Experimental Evaluation of Different Microturbojet EGT Modeling Approaches

Villarreal-Valderrama, Francisco; Licéaga‐Castro, Eduardo; Zambrano‐Robledo, Patricia del Carmen; Amézquita-Brooks, Luis

doi:10.1061/(asce)as.1943-5525.0001205

Cited by 6 publications

(4 citation statements)

References 39 publications

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“…The resulting LADRC + LSC is evaluated with real operational data measured from turbojet operation and the non-linear simulation of the variable exhaust nozzle of Equation (11). The data was measured with the SR-30 turbojet test bench, which has been previously used to perform thermodynamic and data-mining analyses [5]. This test-bench allows measuring the generated thrust, shaft speed, fuel flow and gas-path properties at the input and output of each component.…”

Section: Case Of Study: Exhaust Nozzle Area Controlmentioning

confidence: 99%

“…Small-scale turbojets applications usually involve operating in environments with different sources of disturbances, from wind gusts and variations in the ambient conditions to more complex situations, such as variations in the effective payload [4] that modify the required throttle turbojet setting. These turbojet disturbances translate into disturbances in both the nozzle input and nozzle output, since the turbojet thermal state directly affects the input nozzle gas-path properties [5]. Maximizing the thrust production requires variable exhaust nozzles that reject the operating disturbances while optimally expanding the exhaust gas to the ambient conditions.…”

Section: Introductionmentioning

confidence: 99%

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Turbojet Thrust Augmentation through a Variable Exhaust Nozzle with Active Disturbance Rejection Control

Villarreal-Valderrama

Zambrano‐Robledo

Hernández-Alcantara

et al. 2021

Aerospace

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Turbojets require variable exhaust nozzles to fit high-demanding applications; however, few reports on nozzle control are available. The purpose of this paper is to investigate the possible advantages of an exhaust gas control through a variable exhaust nozzle. The control design method combines successful linear active disturbance rejection control (LADRC) capabilities with a loop shaping controller (LSC) to: (i) allow designing the closed-loop characteristics in terms of gain margin, phase margin and bandwidth, and (ii) increase the LSC disturbance rejection capabilities with an extended state observer. A representation of the nozzle dynamics is obtained from first principles and adapted to achieve a stream-velocity-based control loop. The results show that the resulting controller allows improving the expansion of the exhaust gas to the ambient pressure for the whole operating range of the turbojet, increasing the estimated thrust by 14.23% during the tests with experimental data.

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Section: Case Of Study: Exhaust Nozzle Area Controlmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Turbojet Thrust Augmentation through a Variable Exhaust Nozzle with Active Disturbance Rejection Control

Villarreal-Valderrama

Zambrano‐Robledo

Hernández-Alcantara

et al. 2021

Aerospace

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“…The state-space representation (1) in combination with equations ( 5) and ( 6) yields the complete turbojet Wiener model. Note that further specifics on aeroengine modeling are out of the scope of this article; the interested reader is referred to Torres et al (2013), Mohammadi and Montazeri-Gh (2015), Koleini et al (2018), Villarreal-Valderrama et al (2020. The goal of aeroengine control is to maintain the thrust production within a set of specified robustness and performance parameters.…”

Section: Turbojet Mathematical Modelmentioning

confidence: 99%

Turbojet direct-thrust control scheme for full-envelope fuel consumption minimization

Villarreal-Valderrama

Delgado

Zambrano‐Robledo

et al. 2020

AEAT

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Purpose Reducing fuel consumption of unmanned aerial vehicles (UAVs) during transient operation is a cornerstone to achieve environment-friendly operations. The purpose of this paper is to develop a control scheme that improves the fuel economy of a turbojet in its full operating envelope. Design/methodology/approach A novel direct-thrust linear quadratic integral (LQI) approach, comprised by an optimal observer/controller satisfying specified performance parameters, is presented. The thrust estimator, based in a Wiener model, is validated with the experimental data of a micro-turbojet. Model uncertainty is characterized by analyzing variations between the identified model and measured data. The resulting uncertainty range is used to verify closed-loop stability with the circle criterion. The proposed controller provides stable responses with the specified performance in the whole operating range, even with after considering plant nonlinearities. Finally, the direct-thrust LQI is compared with a standard thrust controller to assess fuel economy and performance. Findings The direct-thrust LQI approach reduced the fuel consumption by 2.1090% in the most realistic scenario. The controllers were also evaluated using the environmental effect parameter (EEP) and transient-thrust-specific fuel consumption (T-TSFC). These novel metrics are proposed to evaluate the environmental impact during transient-thrust operations. The direct-thrust LQI approach has a more efficient fuel consumption according to these metrics. The results also show that isolating the thrust dynamics within the feedback loop has an important impact in fuel economy. Controllers were also evaluated using the EEP and T-TSFC. These novel metrics are proposed to evaluate the environmental impact during transient-thrust operations. The direct-thrust LQI approach has a more efficient fuel consumption according to these metrics. The results also show that isolating the thrust dynamics within the feedback loop has an important impact in fuel economy. Originality/value This study shows the design of an effective direct-thrust control approach that minimizes fuel consumption, ensures stable responses for the full operation range, allows isolating the thrust dynamics when designing the controller and is compatible with classical robustness and performance metrics. Finally, the study shows that a simple controller can reduce the fuel consumption of the turbojet during transient operation in scenarios that approximate realistic operating conditions.

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“…They estimated the parameters of the created engine model by using regression analysis and applied it to real engine test data to validate the proposed approach. Villarreal-Valderrama et al (2020) evaluated the prediction accuracy of many different models at various exhaust gas temperatures through detailed experimental data obtained as a result of the operation for three years by determining that one of the health indicators of small-scale turbojet engines is the temperature of the combustion products passing through the exhaust. In this way, they made available comparative information about the advantages and disadvantages of the various models considered in the study.…”

Section: Introductionmentioning

confidence: 99%

Performance of a microjet using component map scaling

Coban¹,

Ekici

Çolpan

et al. 2021

AEAT

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Purpose This paper aims to investigate the cycle performance of a small size turbojet engine used in unmanned aerial vehicles at 0–5,000 m altitude and 0–0.8 Mach flight speeds with real component maps. Design/methodology/approach The engine performance calculations were performed for both on-design and off-design conditions through an in-house code generated for simulating the performance of turbojet engines at different flight regimes. These calculations rely on input parameters in which fuel composition are obtained through laboratory elemental analysis. Findings Exemplarily, according to comparative results between in-house developed performance code and commercially available software, there is 0.25% of the difference in thrust value at on-design conditions. Practical implications Once the on-design performance parameters and fluid properties were determined, the off-design operation calculations were performed based on the compressor and turbine maps and scaling methodology. This method enables predicting component maps and fitting them to real conditions. Originality/value A method to be used easily by researchers on turbojet engine performance calculations which best fits to real conditions.

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Experimental Evaluation of Different Microturbojet EGT Modeling Approaches

Cited by 6 publications

References 39 publications

Turbojet Thrust Augmentation through a Variable Exhaust Nozzle with Active Disturbance Rejection Control

Turbojet Thrust Augmentation through a Variable Exhaust Nozzle with Active Disturbance Rejection Control

Turbojet direct-thrust control scheme for full-envelope fuel consumption minimization

Performance of a microjet using component map scaling

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