Identification of the fuel-thrust dynamics of a gas turbo engine

Torres, Maricel; Sosa, Guillermo Urriolagoitia; Amézquita-Brooks, Luis; Licéaga‐Castro, Eduardo; Zambrano‐Robledo, Patricia del Carmen

doi:10.1109/cdc.2013.6760588

Cited by 5 publications

(5 citation statements)

References 14 publications

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“…Using an identification approach similar to that reported in Torres et al (2013), Kazemi and Arefi (2017), Matrices A, B and C for a SR-30 micro-turbojet were calculated as: with the corresponding thrust (T) and shaft speed (h ) nonlinearities:…”

Section: Turbojet Mathematical Modelmentioning

confidence: 99%

“…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%

See 1 more Smart Citation

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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Section: Turbojet Mathematical Modelmentioning

confidence: 99%

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

View full text Add to dashboard Cite

show abstract

“…The recursive least squares (RLS) algorithm is well known for tracking dynamic systems. Torres et al [33] attempted to identify the dynamics of the gas turbine engine offline, mainly at steady states with stochastic signals. Arkov et al [34] focused on real-time identification for transient operations and concluded that an engine system could be averaged to a time-invariant first-or second-order transfer function by the extended RLS.…”

Section: Identification Of the Engine Dynamicsmentioning

confidence: 99%

Advanced Constraints Management Strategy for Real-Time Optimization of Gas Turbine Engine Transient Performance

Nikolaidis¹,

Li²,

Jafari³

2019

Applied Sciences

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Motivated by the growing technology of control and data processing as well as the increasingly complex designs of the new generation of gas turbine engines, a fully automatic control strategy that is capable of dealing with different aspects of operational and safety considerations is required to be implemented on gas turbine engines. An advanced practical control mode satisfaction method for the entire operating envelope of gas turbine engines is proposed in this paper to achieve the optimal transient performance for the engine. A constraint management strategy is developed to generate different controller settings for short-range fighters as well as long-range intercontinental aircraft engines at different operating conditions by utilizing a model predictive control approach. Then, the designed controller is tuned and modified with respect to different realistic considerations including the practicality, physical limitations, system dynamics, and computational efforts. The simulation results from a verified two-spool turbofan engine model and controller show that the proposed method is capable of maneuverability and/or fuel economy optimization indices while satisfying all the predefined constraints successfully. Based on the parameters, natural frequencies, and dynamic behavior of the system, a set of optimized weighting factors for different engine parameters is also proposed to achieve the optimal and safe operation for the engine at different flight conditions. The paper demonstrates the effects of the prediction length and control horizon; adding new constraints on the computational effort and the controller performance are also discussed in detail to confirm the effectiveness and practicality of the proposed approach in developing a fully automatic optimized real-time controller for gas turbine engines.

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“…The multivariable instrumental variable/approximate maximum likelihood method of recursive time-series analysis, proposed by Merrill, is used to identify the multivariable (four inputs-three outputs) dynamics of the Pratt & Whitney aero engine [11]. Torres et al [12] attempted to identify the dynamic of the gas turbine engine offline, mainly at steady states with stochastic signals. Arkov et al [13] focused on real-time identification for transient operations and concluded that an engine system could be averaged to a timeinvariant firstor second-order transfer function by the extended recursive least squares [13].…”

Section: Introductionmentioning

confidence: 99%

Study on Identification Method for Parameter Uncertainty Model of Aero Engine

Bai

Shuai

Wang

2019

International Journal of Aerospace Engineering

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The linear model of an aero engine is effective in a small range of the neighborhood of equilibrium points. According to this problem, the identification method for the parameter uncertain linear model of the aero engine was proposed. The identification problem is solved by calculating nonlinear programming. Considering the parameter uncertainty of the model is the critical point of this research during the optimization process. A parameter uncertain model of an aero engine can be obtained, which has large use range. This method is used for DGEN380 aero engine. The two parameters, VDD and VE, are defined for describing error range. Compared with experimental data, the uncertain model of DGEN 380 can simulate the real state of DGEN380 within 1% error range when ΔPLA < 22%. Compared with another conventional method of identification (recursive least squares), the parameter uncertain model, established by the method of this research, has a broad application area through parameter uncertainty of the model.

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Identification of the fuel-thrust dynamics of a gas turbo engine

Cited by 5 publications

References 14 publications

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

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

Advanced Constraints Management Strategy for Real-Time Optimization of Gas Turbine Engine Transient Performance

Study on Identification Method for Parameter Uncertainty Model of Aero Engine

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