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.

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.

scholarly journals Estimation of the flight thrust increment changing the operation mode of the engine

2018 ◽  
Vol 18 ◽  
pp. 01002
Author(s):  
O.N. Korsun ◽  
S.Yu. Prihodko ◽  
S.A. Sergeev
Keyword(s):  
Drag Force ◽  
Aerodynamic Drag ◽  
Operation Mode ◽  
Aircraft Engine ◽  
Flight Test ◽  
Problem Formulation ◽  
Engine Operation ◽  
Engine Thrust ◽  
Ill Posed ◽  
To Come

The paper presents a new method for flight test identification of the thrust increment when changing engine operation mode. It is known that the problem of separate estimation of the engine thrust and the aerodynamic drag force from the aircraft flight data belongs to a class of ill-posed. The idea of the presented method is to come out of the ill-posed class by changing the original problem formulation. To achieve this purpose we give up the absolute values of the thrust and proceed to estimating the thrust increment resulting from the change of the aircraft engine operation mode. The accuracy of the solution is improved by introducing the special flight test maneuver. The algorithm requires only a few on-board measured parameters, such as longitudinal and normal overload, airspeed and altitude, and angle of attack. The complimentary use of the engine gas-dynamic model may improve the estimates but is not obligatory. The proposed method also does not require a-priory estimates of the aerodynamic drag force.

scholarly journals TECHNOLOGICAL PROCESSES AND QUALITY CONTROL IN AIRCRAFT ENGINE MAINTENANCE

Aviation ◽  
2015 ◽  
Vol 19 (3) ◽  
pp. 133-137 ◽  
Author(s):  
Sergiy Dmitriev ◽  
Vadym Burlakov ◽  
Oleksandr Popov ◽  
Dmytro Popov
Keyword(s):  
Quality Control ◽  
Quality Assessment ◽  
Aircraft Engine ◽  
Technological Processes ◽  
Engine Maintenance

The paper analyzes some issues which refer to the quality assessment of operations performed by aviation specialists when maintaining aircraft. Technological processes and quality control in aircraft engine maintenance are considered.

Design of Fault Tolerant Control Laws for Jet Engines

2013 ◽  
Vol 367 ◽  
pp. 96-100
Author(s):  
Rachel Francis Sneha ◽  
J.S. Mija
Keyword(s):  
Fault Tolerant ◽  
Pressure Ratio ◽  
Jet Engines ◽  
Engine Operation ◽  
Control Laws ◽  
Engine Thrust ◽  
Fuel Flow ◽  
Thrust Measurement ◽  
Range Rate ◽  
Exhaust Jet

Full Authority Digital Electronic Control (FADEC) system is common in all modern jet engines. In jet engine, the simplest control system is to produce desired engine thrust by changing the fuel flow. Since in flight engine thrust measurement is practically not possible, engine low pressure shaft rotational speed (N1/NL), engine pressure ratio (EPR), or exhaust jet temperature (EJT) has been effectively used as an indicator of the engine thrust. In this paper, the model used is twin spool turbofan engine. If any fault occurs in N1 sensor, the entire engine operation will be affected. Since there exists a unique aerodynamic relationship among the spool speeds, if any fault occurs in N1 sensor, engine thrust can be controlled with a certain amount of degradation using high pressure spool speed (N2/NH).Both soft and hard failures are detected using kalman filter, range, rate and comparison techniques. The effectiveness of the proposed approach is demonstrated by means of simulations.

ABOUT NECESSITY OF MATHEMATICAL MODELING OF THE BUSINESS PROCESS OF COST ESTIMATE CALCULATIONS IN THE CONSTRUCTION OF OIL AND GAS FACILITIES

2017 ◽  
pp. 139-145
Author(s):  
R. I. Hamidullin ◽  
L. B. Senkevich
Keyword(s):  
Mathematical Modeling ◽  
Quality Assessment ◽  
Business Process ◽  
Oil And Gas ◽  
Oil And Gas Industry ◽  
Gas Industry ◽  
Construction Organizations ◽  
The Cost ◽  
Cost Of Construction

A study of the quality of the development of estimate documentation on the cost of construction at all stages of the implementation of large projects in the oil and gas industry is conducted. The main problems that arise in construction organizations are indicated. The analysis of the choice of the perfect methodology of mathematical modeling of the investigated business process for improving the activity of budget calculations, conducting quality assessment of estimates and criteria for automation of design estimates is performed.

An acoustic liner design methodology based on a statistical source model

2021 ◽  
pp. 1475472X2110238
Author(s):  
Douglas M Nark ◽  
Michael G Jones
Keyword(s):  
Design Methodology ◽  
Three Dimensional ◽  
Aircraft Engine ◽  
Flight Test ◽  
Source Model ◽  
Practical Implementation ◽  
Source Information ◽  
Fan Noise ◽  
Future Design ◽  
Acoustic Liner

The attenuation of fan tones remains an important aspect of fan noise reduction for high bypass ratio turbofan engines. However, as fan design considerations have evolved, the simultaneous reduction of broadband fan noise levels has gained interest. Advanced manufacturing techniques have also opened new possibilities for the practical implementation of broadband liner concepts. To effectively address these elements, practical acoustic liner design methodologies must provide the capability to efficiently predict the acoustic benefits of novel liner configurations. This paper describes such a methodology to design and evaluate multiple candidate liner configurations using realistic, three dimensional geometries for which minimal source information is available. The development of the design methodology has been guided by a series of studies culminating in the design and flight test of a low drag, broadband inlet liner. The excellent component and system noise benefits obtained in this test demonstrate the effectiveness of the broadband liner design process. They also illustrate the value of the approach in concurrently evaluating multiple liner designs and their application to various locations within the aircraft engine nacelle. Thus, the design methodology may be utilized with increased confidence to investigate novel liner configurations in future design studies.

scholarly journals Certain investigation on RC aircraft engine to identify the suitability of Methanol and Castor oil Alternative fuel

2021 ◽  
Vol 850 (1) ◽  
pp. 012010
Author(s):  
S Yuvaraj ◽  
C J Thomas Renald ◽  
A P Senthil Kumar ◽  
K Sadesh ◽  
D Naveen Promoth
Keyword(s):  
Castor Oil ◽  
Calorific Value ◽  
Aircraft Engine ◽  
Fuel Properties ◽  
Aircraft Engines ◽  
New Creation ◽  
Emission Standards ◽  
Fire Point ◽  
Alternate Fuel ◽  
The Cost

Abstract In the current age drones are broadly utilized for different applications in pretty much every field. Because of the disturbing expense of the glow fuel utilized in the RC motors, utilization of the equivalent includes a ton of capital. Adding to it, the current fuel brings about intermittent combustion is in demand of alternate fuel. This paper manages the investigation of existing fuel synthesis and discovering the cost required to dispose of the high capital included, so that considerably more tests and study utilizing the RC Engines 2.5 cc can be completed easily. Methanol and Castor oil Combination is considered as an alternate fuel. The approach includes testing of the fuel to decipher the substance parts and their individual pieces through a progression of tests. Followed by the study of possible additives to enhance the performance of the engine without actually altering the timing intervals. The new creation of the fuel showed up is blended in with extraordinary hardware and the equivalent is tried for essential fuel properties viz., Density, Flash point, Fire point, Calorific value, and so forth The productivity arrangement is made utilizing a pulley instrument and the equivalent is tried for both the energizes. Performance of the R/C aircraft engine was tested with existing glow fuel and the new blend. Results are compared and concluded that the designed blend is a potent alternate fuel for R/C aircraft engines. *Future scope: It can be further tested for its SFC and emission standards. The outcome shows that the new fuel is exceptionally cost productive and the essential substance properties are profoundly improved.

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