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

Bauer, Marc; Friedrichs, Jens; Wulff, Detlev; Werner-Spatz, Christian

doi:10.1115/gt2017-63277

Cited by 8 publications

(3 citation statements)

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“…For practical reasons, the direct measurement of thrust in ight is not yet feasible [16]. Although research has been undertaken in that domain [17], it is common practice for thrust to be deduced indirectly from engine operating parameters and drag determined by equating it to the thrust required for steady level ight [16,18]. One method for the measurement of gross thrust in-ight is to measure the total pressure at the inlet to each nozzle duct, calculate the ideal isentropic thrust and determine the gross thrust through the multiplication of the isentropic thrust by a velocity coecient evaluated from a static ground test [18].…”

Section: Determination Of In-ight Thrustmentioning

confidence: 99%

Installation aerodynamics of civil aero-engine exhaust systems

Otter

Stańkowski

Robinson

et al. 2019

Aerospace Science and Technology

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Without careful consideration of aerodynamic installation eects on exhaust system performance the projected benets of high bypass ratio engines may not be achievable. This work presents a computational study of propulsion system integration in order to quantify the eect that aircraft installation has on the aerodynamic performance of separate-jet aero-engine exhaust systems. Within this study the sensitivity of exhaust nozzle performance metrics to aircraft incidence and under wing position were investigated for two engines of dierent specic thrust. Upon installation, thrust generation was found to be benecial or detrimental relative to an isolated engine depending on the position of the engine relative to the wing leading edge. The dominant installation eect was observed on the exhaust afterbodies and, over the range of engine positions investigated at cruise conditions, the installed modied velocity coecient was shown to vary up to 1 % relative to an isolated engine. Furthermore, due to variations in the core nozzle mass ow rate by

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Section: Determination Of In-ight Thrustmentioning

confidence: 99%

Installation aerodynamics of civil aero-engine exhaust systems

Otter

Stańkowski

Robinson

et al. 2019

Aerospace Science and Technology

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“…Raman et al [19] used PIV to investigate the flow structures of a jet in a miniature fluidic oscillator. However, it is difficult to directly measure the in-flight engine thrust [20]. In-flight optical non-contact measurement of the exhausted jet is also difficult and impractical.…”

Section: Introductionmentioning

confidence: 99%

An Optimized Pressure-Based Method for Thrust Vectoring Angle Estimation

Shi,

Gu,

et al. 2023

Aerospace

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This research developed a pressure-based thrust vectoring angle estimation method for fluidic thrust vectoring nozzles. This method can accurately estimate the real-time in-flight thrust vectoring angle using only wall pressure information on the inner surface of the nozzle. We proposed an algorithm to calculate the thrust vectoring angle from the wall pressure inside the nozzle. Non-dominated sorting genetic algorithm II was applied to find the optimal sensor arrays and reduce the wall pressure sensor quantity. Synchronous force and wall pressure measurement experiments were carried out to verify the accuracy and real-time response of the pressure-based thrust vectoring angle estimation method. The results showed that accurate estimation of the thrust vectoring angle can be achieved with a minimum of three pressure sensors. The pressure-based thrust vectoring angle estimation method proposed in this study has a good prospect for engineering applications; it is capable of accurate real-time in-flight monitoring of the thrust vectoring angle. This method is important and indispensable for the closed-loop feedback control and aircraft attitude control of fluidic thrust vectoring control technology.

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“…Lufthansa Technik (LHT) and the Institute of Jet Propulsion and Turbomachinery of Technische Universitat Braunschweig develop a method for direct measurement of engine thrust during the operation. 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 (Bauer et al, 2017).…”

Section: Introductionmentioning

confidence: 99%

The thrust measurement system research for combined nozzle in small space

Lü

Zhang

et al. 2018

Transactions of the Institute of Measurement and Control

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For measuring the thrust of combined nozzles in satellite thruster with a small space, the test method that the nozzle directly sprays on the load baffle is employed in this paper. The key problem is how to design the positions of 10 load baffles and how to construct the measurement system. A set of complete and automatic nozzle thrust measurement system is designed and built, and the influence of the load baffle applied on the flow field of nozzles is analyzed using the software FLUENT. Furthermore, the load surface locations of the sensors for the different types of nozzles are analyzed. We draw the conclusion that the load baffle position should range from 4–8 mm for the I-type nozzle and range in 6–12 mm for II-type and III-type nozzle. The correction coefficients of the thrust forces for all channels of the measurement system are determined in the calibration experiment. The uncertainty of measurement system is estimated and the error source of the measurement system is traced. We found that the systematic uncertainty is mainly contributed by the A-type uncertainty which is related with the nozzle dimension and its inner structure. The B-type uncertainty of system is contributed by the force sensor.

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

Cited by 8 publications

References 0 publications

Installation aerodynamics of civil aero-engine exhaust systems

Installation aerodynamics of civil aero-engine exhaust systems

An Optimized Pressure-Based Method for Thrust Vectoring Angle Estimation

The thrust measurement system research for combined nozzle in small space

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