scholarly journals Investigation of accidents caused by the failure of the main engines of the ekranoplan

2020 ◽  
Author(s):  
В.Ю. Каминский ◽  
Д.А. Скороходов ◽  
А.А. Таранцев ◽  
М.Л. Маринов
Keyword(s):  
Time Characteristic ◽  
Stabilization System ◽  
Engine Thrust ◽  
Flight Height ◽  
Engine Failure ◽  
Engine Maintenance

В статье выполнен анализ лётных характеристик экраноплана с включенной системой стабилизации скорости. Рассмотрен сценарий, в котором после отказа двигателя пилот подключает ранее не работавший двигатель, находившийся в режиме авторотации. Учитывается отказ одного двигателя, поскольку вероятность одновременного отказа двух и большего числа двигателей мала. Рассмотрены различные режимы движения экраноплана по высоте полёта и числу работающих двигателей. Делается допущение, что при отказе двигателя сброс тяги происходит мгновенно. Набор тяги двигателем после подключения осуществляется в соответствии с инструкцией по обслуживанию двигателя. Принята временная характеристика запуска двигателя, находившегося ранее в режиме авторотации, аналогичная действиям пилотов экраноплана, движущегося со скоростью 400 км/час.После прогрева запускаемого двигателя он подключается к системе автоматической стабилизации скорости и выходит на требуемый тяговый режим. Считается, что подключение двигателя к системе автоматической стабилизации скорости и выход на требуемую тягу происходят мгновенно. The article analyzes the flight characteristics of an ekranoplane with a speed stabilization system enabled. We consider a scenario in which, after an engine failure, the pilot connects a previously inactive engine that was in autorotation mode. One engine failure is taken into account, since the probability of simultaneous failure of two or more engines is small. Various modes of movement of the ekranoplan by flight height and number of working engines are considered. It is assumed that when the engine fails, the thrust is reset instantly. After connecting the engine, the engine thrust is set in accordance with the engine maintenance instructions. The time characteristic of starting the engine, which was previously in autorotation mode, is similar to the actions of the pilots of the ekranoplan, whose speed is 400 km / h.After warming up the starting engine, it is connected to the automatic speed stabilization system and enters the required traction mode. It is assumed that the engine is connected to the automatic speed stabilization system and reaches the required thrust instantly.

Development and Validation of an On-Wing Engine Thrust Measurement System

2017 ◽  
Author(s):  
Marc Bauer ◽  
Jens Friedrichs ◽  
Detlev Wulff ◽  
Christian Werner-Spatz
Keyword(s):  
Measurement System ◽  
Standard Procedure ◽  
Flight Test ◽  
Engine Thrust ◽  
Thrust Measurement ◽  
Ground Test ◽  
Engine Maintenance ◽  
The Cost ◽  
Development And Validation ◽  
Engine Condition

Maintenance on aircraft engines is usually performed on an on-condition basis. Monitoring the engine condition during operation is an important prerequisite to provide efficient maintenance. Engine Condition Monitoring (ECM) has thus become a standard procedure during operation. One of the most important parameters, the engine thrust, is not directly measured, however, and can therefore not be monitored, which makes it difficult to distinguish whether deteriorating trends e.g. in fuel comsumption must be attributed to the engine (e.g. due to thermodynamic wear) or to the aircraft (e.g. due to increased drag). Being able to make this distinction would improve troubleshooting and maintenance planning and thus help to reduce the cost of ownership of an aircraft. As part of the research project APOSEM (Advanced Prediction of Severity effects on Engine Maintenance), Lufthansa Technik (LHT) and the Institute of Jet Propulsion and Turbomachinery of Technische Universität Braunschweig develop a method for direct measurement of engine thrust during the operation. In this paper, the design process of the On-Wing (OW) Measurement System is presented, including the validation in labratory tests, the mechanical and thermal calibration as well as the final ground test during an engine test run at LHT test cell and the work on the flight test certification.

Measurement Quality Assessment of an On-Wing Engine Thrust Measurement System

2018 ◽  
Author(s):  
Marc Bauer ◽  
Jens Friedrichs ◽  
Detlev Wulff ◽  
Christian Werner-Spatz
Keyword(s):  
Quality Assessment ◽  
Standard Procedure ◽  
Aircraft Engine ◽  
Flight Test ◽  
Engine Operation ◽  
Engine Thrust ◽  
Thrust Measurement ◽  
Engine Maintenance ◽  
The Cost ◽  
Engine Condition

Aircraft engine maintenance is performed on an on-condition basis. Monitoring the engine condition during operation is important to provide an efficient maintenance. Engine Condition Monitoring has thus become a standard procedure during operation. However, one of the most important parameters, the engine thrust, is not directly measured and can therefore not be monitored, which makes it difficult to distinguish whether deteriorating trends e.g. in fuel comsumption must be attributed to the engine (e.g. due to thermodynamic wear) or to the aircraft (e.g. due to increased drag). Being able to make this distinction would improve troubleshooting and maintenance planning and thus help to reduce the cost of ownership of an aircraft. This paper describes the development and quality assessment of a system for direct engine thrust measurement during the normal engine operation. The system was designed, calibrated and validated with engine test runs. After the necessary certification of the whole system a flight test campaign to validate the system, when installed on an aircraft, was started. In the presented work an assessment of the quality of measured data from the first period of the ongoing flight test is presented.

scholarly journals Perancangan Jadwal Perawatan Mesin Menggunakan Pendekatan Reliability Centered Maintenance (RCM) pada PT. XYZ

2018 ◽  
Vol 1 (2) ◽  
pp. 211-216
Author(s):  
Nurhayati Sembiring ◽  
Gita Ade Elvira
Keyword(s):  
Palm Kernel ◽  
Working Hours ◽  
Screw Press ◽  
Double Cone ◽  
Maintenance Schedule ◽  
Reliability Centered Maintenance ◽  
Engine Failure ◽  
Critical Components ◽  
Engine Maintenance ◽  
Engine Components

PT. XYZ adalah suatu perusahaan yang bergerak dalam bidang usaha perkebunan dan pengolahan hasil perkebunan.Produk utamanya adalah Minyak Sawit (CPO) dan Inti Sawit (Kernel). Apabila terjadi kerusakan mesin pada saat jam kerja mesin, maka proses produksi tidak berjalan. Untuk itu diperlukan sistem perawatan yang terjadwal. Tujuan dari penelitian ini adalah mengidentifikasi sumber utama kerusakan mesin, menganalisis kerusakan komponen kritis mesin dengan metode Reliability Centered Maintenance dan membuat jadwal perawatan mesin yang terencana. Komponen kritis pada mesin Screw Press yang dianalisaadalah Gearbox, Hydraulic Double Cone dan Van Belt. Hasil penelitian menunjukan selang waktu penggantian komponen Gearbox adalah 94 hari, komponen Hydraulic Double Cone adalah 105 hari dan komponen Van Belt adalah 116 hari.   PT. XYZ is a company engaged in the business of plantation and processing of plantation products. Its main products are crude palm oil (CPO) and palm kernel (kernel). If an engine failure occured during engine working hours, the production process does not work. For this reason, a scheduled maintenance system is needed. The purpose of this study is to identify the main source of engine failure, analyze the failure of critical engine components by using the Reliability Centered Maintenance method and making an engine maintenance schedule. The critical components on Screw Press engine which was analyzed were Gearbox, Hydraulic Double Cone and Van Belt. The results showed the replacement interval for Gearbox component was 94 days, Hydraulic Double Cone component was 105 days, and Van Belt component was 116 days.

scholarly journals To the question of the need to out of operation the ship and the loss of ship owners finances as a result of the main high-speed engine failure

2020 ◽  
pp. 28-33
Author(s):  
В.В. Герасиди ◽  
А.В. Лисаченко ◽  
Б.П. Башуров
Keyword(s):  
High Speed ◽  
Operating Time ◽  
Electrochemical Corrosion ◽  
Air Cooling ◽  
Combustion Chambers ◽  
High Speed Engine ◽  
Periodic Monitoring ◽  
Engine Failure ◽  
Engine Maintenance ◽  
Operating Instructions

В работе выполнен анализ примера неисправности ВОД фирмы Caterpillar С32, установленного в качестве одного из главных двигателей судов вспомогательного флота. Наработка двигателя составляет 6 500 часов. Выявлена неисправность охладителя наддувочного воздуха, вследствие чего судно было выведено из эксплуатации. Для подтверждения полученных результатов о текущем состоянии двигателей, принято решение о выполнении частичной разборкидвигателя для проведения его дефектации. Результат дефектации двигателя показывает, что при позднем обнаружении протечки забортной воды, начала прогрессировать коррозия на деталях ЦПГ, куда попала вода. Анализ инструкции по эксплуатациипоказал, что должен выполняться периодический контроль состояния ОНВ. Анализ конструкции и системы охлаждения показал, что на таких типах двигателей устанавливаются два варианта системы охлаждения воздуха: забортной водой и антифризом. Причиной, рассмотренной неисправности двигателя, являлось не соблюдение рекомендаций завода-изготовителя по техническому обслуживанию двигателя. Что повлекло к нарушению плотности сердцевины ОНВ в результате возникновения электрохимической коррозии. А также отсутствие внимания обслуживающего персонала к дренажному клапану, увеличило время прохода забортной воды по системе впуска наддувочного воздуха в камеры сгорания цилиндров. В результате такой неисправности судовладелец понес большие потери, связанные с ремонтном двигателя и простоем судна. The paper analyzes an example of a caterpillar C32 failure, installed as one of the main engines of fleet vessels. The operating time of the engine is 6 500 hours. The after cooler failure was detected; as a result the vessel was taken out of operation. The results obtained confirm about the current state of the engines, it was decided to perform a partial disassembly of the engine to defecation. The result of engine defects shows that when a late detection of seawater leaks, corrosion began to progress on the parts of the engine. The operating instructions analysis showed that periodic monitoring of the after cooler should be performed. The engine design analysis showed that there two types of air cooling systemengine: seawater and antifreeze. The reason for the engine failurewas non-compliance with the recommendations for engine maintenance. The caused the disruption of the aftercooler core density as a result of electrochemical corrosion. As well as the lack of drain valve attention of service personnel, increased the time of seawater passage through the charge air intake system of cylinders combustion chambers. As a result of this failure, the ship owner has suffered heavy damage related to engine repairs and downtime of the vessel.

An Alternative Method for Identifying a Failed Engine in Twin-Engine Propeller Aircraft

2020 ◽  
Vol 10 (2) ◽  
pp. 103-111
Author(s):  
Andrey K. Babin ◽  
Andrew R. Dattel ◽  
Margaret F. Klemm
Keyword(s):  
Human Error ◽  
Flight Simulator ◽  
Traditional Group ◽  
Aircraft Accidents ◽  
Alternative Method ◽  
Indicator Group ◽  
Group A ◽  
The Dead ◽  
Engine Failure ◽  
And Performance

Abstract. Twin-engine propeller aircraft accidents occur due to mechanical reasons as well as human error, such as misidentifying a failed engine. This paper proposes a visual indicator as an alternative method to the dead leg–dead engine procedure to identify a failed engine. In total, 50 pilots without a multi-engine rating were randomly assigned to a traditional (dead leg–dead engine) or an alternative (visual indicator) group. Participants performed three takeoffs in a flight simulator with a simulated engine failure after rotation. Participants in the alternative group identified the failed engine faster than the traditional group. A visual indicator may improve pilot accuracy and performance during engine-out emergencies and is recommended as a possible alternative for twin-engine propeller aircraft.

Advanced stabilization system algorithms of launch vehicle's first stage with attack and sliding angles control

2009 ◽  
Vol 15 (4) ◽  
pp. 72-78
Author(s):  
A.N. Kalnoguz ◽  
◽  
V.M. Tykhovskiy ◽  
V.A. Bataev ◽  
V.N. Pilguy ◽  
...  
Keyword(s):  
Stabilization System

Assessing the Impact of the Inlet Total Pressure Distortion on the Turbofan Thrust

2018 ◽  
pp. 19-30
Author(s):  
Yu. A. Ezrokhi ◽  
E. A. Khoreva
Keyword(s):  
Total Pressure ◽  
External Compression ◽  
Average Value ◽  
Inlet Distortion ◽  
Air Inlet ◽  
Engine Thrust ◽  
Relative Value ◽  
Main Effect ◽  
Pressure Recovery Factor ◽  
The Impact

The paper considers techniques to develop a mathematical model using a method of «parallel compressors». The model is intended to estimate the impact of the air inlet distortion on the primary parameters of the aero-engine.  The paper presents rated estimation results in the context of twin spool turbofan design for two typical cruiser modes of flight of the supersonic passenger jet. In estimation the base values σbase and the average values of the inlet ram recovery σave remained invariable. Thus, parametrical calculations were performed for each chosen relative value of the area of low-pressure region.The paper shows that an impact degree of the inlet distortion on the engine thrust for two modes under consideration is essentially different. In other words, if in the subsonic mode the impact assessment can be confined only to taking into account the influence of decreasing average values of the inlet total pressure, the use of such an assumption in the supersonic cruiser mode may result in considerable errors.With invariable values of the pressure recovery factor at the engine intake, which correspond to the speed of flight for a typical air inlet of external compression σbase, and average value σave, a parameter Δσuneven  has the main effect on the engine thrust, and degree of this effect essentially depends on a difference between σave and σbase values.

Study on the Correlations between the Flight Height and the Two-Legged and One-Legged Take-Off Power in the "Division A" Female Volleyball Players

2010 ◽  
Vol 19 (3-4) ◽  
Author(s):  
Gloria Raţă ◽  
Florin Grapă ◽  
Bogdan Raţă ◽  
Lăcrămioara Manole ◽  
Dana Ciocan
Keyword(s):  
Flight Height ◽  
Volleyball Players

Failure Investigation of an Airline Engine Failure During Take Off

2013 ◽  
Vol 50 (12) ◽  
pp. 821-830
Author(s):  
K. Andersson ◽  
R. Pederson ◽  
B. Pettersson ◽  
U. Klement
Keyword(s):  
Failure Investigation ◽  
Engine Failure
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