crash-Resistant Aircraft Fuel and Oil SystemsARP1616B (Current)8/31/2017
This document defines design, performance, and test criteria for self-sealing breakaway valves for use in crash-resistant aircraft fuel systems.
AE-5A Aerospace Fuel, Inerting and Lubrication Sys Committee
Aerospace & Defense Technology: August 201717AERP088/3/2017
The Rapid Rise of Beryllium-Aluminum Alloys in Aerospace Aeroacoustic Simulation Delivers Breakthroughs in Aircraft Noise Reduction Using System Simulation to Manage Increasing Thermal Loads on Aircraft Fuel Systems Ensuring the Compliance of Avionics Software with DO-178C Microwave Photonic Notch Filter Helps Ensure Critical Mission Success Measuring Propellant Stress Relaxation Modulus Using Dynamic Mechanical Analyzer New testing technique requires less material, gives more accurate results. Combustion Characteristics of Hydrocarbon Droplets Induced by Photoignition of Aluminum Nanoparticles Test methodology allows analysis of combustion dynamics for subscale rocket injectors under super critical conditions. Vapor Pressure Data and Analysis for Selected Organophosphorous Compounds: DIBMP, DCMP, IMMP, IMPA, EMPA, and MPFA Determining the thermophysical properties of chemical warfare agent simulants can help evaluate the performance of defensive equipment. Coupling of Coastal Wave
Coupling Assembly, Threadless, Flexible, Fixed Cavity, Self-Bonding, Procurement SpecificationAS1650D (Historical)7/10/2017
This SAE Aerospace Standard (AS) defines the requirements for a threadless, flexible, self-bonding coupling assembly which, when installed on machined fixed cavity ferrules, provides a flexible connection for joining tubing and components in aircraft fuel, vent or other systems. This assembled coupling, hereafter referred to as the assembly, and is designed for use from -65 to +400 °F and at 125 psig nominal operating pressure.
G-3, Aerospace Couplings, Fittings, Hose, Tubing Assemblies
Kilohertz Mie Scattering and OH* Chemiluminescence Imaging of JP-8 Multiple Injections Using a 250 MPa Fuel Injector2017-01-08323/28/2017
The objective of the study was to investigate the spray and combustion characteristics of Jet Propellant-8 (JP-8) using a high-pressure fuel injector which is capable of up to 250-MPa fuel injection pressure. Experiments were performed in a constant-pressure flow-through combustion chamber at the ambient conditions of 825 K and 6 MPa for the oxygen concentration of 0 and 21%. JP-8 was injected over a range of fuel injection pressures from 50 to 250 MPa for single injection events to establish a baseline operation. Pilot and post injections were used to study the effect of multiple injections on spray and combustion of the high-pressure fuel injector. Both pilot and post injection separation times and quantities were systematically varied. JP-8 spray and combustion events were imaged at 75 kHz using a combination of Mie scattering and OH* chemiluminescence imaging. The Mie scattering results showed that spray atomization and mixing was enhanced with increasing fuel injection pressure
Temme, Jacob, Coburn, Vincent, Kweon, Chol-Bum
Fluid, Jet ReferenceAMS2629E (Historical)2/8/2017
This specification covers a mixture of liquid hydrocarbons and soluble additives.
AMS G9 Aerospace Sealing Committee
Alternative Fuels: A Review About Anhydrous and Hydrous Ethanol Properties2016-36-040910/25/2016
Since 70′, ethanol has risen as an alternative and ecological fuel, it has also been pointed as a potential candidate for replacing partial, or even totally, oil derived fuel application on internal combustion engines, supporting automotive industry. Ethanol is obtained from renewable sources and contributes to pollutants emission reduction in the atmosphere. In Brazil, it is obtained from sugarcane, but it can be obtained from others vegetable growing, such as beet or corn, common in other countries. For Brazilian automotive applications two types of ethanol are commonly applied: anhydrous, that contains at most 0.4% water in volume and has been used in gasoline blends up to 27%; and hydrous, with a maximum water content of 4.9% in volume, used as a substitute to gasoline on flex fuels engines. Although the widely application of ethanol, there is still lack of data available in literature regarding the fuel properties. The purpose of this research work is to gather the information
Martins, Fernanda Pinheiro, Lacava, Pedro Teixeira, de Andrade, Claudia Regina, Garzuzi, Sandra
Derived Cetane Number, Distillation and Ignition Delay Properties of Diesel and Jet Fuels Containing Blended Synthetic Paraffinic Mixtures2016-01-907610/24/2016
Aviation turbine fuel and diesel fuel were blended with synthetic paraffins produced via two pathways and the combustion properties measured. Both aviation and diesel fuel containing synthetics produced from the fermentation of sugars, had a linear response to blending with decreasing ignition delay times from 5.05 - 3.52 ms for F-34 and 3.84 - 3.52 ms for F-76. For the same fuels blended with synthetics produced from the fermentation of alcohols, ignition delay times were increased out to 18.66 ms. The derived cetane number of the blends followed an inversely similar trend. Additionally, simulated distillation using ASTM D2887 at high synthetic paraffinic kerosene blend ratios resulted in the recovery temperatures being incorrectly reported. In this case, higher recovery volumes were at lower temperatures than earlier recovery points i.e. T90< T50, for SIP-SPK.
Abanteriba, Sylvester, Yildirim, Ulas, Webster, Renee, Evans, David, Rawson, Paul
Energy Storage for Commercial Hybrid Electric Aircraft2016-01-20149/20/2016
Energy storage options for a hybrid electric commercial single aisle aircraft were investigated. The propulsion system features twin Geared Turbofan™ engines in which each low speed spool is assisted by a 2,500 HP electric motor during takeoff and climb. During cruise, the aircraft is powered solely by the turbine engines which are sized for efficient operation during this mission phase. A survey of state of the art energy storage options was conducted. Battery, super-capacitor, and flywheel metrics were collected from the literature including Specific Energy (Wh/kg), Volumetric Energy Density (Wh/L), Specific Power (W/kg), Cost ($/kWh), and Number of Cycles. Energy storage in fuels was also considered along with various converters sized to produce a targeted quantity of electric power. The fuel and converters include fuel cells (both proton exchange membrane and solid oxide operating on hydrogen or on jet fuel) and a turbogenerator (jet fuel or LNG). The various energy storage options
Rheaume, Jonathan M., Lents, Charles
Ball-On-Cylinder (BOC) Aircraft Turbine Fuel Lubricity TesterAIR1794A (Historical)5/13/2016
This metric SAE Aerospace Information Report (AIR) details a ball-on-cylinder (BOC) test device and specifies a method of rating the relative lubricity of aviation turbine fuel samples. The BOC produces a wear scar on a stationary steel ball by forcing it with a fixed load against a fuel wetted steel test ring in a controlled atmosphere. The test ring is rotated at a fixed speed so its surface is wetted by a momentary exposure to the fluid under test. The size of the wear scar is a measure of the test fluid lubricity and provides a basis for predicting friction or wear problems.
AE-5B Aircraft and Engine Fuel and Lubricant Sys Components
Rings, Sealing, Phosphonitrilic Fluoroelastomer (FZ) Aviation Fuel-Resistant 75 - 85 Shore AAMS7284/2A (Current)5/3/2016
This specification covers phosphonitrilic fluoroelastomer (FZ) in the form of molded rings. Primarily for use in aircraft fuel systems operating from -55 to +150 degrees C (-67 to +302 degrees F).
AMS CE Elastomers Committee
Rings, Sealing, Phosphonitrilic Fluoroelastomer (Fz) Aviation Fuel ResistantAMS7284B (Current)5/3/2016
This specification and its associated detail specifications cover phosphonitrilic fluoroelastomers (FZ) in the form of molded rings.
AMS CE Elastomers Committee
Rings, Sealing, Phosphonitrilic Fluoroelastomer (FZ) Aviation Fuel Resistant 65 - 75 Shore AAMS7284/1A (Current)5/3/2016
This specification covers a phosphonitrilic fluoroelastomer (FZ) in the form of molded rings. Primarily for use in aircraft fuels systems operating from -55 to +150 degrees C (-67 to 302 degrees F).
AMS CE Elastomers Committee
Spray Characterization and Ignition Delay Measurements of JP-8 and IPK in a Constant-Pressure Flow Chamber2016-01-07364/5/2016
This research compares the spray development and combustion characteristics of jet propellant 8 (JP-8) and iso-paraffinic kerosene (IPK) through a range of diesel engine in-cylinder operating conditions. Non-reacting spray experiments were performed in a constant-pressure flow chamber with 99% nitrogen gas composition at constant temperature (900 K) and densities ranging from 11-56 kg/m3. Near-simultaneous, high-speed Mie and schlieren images of the spray were acquired to measure the liquid and vapor penetration lengths of the non-reacting jet. Reacting experiments, consisting of photodiode measurements and intensified high-speed movies of OH* chemiluminescence, were performed at the same thermodynamic conditions as the non-reacting experiments, except with a 21%/79% oxygen/nitrogen ambient gas composition. Measurements of the rate of injection, issued from a single-hole axial common-rail fuel injector, showed negligible differences between the fuels. The non-reacting liquid length of
Tess, Michael, Kurman, Matthew, Kweon, Chol-Bum
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