Browse Topic: Gas turbines

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QA Test for CSP-70370530202405/15/2024
QA Test
Airlines Electronic Engineering Committee
test download manager cache issue 12/27/2023 at 9 amSAE-PP-0908512/27/2023
test download manager cache issue 12/27/2023 at 9 am
Mutagaana, Festo
Infrared Signature of Fixed and Variable Area C-D Nozzle of Aircraft Engine01-16-02-001101/02/2023
The use of converging-diverging (C-D) variable area nozzle (VAN) in military aeroengines is now common, as it can give optimal expansion and control over engine back pressure, for a wide range of engine operations. At higher main combustion temperatures (desired for supercruise), an increase in the nozzle expansion ratio is needed for optimum performance. But changes in the nozzle throat and exit areas affect the visibility of engine hot parts as the diverging section of the nozzle is visible for a full range of view angle from the rear aspect. The solid angle subtended by engine hot parts varies with change in visibility, which affects the aircraft infrared (IR) signature from the rear aspect. This study compares the performances of fixed and variable area nozzles (FAN and VAN) in terms of engine thrust and IR signature of the engine exhaust system in the boresight for the same increase in combustion temperature. This study is performed for two cases: (i) variable throat area and
Baranwal, Nidhi, Mahulikar, Shripad P.
Potential Applications of Fuel Cells in Air Mobility2022-26-121605/26/2022
The climate change impact due to increased greenhouse gas emissions like carbon dioxide (CO2), methane, nitrous oxide (NOx) and ozone etc. has been immense over the years and causing increase in temperatures of the earth’s surface and global warming. Recently, there is a significant effort to reduce the emissions especially after Paris agreement in 2015. There are several research initiatives across the globe to reduce the emissions like NOx, CO2 and other harmful substances. The air mobility also contributed to the increased greenhouse gases due to CO2 and NOx. This paper presents the potential applications of fuel cells for air mobility that includes helicopters, hybrid electric aircrafts and all electric aircrafts to achieve the reduced emissions and reduced fuel consumption. The objective of this paper is to take a broad view of how fuel cell technology works, various types of existing technologies and their potential applications and challenges for air mobility vehicles in terms
Kari, Sreedhar, Kumar, Ravi
Tuning of blade natural frequencies outside high excitation region by using Ceramic Particle Reinforced Composite Materials for a typical Gas Turbine Engine Compressor Blade 2022-26-114405/26/2022
Composite materials have time and again proven to be highly useful, especially in the aerospace industry with the increasing need for light-weight materials albeit with high stiffness to strength ratios. The Ceramic Particle Reinforced Composites can be effectively utilized in tuning the natural frequencies of components by varying the volume fractions up to 60% with the help of Representative Unit Cell (RUC) Models. The aim of this paper is to tune the natural frequencies of a typical compressor blade used in a gas turbine engine by modifying the material properties without changing the design profile significantly. The design profiles of blades are arrived at after a lot of engineering iterations from aerodynamics stability point of view and are also finalized based on meeting key performance parameters. However, the structural analysis studies are carried out after the profile generation, which may sometime predict that the natural frequencies are within the high excitation range of
Putrevu, Ravi, Kari, Sreedhar
Design and Simulation of Isolated AC-DC Flyback Conversion System for High Energy Ignition Unit of Gas Turbine Engine2022-26-118705/26/2022
A high energy ignition system is used in the gas turbine engine to provide desired heat energy which ignites the fuel and compressed air passing through the combustion chamber. The high energy output of the ignition system depends on the suitable selection of converter mechanism. Therefore, an AC-DC fly back converter mechanism is used in the exciter unit which supplies high input voltage (3000V) to the gas discharge tube.This converter design provides input and output side electrical isolation and assures the safety of the system. Also, by incorporating this circuit with the ignition coil, the desired output of 3-6 joules and spark rate of 200 to 350 micro seconds can be achieved. This paper discusses the procedures involved in the design and simulation of fly back conversion mechanism for high energy ignition unit.
J, Abarna, Kumari, Poonam, AN, Vishwanatha
Analysis of a Supercharged Gas Turbine Engine Concept and Preliminary Investigation of a Version Using Argon as the Working Fluid2022-01-071503/29/2022
The paper presents results from a study into the potential of a complex cycle gas turbine engine, originally investigated by the Ford Motor Company for truck applications in the 1960s, updated to gauge the possible improvements by raising the efficiencies of its constituent components from the values used in period to modern levels. To perform this investigation, firstly a spreadsheet model was constructed and the available literature data used to validate it. The methodology used in the model was to balance the power consumed by the compressors (and auxiliaries where applicable) with that produced by their driving turbines, and to match the thermal power in the heat exchangers with the data provided. Using the quoted lower heating value of the diesel fuel originally used this approach led to an accuracy of 100% (using three places of decimals in brake specific fuel consumption). Any improvement in the devices would then manifest in an increase in expansion ratio of the power turbine
Turner, James, Togawa, Keita
A Numerical Study on the Effect of a Pre-Chamber Initiated Turbulent Jet on Main Chamber Combustion2022-01-046903/29/2022
To elucidate the complex characteristics of pre-chamber combustion engines, the interaction of the hot gas jets initiated by an active narrow throated pre-chamber with lean premixed CH4/air in a heavy-duty engine was studied computationally. A twelve-hole KAUST proprietary pre-chamber geometry was investigated using CONVERGE software. The KAUST pre-chamber has an upper conical part with the spark plug, and fuel injector, followed by a straight narrow region called the throat and nozzles connecting the chambers. The simulations were run for an entire cycle, starting at the previous cycle's exhaust valve opening (EVO). The SAGE combustion model was used with the chemistry modeled using a reduced methane oxidation mechanism based on GRI Mech 3.0, which was validated against in-house OH chemiluminescence data from the optical engine experiments. Two different piston geometries, a flat piston geometry, and a more realistic bowl piston geometry were studied to understand the influence of jet
Sanal, Sangeeth, Echeverri Marquez, Manuel, Silva, Mickael, Cenker, Emre, Im, Hong G.
Combustion Performance of Methane Fermentation Gas with Hydrogen Addition under Various Ignition Timings2022-32-004301/09/2022
Hydrogen (H2) addition is widely used for natural gas combustion to improve the engine efficiency. However, less attention was paid on the various ignition timings for the maximum brake torque (MBT) and brake thermal efficiency (BTE). In order to check the ignition timing effect, experiments were performed in a spark ignition engine with engine speed fixed on 1500 revolutions per minute (rpm). Firstly, CH4 was only used for combustion with excess air ratio (λ) changing from 0.8 to 1.4. Then, co-combustion of 50 vol% CH4 and 50 vol% CO2 was checked to simulate methane fermentation gas. Finally, H2 was added with volume percentage varying from 5% to 20%. Among these discussions, torque, brake mean effective pressure (BMEP), BTE and cylinder pressure were evaluated. Based on the results, high efficiency can be achieved by advancing the ignition timing with H2 addition at λ=1.4. However, with H2 addition, the ignition timing should be retarded to obtain higher BTE. At the lean-burn
Luo, Hongliang, Jin, Yu, An, Yanzhao, Matsumura, Yukihiko, Ichikawa, Takayuki, Kim, Wookyung, Nakashimada, Yutaka, Nishida, Keiya
O-RING, MOLDED FROM AMS7379 RUBBER FOR USE WITH AS5202 PORTSAS6203A (Current)11/09/2021
A-6C2 Seals Committee
Aircraft Turbine Fuel Contamination History and Endurance Test RequirementsAIR4023C (Current)11/01/2021
This document discusses the history and development of endurance requirements, provides an analysis of test contaminant material and includes a discussion of future requirements.
AE-5B Aircraft and Engine Fuel and Lubricant Sys Components
Rubber: Fluorocarbon Elastomer (FKM) Aircraft Engine Oil, Fuel and Hydraulic Fluid Resistant 70 to 80 Shore Type A Hardness Low Temperature Sealing Tg -47 °F (-43.9 °C) for Elastomeric Seals in Aircraft Engine, Fuel and Hydraulic SystemsAMS7410 (Current)10/06/2021
This specification covers high temperature, compression set, and fluid resistant fluorocarbon (FKM) elastomer in the form of molded rings, compression seals, O-ring cord, and molded-in-place gaskets for aeronautical and aerospace applications.
AMS CE Elastomers Committee
Rubber: Fluorocarbon Elastomer (FKM) Aircraft Engine Oil, Fuel and Hydraulic Fluid Resistant 70 to 80 Shore Type A Hardness Low Temperature Sealing Tg -47 °F (-43.9 °C) for Elastomeric Seals in Aircraft Engine, Fuel and Hydraulic SystemsAMS7410-TEST-REC (Historical)10/06/2021
This specification covers high temperature, compression set, and fluid resistant fluorocarbon (FKM) elastomer in the form of molded rings, compression seals, O-ring cord, and molded-in-place gaskets for aeronautical and aerospace applications.
AMS CE Elastomers Committee
Defining and Measuring Factors Affecting Helicopter Turbine Engine Power AvailableARP1702B (Current)10/01/2021
This SAE Aerospace Recommended Practice (ARP) identifies and defines a method of measuring those factors affecting installed power available for helicopter powerplants. These factors are installation losses, accessory power extraction, and operational effects. Accurate determination of these factors is vital in the calculation of helicopter performance as described in the RFM. It is intended that the methods presented herein prescribe and define each factor as well as an approach to measuring said factor. Only basic installations of turboshaft engines in helicopters are considered. Although the methods described may apply in principle to other configurations that lead to more complex installation losses, such as an inlet particle separator, inlet barrier filter (with or without a bypass system), or infrared suppressor, specialized or individual techniques may be required in these cases for the determination and definition of engine installation losses. Some rotorcraft may use an
S-12 Powered Lift Propulsion Committee
Effect of Ambient and Operating Parameters on the Exergy Performance of a Marine Gas Turbine Engine.2021-01-115209/21/2021
The paper presents the effect of ambient and operating parameters on the performance of Marine Gas turbine integrated with vapor refrigeration inlet air cooling. The rational efficiency of gas turbine and along with summation of exergy destruction in all components with and without inlet air cooling has been analyzed. The variation of total exergy destruction of all components indicates that the destruction of exergy is only marginally effected by inlet air cooling. The sensitivity analysis depicting the effect of variation of compressor pressure ratio (rp,c) turbine inlet temperature (TIT), ambient temperature and ambient relative humidity on Gas turbine rational efficiency and non-dimensional component-wise exergy destruction of inlet air cooled gas turbine has been discussed in detail. At higher values of TIT, higher exergy destruction is observed in (%) in gas turbine but exergy destruction is lower (in percentage terms) at higher values of TIT in case of combustion chamber and
Sahu, Sabyasachi, Thatoi, Dhirendranath, Mohapatra, Alok Kumar
Adapter Interface - Turbine Engine Blade Moment Weighing ScaleARP1134A (Current)09/15/2021
To provide a standard interface adapter flange on any blade classification instrument capable of meeting the sensitivity requirements for the specific class.
EG-1A Balancing Committee
Data Formats and Practices for Life Cycle Cost InformationARP4294A (Current)09/10/2021
This SAE Aerospace Recommended Practice (ARP)4294 is directed at life cycle cost (LCC) analysis of aerospace propulsion systems and supplements AIR1939. Specific topics addressed by ARP4294 are listed below: a Propulsion system LCC element structure. b Information exchange and relationships with: (1) Aircraft manufacturer (2) Equipment suppliers (3) Customer c The relationship of the LCC element structure to work breakdown structures. d The relationship between LCC analysis and other related disciplines (e.g., technical (performance analysis, weight control, component lives), reliability, availability and maintainability (RAM), integrated logistic support (ILS), production and finance). e Classification of the accuracy and applicability of LCC assessments.
LCLS Life Cycle Logistics Supportability
Aircraft Engine Life Cycle Cost GuideAIR1939A (Current)09/10/2021
AIR 1939 addresses communication of LCC data between equipment suppliers, aircraft engine producers, aircraft manufacturers, and users, as illustrated in Figure 1. The LCC data categories addressed include: research, development, test and evaluation (RDT&E); acquisition (initial procurement and investment); and operating and support (O&S) costs. While input and output formats are suggested, calculation procedures and cost methodology are specifically excluded since many LCC models preferred by the industry are company sensitive or proprietary (Figure 1). The relationship of LCC input data to program phase is described. Ground rules and assumptions are addressed. A glossary of LCC terms is provided. The LCC impact of propulsion systems on other aircraft systems is considered. This document was specifically developed for military propulsion system cost analysis. However, it is believed that a functional relationship exists between military and commercial Life Cycle Cost analysis and that
LCLS Life Cycle Logistics Supportability
Data Formats and Practices for Life Cycle Cost InformationARP4294A-TEST-REC (Historical)09/10/2021
This SAE Aerospace Recommended Practice (ARP)4294 is directed at life cycle cost (LCC) analysis of aerospace propulsion systems and supplements AIR1939. Specific topics addressed by ARP4294 are listed below: a Propulsion system LCC element structure. b Information exchange and relationships with: (1) Aircraft manufacturer (2) Equipment suppliers (3) Customer c The relationship of the LCC element structure to work breakdown structures. d The relationship between LCC analysis and other related disciplines (e.g., technical (performance analysis, weight control, component lives), reliability, availability and maintainability (RAM), integrated logistic support (ILS), production and finance). e Classification of the accuracy and applicability of LCC assessments.
LCLS Life Cycle Logistics Supportability
Measuring Aircraft Gas Turbine Engine Fine Fuel Filter Element PerformanceARP1827D-TEST-REC (Historical)07/23/2021
This SAE Aerospace Recommended Practice (ARP) delineates two complementary filter element performance parameters: (1) dirt capacity, and (2) filtration efficiency, and corresponding test procedures. It is intended for non-cleanable (disposable), fine fuel filter elements, rated at 25 µm(c) or finer, used in aviation gas turbine engine fuel systems.
AE-5B Aircraft and Engine Fuel and Lubricant Sys Components
Measuring Aircraft Gas Turbine Engine Fine Fuel Filter Element PerformanceARP1827D (Current)07/23/2021
This SAE Aerospace Recommended Practice (ARP) delineates two complementary filter element performance parameters: (1) dirt capacity, and (2) filtration efficiency, and corresponding test procedures. It is intended for non-cleanable (disposable), fine fuel filter elements, rated at 25 µm(c) or finer, used in aviation gas turbine engine fuel systems.
AE-5B Aircraft and Engine Fuel and Lubricant Sys Components
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
Gas Turbine Engine Performance Presentation for Computer Programs Using FortranAS4191A (Current)05/13/2021
This SAE Aerospace Standard (AS) provides a method for gas turbine engine performance computer programs to be written using Fortran COMMON blocks. If a “function-call application program interface” (API) is to be used, then ARP4868 and ARP5571 are recommended as alternatives to that described in this document. When it is agreed between the program user and supplier that a particular program shall be supplied in Fortran, this document shall be used in conjunction with AS681 for steady-state and transient programs. This document also describes how to take advantage of the Fortran CHARACTER storage to extend the information interface between the calling program and the engine subroutine.
S-15 Gas Turbine Perf Simulation Nomenclature and Interfaces
Use of Health Monitoring Systems to Detect Aircraft Exposure to Volcanic EventsAIR6212 (Current)05/13/2021
This document collates the ways and means that existing sensors can identify the platform’s exposure to volcanic ash. The capabilities include real-time detection and estimation, and post flight determinations of exposure and intensity. The document includes results of initiatives with the Federal Aviation Administration (FAA), the European Aviation Safety Agency (EASA), the International Civil Aviation Organization (ICAO), Transport Canada, various research organizations, Industry and other subject matter experts. The document illustrates the ways that an aircraft can use existing sensors to act as health monitoring tools so as to assess the operational and maintenance effects related to volcanic ash incidents and possibly help determine what remedial action to take after encountering a volcanic ash (VA) event. Finally, the document provides insight into emerging technologies and capabilities that have been specifically pursued to detect volcanic ash encounters but are not yet a part
HM-1 Integrated Vehicle Health Management Committee
Liquid Filter Ratings, Parameters and TestsAIR887C (Current)04/29/2021
This SAE Aerospace Information Report (AIR) identifies and explains the meaning of various ratings and terms used to describe the physical characteristics of liquid filter elements. The significance of various filter parameters is discussed. In addition, a number of filter test methods are briefly described. This AIR and the data presented are only applicable where the system liquid wets the filter elements.
A-6C1 Contamination and Filtration Committee
EVALUATION OF HELICOPTER TURBINE ENGINE LINEAR VIBRATION ENVIRONMENTAIR1289A (Current)03/11/2021
This SAE Aerospace Information Report (AIR) outlines a recommended procedure for evaluation of the vibration environment to which the gas turbine engine powerplant is subjected in the helicopter installation. This analysis of engine vibration is normally demonstrated on a one-time basis upon initial certification, or after a major modification, of an engine/helicopter configuration. This AIR deals with linear vibration as measured on the basic case structure of the engine and not, for example, torsional vibration in drive shafting or vibration of a component within the engine such as a compressor or turbine airfoil. In summary, this AIR discusses the engine manufacturer’s "Installation Test Code" aspects of engine vibration and proposes an appropriate measurement method.
S-12 Powered Lift Propulsion Committee
ENGINE EXHAUST SYSTEM DESIGN CONSIDERATIONS FOR ROTORCRAFTARP4056 (Current)03/11/2021
Turbine engines installed in rotorcraft have an exhaust system that is designed and produced by the aircraft manufacturer. The primary function of the exhaust system is to direct hot exhaust gases away from the airframe. The exhaust system may consist of a tailpipe, which is attached to the engine, and an exhaust fairing, which is part of the rotorcraft. The engine manufacturer specifies a baseline "referee" tailpipe design, and guaranteed engine performance is based upon the use of the referee tailpipe and tailpipe exit diameter. The configuration used on the rotocraft may differ from the referee tailpipe, but it is intended to minimize additional losses attributed to the installation. This Aerospace Recommended Practice (ARP) describes the physical, functional, and performance interfaces to be considered in the design of the aircraft exhaust system.
S-12 Powered Lift Propulsion Committee
Helicopter Engine-Rotor System CompatibilityARP704A (Current)03/10/2021
This SAE Aerospace Recommended Practice (ARP) recommends a methodology to be used for the design, analysis and test evaluation of modern helicopter gas turbine propulsion system stability and transient response characteristics. This methodology utilizes the computational power of modern digital computers to more thoroughly analyze, simulate and bench-test the helicopter engine/rotor system speed control loop over the flight envelope. This up-front work results in significantly less effort expended during flight test and delivers a more effective system into service. The methodology presented herein is recommended for modern digital electronic propulsion control systems and also for traditional analog and hydromechanical systems.
S-12 Powered Lift Propulsion Committee
Thermodynamic Analysis of Aeroderivative Gas Turbine Engine Featuring Ceramic Matrix Composite Rotating Blades2021-01-003303/02/2021
The quest for achieving more efficient gas turbine engine systems (GTESs) has led the researchers to try getting into many new dimensions of research. Simple Brayton cycle-based GTESs were coupled with recuperators, regenerators and reheaters to avoid/recoup heat energy from being wasted and these were designated as complex GTESs. Multistage compression (multi-casing) in axial compressors and multistage (two-cylinder) expansions in turbines paved the path to optimize the plant design for greater thrust to weight ratio and greater efficiency of the GTESs. Since the increase in efficiency of any power plant is directly or indirectly related to temperatures at which the plant cycle is being operated, this thermodynamic constraint had led to the development of high temperature materials such as single crystal nickel-based superalloys. To further achieve the increment in operating temperature, different blade cooling techniques were adopted and thermal barrier coatings were applied on
Rathore, Souvik Singh, Kar, Vishesh, S, Sanjay, Mishra, Shivam
Augmentation of Gas-Turbine Performance Using Inlet Air Cooling and Turbine Blade Cooling: A Thermodynamic Approach2021-01-003103/02/2021
A systematic and comprehensive first law analysis of a cooled gas turbine cycle subjected to vapor compressor inlet air cooling (VC-IAC) has been conducted in our study. Film air cooling technique has been implemented to cool the gas turbine (GT) buckets. The gas turbine is subjected to variation of various operating and ambient parameters and the corresponding effect is analyzed to find out the optimal one. The integration of VC-IAC has been reported to further enhance the plant specific work and plant efficiency of gas turbine cycle, the enhancement being higher in regions having a hot and dry climate. This increase in cycle performance due to VC-IAC has been found superior in case of bucket cooled GT cycle when compared to uncooled one. It has further been witnessed that the plant specific work increases by more than 0.35 % and the plant efficiency increases by little above 0.1 % for every 1o C drop in CIT. The work ratio representing the excess of work of turbine over work of
Mishra, Alok, Srivastava, Anshuka, Mohapatra, Alok Kumar
Thermodynamic and Emission Performance Analysis of CMC Bladed Gas Turbine2021-01-003003/02/2021
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
Design Considerations for Enclosed Turbofan/Turbojet Engine Test CellsAIR4869B (Current)02/01/2021
This SAE Aerospace Information Report (AIR) has been written for individuals associated with the ground-level testing of large and small gas turbine engines and particularly for those who might be interested in upgrading their existing or acquiring new test cell facilities.
EG-1E Gas Turbine Test Facilities and Equipment
An Assessment of Planar WavesAIR5866A (Current)02/01/2021
“An Assessment of Planar Waves” provides background on some of the history of planar waves, which are time-dependent variations of inlet recovery, as well as establishing a hierarchy for categorizing various types of planar waves. It further identifies approaches for establishing compression-component and engine sensitivities to planar waves, and methods for accounting for the destabilizing effects of planar waves. This document contains an extensive list and categorization (see Appendix A) of references to aid both the newcomer and the practitioner on this subject. The committee acknowledges that this document addresses only the impact of planar waves on compression-component stability and does not address the impact of planar waves on augmenter rumble, engine structural issues, and/or pilot discomfort.
S-16 Turbine Engine Inlet Flow Distortion Committee
Guidelines for Characterization of Gas Turbine Engine Total-Pressure, Planar-Wave, and Total-Temperature Inlet-Flow DistortionARP6420 (Historical)01/14/2021
The turbine-engine-inlet flow distortion descriptors summarized in this document apply to the effects of inlet total-pressure, planar-wave, and total-temperature distortions. Guidelines on stability margin, destabilizing influences, types and purposes of inlet data, AIP definition, and data acquisition and handling are summarized from AIR5866, AIR5867, ARP1420, and AIR1419. The degree to which these recommendations are applied to a specific program should be consistent with the complexity of the inlet/engine integration. Total-pressure distortion is often the predominant destabilizing element that is encountered and is often the only type of distortion to be considered, i.e, not all types of distortion need to be considered for all vehicles.
S-16 Turbine Engine Inlet Flow Distortion Committee
Measurement of Far Field Noise from Gas Turbine Engines During Static OperationARP1846B (Current)12/21/2020
Recommendations presented in this document are intended primarily for the acquisition of far-field noise data. The test engine is to be appropriately configured and operated so that the sound pressure levels obtained are consistent with the specific objectives of the test. The principal output of the data reduction system is one-third octave band sound pressure levels. However, when appropriate, data may be recorded for purposes of broader or narrower bandwidth analysis.
A-21 Aircraft Noise Measurement Aviation Emission Modeling
Aerospace Auxiliary Power SourcesAIR744D (Current)11/19/2020
This SAE Aerospace Information Report (AIR) is a review of the general characteristics of power sources that may be used to provide secondary, auxiliary, or emergency power for use in aircraft, space vehicles, missiles, remotely piloted vehicles, air cushion vehicles, surface effect ships, or other vehicles in which aerospace technology is used. The information contained herein is intended for use in the selection of the power source most appropriate to the needs of a particular vehicle or system. The information may also be used in the preparation of a power source specification. Considerations for use in making a trade study and an evaluation of the several power sources are included. More detailed information relating to specific power sources is available in other SAE Aerospace Information Reports or in Aerospace Recommended Practices.
A-6C4 Power Sources Committee
Aerospace Auxiliary Power SourcesAIR744D-TEST-REC (Historical)11/19/2020
This SAE Aerospace Information Report (AIR) is a review of the general characteristics of power sources that may be used to provide secondary, auxiliary, or emergency power for use in aircraft, space vehicles, missiles, remotely piloted vehicles, air cushion vehicles, surface effect ships, or other vehicles in which aerospace technology is used. The information contained herein is intended for use in the selection of the power source most appropriate to the needs of a particular vehicle or system. The information may also be used in the preparation of a power source specification. Considerations for use in making a trade study and an evaluation of the several power sources are included. More detailed information relating to specific power sources is available in other SAE Aerospace Information Reports or in Aerospace Recommended Practices.
A-6C4 Power Sources 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
Design Considerations for Enclosed Turbofan/Turbojet Engine Test CellsAIR4869A (Historical)10/22/2020
This SAE Aerospace Information Report (AIR) has been written for individuals associated with the ground-level testing of large and small gas turbine engines and particularly for those who might be interested in upgrading their existing or acquiring new test cell facilities.
EG-1E Gas Turbine Test Facilities and Equipment
Turbine Flowmeter Fuel Flow CalculationsARP4990B (Current)10/22/2020
This SAE Aerospace Recommended Practice (ARP) provides to the aerospace industry a procedure for the consistent and accurate calculation of fuel flow using turbine flowmeters during development, production, and post overhaul/repair gas turbine engine testing.
EG-1E Gas Turbine Test Facilities and Equipment
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
Configuration Control for Maintaining Correlation of Gas Turbine Engine Test CellsARP6028A (Current)10/21/2020
The FAA has issued Advisory Circular, AC43-207, that recommends re-correlation, trending or period checks. The FAA, AC43-207 bases their recommendation on ARP741. This paper describes a recommended practice and procedure for the configuration control requirements to maintain test cell correlation status. This is necessary to maintain performance measurement integrity, particularly when correlation approval is achieved by statistical trending. The configuration of a test facility that exists at the time when a correlation is being carried out should be "base lined" as a condition of correlation approval acceptance, and, be maintained during the time period that the respective correlation approval lasts. This defines test facility configuration control. This is due to the fact that a change in configuration may have the potential to change the established correlation factors and measured engine performance. If such a change occurs then this should be judged by the respective OEMs or
EG-1E Gas Turbine Test Facilities and Equipment
Prognostics for Aerospace Propulsion SystemsAIR5871A (Current)10/14/2020
This document applies to prognostics of aerospace propulsion systems. Its purpose is to define the meaning of prognostics in this context, explain their potential and limitations, and to provide guidelines for potential approaches for use in existing condition monitoring environments. This document also includes some examples. The current revision does not provide specific guidance on validation and verification, nor does it address implementation aspects such as computational capability or certification.
E-32 Aerospace Propulsion Systems Health Management
Procedure for Measurement of Gaseous Emissions from Aircraft Gas Turbine Engines Using Fourier Transform Infrared AnalysisAIR5917-TEST-REC (Historical)10/09/2020
This Aerospace Information Report (AIR) describes the use of FTIR analyzers for measurements of gaseous emissions from aircraft gas turbine engines and combustion rigs. The use of FTIR analyzers can be demonstrated as a suitable and cost-effective equivalent to NDIR and chemiluminescence analyzers as prescribed in ARP1256 for the measurement of CO, CO2, NO, and NO2, where NOx is closely approximated by the sum of NO and NO2 concentrations. FTIR analyzers may be proven suitable for equivalency of analyzers used in current emission testing. Additionally, FTIR analyzers have potential for equivalent measurements of “total” hydrocarbon (THC) as currently defined in ARP1256.
E-31G Gaseous Committee
Procedure for Measurement of Gaseous Emissions from Aircraft Gas Turbine Engines Using Fourier Transform Infrared AnalysisAIR5917 (Current)10/09/2020
This Aerospace Information Report (AIR) describes the use of FTIR analyzers for measurements of gaseous emissions from aircraft gas turbine engines and combustion rigs. The use of FTIR analyzers can be demonstrated as a suitable and cost-effective equivalent to NDIR and chemiluminescence analyzers as prescribed in ARP1256 for the measurement of CO, CO2, NO, and NO2, where NOx is closely approximated by the sum of NO and NO2 concentrations. FTIR analyzers may be proven suitable for equivalency of analyzers used in current emission testing. Additionally, FTIR analyzers have potential for equivalent measurements of “total” hydrocarbon (THC) as currently defined in ARP1256.
E-31G Gaseous Committee
Acceptance Test Procedures and Standards to Ensure Clean Fuel System ComponentsARP1953B (Current)10/01/2020
To describe general guidelines for achieving selected levels of cleanliness in gas turbine engine fuel system components and to describe laboratory methods for measuring and reporting the contamination level of the wetted portion of fuel system components. As in SAE J1227 (covering hydraulic components) this practice includes guidelines for levels of acceptance but does not attempt to set those levels.
AE-5A Aerospace Fuel, Inerting and Lubrication Sys Committee
Augmentation of Energy, Exergy and Emission Performance of Gas Turbine Engines Used for Ship Propulsion2020-01-202809/15/2020
Majority of prime movers for ship propulsion used currently are diesel engines mainly because of their elevated efficiency and their ability to run on residual oil. But in view of the increasing awareness for pollution control and stricter environmental regulations, gas turbine cycle can be regarded as a suitable alternative to propel large ships for cargo and military purpose. However during summer and in hot and humid climates, an increase in ambient temperature and ambient relative humidity is observed to adversely affect the performance of gas turbine (GT). In such circumstances, integration of inlet air cooling to GT cycle can be considered as a suitable alternative. The present paper discusses the possibility of using a vapor absorption inlet air cooled gas turbine cycle as a prime mover for marine application. A parametric study of the effect of compressor pressure ratio, turbine inlet temperature, ambient relative humidity and ambient temperature on energy, exergy and exhaust
Mohapatra, Alok Kumar, Panigrahi, Nabnit, Das, Amar Kumar
Balancing Machines - Verification Test RequirementsAS8617-TEST-REC (Historical)08/25/2020
This document specifies instructions to verify proper calibration of all balancing machines used for processing gas turbine rotors. Detailed test procedures and test log samples are provided to evaluate the condition of the machine under test. These performance and test requirements may be used for new installations, periodic surveillance, or following repairs that may have affected machine performance. Calibration of the balancing machine is an activity done prior to verification testing and is outside the scope of this document. Troubleshooting of difficulties during the verification tests is also outside the scope of this document; this document is purely an instructive procedure.
EG-1A Balancing Committee
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