Aircraft Engine Technology Review - The Pathways for an Efficient, Cleaner and Quieter Aviation Industry

2020 ◽  
Author(s):  
Fábio Coelho Barbosa
Keyword(s):  
Aircraft Engine ◽  
Aviation Industry ◽  
Technology Review

scholarly journals The Design of Technological Instructions for an Assembling the Aircraft Engine

2016 ◽  
Vol 4 (18) ◽  
pp. 14
Author(s):  
Martin Novák ◽  
Petr Daňko ◽  
Martin Lukavský
Keyword(s):  
Aircraft Engine ◽  
Aviation Industry

This article is about a design of new technological instructions for an aviation industry. The goal of the new technological instructions is to replace the old ones. The old instructions are less clear and less suitable for new workers. A change and an upgrade of the new instructions is shown on the technological instructions for disassembling of free turbine´s blades during general overhaul. The free turbine is from the M601 engine. The new instructions should be more efficient and enhanced general overhaul.

Mechanical Testing of Additively Manufactured Superalloy Lugs

2021 ◽  
Author(s):  
Sushovan Roychowdhury ◽  
Henrik Karlsson ◽  
Björn Henriksson ◽  
Pher-Ola Carlson
Keyword(s):  
Structural Integrity ◽  
Low Cycle Fatigue ◽  
Aircraft Engine ◽  
Mechanical Tests ◽  
Aviation Industry ◽  
Length Scales ◽  
Nickel Based Superalloy ◽  
Multiple Length Scales ◽  
Safety Considerations ◽  
Design Calculations

Abstract Additively manufactured parts, in spite of their many advantages, face substantial challenges on the path towards certification. This challenge is more pronounced in the quality-demanding aviation industry, where the safety considerations are paramount. A major reason for this challenge is the lack of history associated with additively built parts compared to the traditional cast and wrought components. In assessing the structural integrity of cast and wrought components, material properties obtained from laboratory coupon tests are routinely applied for design calculations of large components. However, for AM parts, questions remain over transferability of properties over multiple length scales due to possible variations in material chemistry, microstructure, and defect. In this work, this issue is investigated by conducting mechanical tests on small simplified lugs of nickel-based superalloy Haynes 282. The lugs are produced by the laser powder bed fusion process. After appropriate heat treatment and machining operations, the lugs are subjected to strength, low cycle fatigue, and crack propagation tests. Multiple tests are carried out in order to assess repeatability. Design calculations are performed to assess whether the test results can be predicted with standard methods. The results in the current work generate confidence in predictable, repeatable behavior of the AM built lugs. Continuation of this approach over larger length scales has the potential to build enough confidence so that additively manufactured parts can be used in load-bearing structural elements of the aircraft engine.

Assessment and Rehabilitation of Foreign Object Damage Potential on Airfield Shoulder and Blast Pavements

2005 ◽  
Vol 1915 (1) ◽  
pp. 105-111
Author(s):  
Katherine Keegan ◽  
Scott D. Murrell ◽  
Guy Zummo ◽  
Gonzalo Rada
Keyword(s):  
New York ◽  
Flight Control ◽  
Aircraft Engine ◽  
Rehabilitation Program ◽  
Pavement Management ◽  
Aviation Industry ◽  
Foreign Object ◽  
Damage Potential ◽  
Foreign Object Damage ◽  
Pavement Maintenance

Foreign object damage (FOD) is a term used by the aviation industry to describe damage caused by any object that can be ingested by an aircraft engine or flight control mechanism. FOD is estimated to cost the global aerospace industry up to $4 billion annually. Deteriorated pavements are one source of FOD and fall into two categories: runway, taxiway, and apron pavements that aircraft traverse and shoulders and other infield pavements that are not traversed but are subjected to jet blast. Widely recognized procedures for the assessment of pavements traveled on by aircraft are well documented. However, procedures for the assessment of FOD potential for shoulder and blast pavements at commercial airports are not widely recognized. In an effort to manage shoulder and blast pavements proactively and eliminate pavement-related FOD incidents, the Port Authority of New York and New Jersey undertook to assess the current condition of these pavements, rehabilitate and repair areas with unacceptable FOD potential, and initiate periodic inspections on these pavements to facilitate the implementation of an effective pavement maintenance and rehabilitation program. To achieve this goal, a dual project- and network-level inspection approach was implemented. The project-level objective was to identify immediate repairs needed to address unacceptable FOD potential. The network-level objective was to assess the current condition and initiate a proactive inspection regime to assist in maintaining these pavements. The approaches to assessment and rehabilitation are detailed and steps to implement a pavement management system for these pavements are discussed.

scholarly journals A prototype method for diagnosing high ice water content probability using satellite imager data

2018 ◽  
Vol 11 (3) ◽  
pp. 1615-1637 ◽  
Author(s):  
Christopher R. Yost ◽  
Kristopher M. Bedka ◽  
Patrick Minnis ◽  
Louis Nguyen ◽  
J. Walter Strapp ◽  
...  
Keyword(s):  
Water Content ◽  
Deep Convection ◽  
Engine Performance ◽  
Aircraft Engine ◽  
High Mass ◽  
Aviation Industry ◽  
Cloud Optical Depth ◽  
Geo Satellite ◽  
Ice Water Content ◽  
Ice Water

Abstract. Recent studies have found that ingestion of high mass concentrations of ice particles in regions of deep convective storms, with radar reflectivity considered safe for aircraft penetration, can adversely impact aircraft engine performance. Previous aviation industry studies have used the term high ice water content (HIWC) to define such conditions. Three airborne field campaigns were conducted in 2014 and 2015 to better understand how HIWC is distributed in deep convection, both as a function of altitude and proximity to convective updraft regions, and to facilitate development of new methods for detecting HIWC conditions, in addition to many other research and regulatory goals. This paper describes a prototype method for detecting HIWC conditions using geostationary (GEO) satellite imager data coupled with in situ total water content (TWC) observations collected during the flight campaigns. Three satellite-derived parameters were determined to be most useful for determining HIWC probability: (1) the horizontal proximity of the aircraft to the nearest overshooting convective updraft or textured anvil cloud, (2) tropopause-relative infrared brightness temperature, and (3) daytime-only cloud optical depth. Statistical fits between collocated TWC and GEO satellite parameters were used to determine the membership functions for the fuzzy logic derivation of HIWC probability. The products were demonstrated using data from several campaign flights and validated using a subset of the satellite–aircraft collocation database. The daytime HIWC probability was found to agree quite well with TWC time trends and identified extreme TWC events with high probability. Discrimination of HIWC was more challenging at night with IR-only information. The products show the greatest capability for discriminating TWC  ≥  0.5 g m−3. Product validation remains challenging due to vertical TWC uncertainties and the typically coarse spatio-temporal resolution of the GEO data.

Mechanical Testing of Additively Manufactured Superalloy Lugs

2021 ◽  
Author(s):  
Sushovan Roychowdhury ◽  
Hekrik Karlsson ◽  
Björn Henriksson ◽  
Pher-Ola Carlson
Keyword(s):  
Structural Integrity ◽  
Low Cycle Fatigue ◽  
Aircraft Engine ◽  
Mechanical Tests ◽  
Aviation Industry ◽  
Length Scales ◽  
Nickel Based Superalloy ◽  
Multiple Length Scales ◽  
Safety Considerations ◽  
Design Calculations

Abstract Additively manufactured parts, in spite of their many advantages, face substantial challenges on the path towards certification. This challenge is more pronounced in the quality-demanding aviation industry, where the safety considerations are paramount. A major reason for this challenge is the lack of history associated with additively built parts compared to the traditional cast and wrought components. In assessing the structural integrity of cast and wrought components, material properties obtained from laboratory coupon tests are routinely applied for design calculations of large components. However, for AM parts, questions remain over transferability of properties over multiple length scales due to possible variations in material chemistry, microstructure, and defect. In this work, this issue is investigated by conducting mechanical tests on small simplified lugs of nickel-based superalloy Haynes 282. The lugs are produced by the laser powder bed fusion process. After appropriate heat treatment and machining operations, the lugs are subjected to strength, low cycle fatigue, and crack propagation tests. Multiple tests are carried out in order to assess repeatability. Design calculations are performed to assess whether the test results can be predicted with standard methods. The results in the current work generate confidence in predictable, repeatable behavior of the AM built lugs. Continuation of this approach over larger length scales has the potential to build enough confidence so that additively manufactured parts can be used in load-bearing structural elements of the aircraft engine.

Being in Control of Noise Levels Improves the Perception of Airplane Seat Comfort

2021 ◽  
Author(s):  
Joyce Bouwens ◽  
Luisa Fasulo ◽  
Suzanne Hiemstra-van Mastrigt ◽  
Udo W. Schultheis ◽  
Alessandro Naddeo ◽  
...  
Keyword(s):  
Aircraft Engine ◽  
Aviation Industry ◽  
Noisy Environment ◽  
Noise Levels ◽  
Engine Noise ◽  
Acoustic Environment ◽  
Physical Discomfort ◽  
Seat Comfort ◽  
Comfort Perception ◽  
Cabin Interior

Abstract. The aviation industry is constantly making compromises when designing comfortable airplane cabins. Providing passengers with a pleasant acoustic environment without adding weight to the cabin structure is a field of tension that challenges cabin interior designers. The aim of this study was to investigate whether noise levels affect the comfort and physical discomfort experienced by airplane passengers, and whether control influences comfort perception. To this end, 30 participants experienced three conditions (silence, aircraft engine noise at 75 dB, and the same noise with the ability to use earplugs), and comfort and discomfort were measured using a questionnaire. It was concluded that aircraft engine noise negatively affected the airplane passengers’ comfort experiences. Having the ability to control this noisy environment with earplugs resulted in the lowest reported physical discomfort.

Iran's commercial aviation awaits post-sanctions boost

2015 ◽  
Keyword(s):  
Competitive Advantage ◽  
Aircraft Engine ◽  
Growth Potential ◽  
Civil Aviation ◽  
Aviation Industry ◽  
Consumer Market ◽  
Commercial Aviation ◽  
Content Type ◽  
Strategic Location ◽  
Foreign Competitors

Subject The growth potential of Iran's civil aviation industry. Significance President Hassan Rouhani's government announced this week that it is in close negotiations with "major manufacturers" to update and to renovate the Iranian air fleet when a deal on Iran's nuclear programme is reached. Agreement would probably see some degree of sanctions relief for the country's beleaguered commercial aviation sector. With its geographically strategic location and large, growing consumer market, Iran has strong growth potential in this sector. However, after decades under sanctions, the industry is hampered by many barriers and has fallen far behind its regional competitors. Impacts Lifting sanctions on acquiring parts would improve Iranian airlines' safety record. It would also be a boon for US aircraft, engine and parts manufacturers, such as Boeing, General Electric and United Technologies. Availability of new aircraft and parts will expand domestic networks, enabling codesharing deals, including potential equity partnerships. Still, foreign competitors will enjoy a significant competitive advantage as Iranian carriers struggle to modernise.

scholarly journals Further investigation of the repetitive failure in an aircraft engine cylinder head - Mechanical properties of Aluminum alloy 242.0

Mechanika ◽  
2020 ◽  
Vol 26 (4) ◽  
pp. 285-292
Author(s):  
Nikola Vučetić ◽  
Gordana Jovičić ◽  
Branimir Krstić ◽  
Miroslav Živković ◽  
Vladimir Milovanović ◽  
...  
Keyword(s):  
Mechanical Properties ◽  
Aluminum Alloy ◽  
Cylinder Head ◽  
Fatal Outcome ◽  
High Strength ◽  
Experimental Tests ◽  
Aircraft Engine ◽  
Fatigue Properties ◽  
Aviation Industry ◽  
Integrity Assessment

Aluminum alloys are widely used in military and aviation industry due to their properties such as low density and high strength. During the aircraft operation there are mechanical failures of various structural components caused by numerous mechanisms such as corrosion, material defects, high cycle fatigue and the like. One of the frequent mechanical failures on air-cooled piston engines is the cylinder head cracking. This paper is the continuation a comprehensive research of the Lycoming IO-360-B1F aircraft cylinder head failure. The failure of this type has already occurred during flight and about 50 failures like this have been registered from around the world, some of them with a fatal outcome and therefore require detailed research. The paper consists of machining of the tested specimens and their testing at many different locations and in many different laboratories throughout Bosnia and Herzegovina, Serbia and Slovenia. This paper is based on a research that includes the experimental analysis of mechanical properties of Aluminum alloy 242.0 which is a constituent material of the cylinder head of the Lycoming IO-360-B1F aircraft engine on which a crack appeared. Based on chemical, metallographic, static and dynamic experimental tests of the material properties, Aluminum alloy 242.0 static and fatigue properties were obtained, S-N curve was formed and endurance limit was determined. Results of numerical simulations of experiments, confirmed by experimental results, were performed to make numerical procedures reliable due to further research. The results of the research are planned to be implemented in numerical modeling of the cylinder assembly stress-strain state under workload and in further numerical research of Lycoming IO-360-B1F cylinder assembly integrity assessment.

A Numerical Study Into the Effects of Bio-Synthetic Paraffinic Kerosine Blends With Jet-A Fuel for Civil Aircraft Engine

2012 ◽  
Author(s):  
Nurul Musfirah Mazlan ◽  
Mark Savill ◽  
Timos Kipouros ◽  
Yi-Guang Li
Keyword(s):  
Crude Oil ◽  
Numerical Study ◽  
Aircraft Engine ◽  
Aviation Industry ◽  
Engine Emissions ◽  
Alternative Technologies ◽  
Fuel Flow ◽  
Civil Aircraft ◽  
Point Condition ◽  
Fuel Costs

Growing concerns regarding fluctuating fuel costs and pollution targets for gas emissions, have led the aviation industry to seek alternative technologies to reduce its dependency on crude oil, and its net emissions. Recently blends of bio-fuel with kerosine, have become an alternative solution as they offer “greener” aircraft and reduce demand on crude oil. Interestingly, this technique is able to be implemented in current aircraft as it does not require any modification to the engine. Therefore, the present study investigates the effect of blends of bio-synthetic paraffinic kerosine with Jet-A in a civil aircraft engine, focusing on its performance and exhaust emissions. Two bio-fuels are considered: Jatropha Bio-synthetic Paraffinic Kerosine (JSPK) and Camelina Bio-synthetic Paraffinic Kerosine (CSPK); there are evaluated as pure fuels, and as 10% and 50% blend with Jet-A. Results obtained show improvement in thrust, fuel flow and SFC as composition of bio-fuel in the blend increases. At design point condition, results on engine emissions show reduction in NOx, and CO, but increases of CO is observed at fixed fuel condition, as the composition of bio-fuel in the mixture increases.

scholarly journals A New Method of Calculating the Attainable Life and Reliability in Aerospace Bearings

2020 ◽  
Vol 5 (6) ◽  
pp. 745-750
Author(s):  
Peter Gloeckner ◽  
W. Sebald
Keyword(s):  
Gas Turbines ◽  
Aircraft Engine ◽  
Operating Conditions ◽  
New Method ◽  
Aviation Industry ◽  
Flight Safety ◽  
Rolling Element Bearings ◽  
Aircraft Engines ◽  
Increased Risk ◽  
Rolling Element

The aviation industry made significant progress improving reliability, efficiency and performance throughout the last decades. Especially aircraft engines and helicopter transmission systems contributed significantly to these improvements. The kerosene consumption decreased by 70 % and the CO2 emissions due to air transport decreased by 30 % per passenger kilometer within the last 20 years. Simultaneously, the flight safety was increased with aircraft engine in-flight-shut-downs as low as 1 ppm and „unscheduled engine removals” as low as 4 ppm. Flight safety is equal to the reliability of the systems in service. Failure of these systems directly leads to exposure of human life. Among the most critical aviation systems are aircraft engines including the rolling element bearings which support the rotors. A serious damage to the aircraft engine main shaft bearings during flight requires shout-down of the engine to avoid a further damage escalation subsequently leading to engine fire. Today, it is a requirement for aircraft to operate with one engine shut down. However, each in-flight-engine-shut-down typically is connected with flight diversion or abort and immediate landing. Inflight-shut-downs translate into increased risk for passengers and crew and substantial on cost. Therefore, rolling element bearings for aircraft engines are developed – similar to other aircraft engine components – targeting a reliability of nearly 100 % over an operation time of more than 10 000 hours prior to overhaul. To achieve this requirement despite the extreme operating conditions such as high speed and temperatures occurring in gas turbines, special high-performance materials are used for the rolling bearing components which are partially integrated in surrounding engine parts like shafts and housings. These special conditions - deviating from conventional industrial rolling element bearing applications - are currently not sufficiently considered in the standardized method of calculating the bearing life per ISO 281. A new method of calculating the attainable life of rolling elements bearing in aerospace applications is presented. This method considers the special aerospace conditions and materials and thus enables a higher reliability of the theoretical analysis and life prediction.

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