Numerical modeling on installed performance of turbofan engine with inlet ejector

Chen, Haoying; Cai, Changpeng; Jiang, Shangbin; Zhang, Haibo

doi:10.1016/j.ast.2021.106590

Cited by 17 publications

(4 citation statements)

References 27 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In their investigation, Valuation parameters including energy efficiency, exergy destruction ratio, fuel heating value ratio (FHVR), specific fuel consumption (SFC), and Thrust, and so on were considered. Chen et al [4] numerically considered a turbofan with an inlet ejector nozzle fortified with a supplementary inlet door. This supplement has been used in the inlet bypass flow to ejector the nozzle.…”

Section: Introductionmentioning

confidence: 99%

Predicting the energy and exergy performance of F135 PW100 turbofan engine via deep learning approach

Sabzehali

Rabiee

Alibeigi

et al. 2022

Energy Conversion and Management

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 99%

Predicting the energy and exergy performance of F135 PW100 turbofan engine via deep learning approach

Sabzehali

Rabiee

Alibeigi

et al. 2022

Energy Conversion and Management

View full text Add to dashboard Cite

“…For the past few years, research into engine modelling has mainly focused on improvements to the modelling of key components, including inlet ejector [25], multiple variable geometries, and combustion chamber design. Scholars have applied various KF-based methods [26][27][28][29] to estimate engine performance parameters and using various neural networks [30], support vector machine [31], extreme learning machine [32][33][34] to increase the accuracy and the real-time performance of the model in full life circle.…”

Section: Introductionmentioning

confidence: 99%

The Aero-Engine Component-Level Modelling Research Based on NSDE Hybrid Damping Newton Method

Wang

Sun

2022

International Journal of Aerospace Engineering

View full text Add to dashboard Cite

Advanced aero-engine component-level models are characterized by strong nonlinearity and multivariate, and traditional iterative algorithms cannot meet the requirements of convergence, real-time, and accuracy at the same time. To improve the convergence and alleviate the initial value dependence, a hybrid damped Newton algorithm based on the neighborhood based speciation differential evolution (NSDE) is proposed in this paper for solving the aero-engine component-level model. The computational efficiency and convergence of the hybrid damped Newton algorithm and NSDE hybrid damped Newton algorithm under four typical steady-state operating point conditions are analyzed, and then, the accuracy of the model is verified. It is demonstrated that the hybrid damped Newton method has the advantage of low initial value sensitivity and high computational efficiency under large deviation conditions. The hybrid damped Newton method is more efficient than the Broyden algorithm in terms of iterative efficiency, faster than the traditional N-R algorithm in terms of computation speed, and has the highest computational convergence rate under the four typical operating conditions, but it cannot eliminate the initial value dependence. The NSDE hybrid damped Newton method offers high simulation accuracy and greatly increases computational real-time performance under large deviation conditions, and the maximum error between the numerical simulation results and the experimental reference value is 8.1%. This study provides advanced theoretical support for component-level modelling and has certain engineering application value.

show abstract

“…Ejectors with curved-mixing chambers have not been sufficiently studied [33,34]. An aircraft engine with an ejector reduces infrared radiation and specific fuel consumption and increases the installed engine thrust [35]. The ejector thrust booster also makes it possible to solve the problem of noise suppression during aircraft take-off and landing [36].…”

Section: Introductionmentioning

confidence: 99%

Designing Mesh Turbomachinery with the Development of Euler’s Ideas and Investigating Flow Distribution Characteristics

Sazonov

Mokhov²,

Gryaznova³

et al. 2022

Civ Eng J

View full text Add to dashboard Cite

This research discusses developing an Euler turbine-based hybrid mesh turbomachinery. Within the framework of mechanical engineering science, turbomachinery classification and a novel method for mesh turbomachinery design were considered. In such a turbomachine, large blades are replaced by a set of smaller blades, which are interconnected to form flow channels in a mesh structure. Previous studies (and reasoning within the framework of inductive and deductive logic) showed that the jet mesh control system allows for operation with several flows simultaneously and provides a pulsed flow regime in flow channels. This provides new opportunities for expanding the control range and reducing the thermal load on the turbomachine blades. The novel method for performance evaluation was confirmed by the calculation: the possibility of implementing pulsed cooling of blades periodically washed by a hot working gas flow (at a temperature of 1000°C) and a cold gas flow (at a temperature of 20°C) was shown. The temperature of the blade walls remained 490–525°C. New results of ongoing research are focused on creating multi-mode turbomachinery that operates in complicated conditions, e.g., in offshore gas fields. Gas energy is lost and dissipated in the throttle at the mouth of each high-pressure well. Within the framework of ongoing research, the environmentally friendly net reservoir energy of high-pressure well gas should be rationally used for operating a booster compressor station. Here, the energy consumption from an external power source can be reduced by 50%, according to preliminary estimates. Doi: 10.28991/CEJ-2022-08-11-017 Full Text: PDF

show abstract

Numerical modeling on installed performance of turbofan engine with inlet ejector

Cited by 17 publications

References 27 publications

Predicting the energy and exergy performance of F135 PW100 turbofan engine via deep learning approach

Predicting the energy and exergy performance of F135 PW100 turbofan engine via deep learning approach

The Aero-Engine Component-Level Modelling Research Based on NSDE Hybrid Damping Newton Method

Designing Mesh Turbomachinery with the Development of Euler’s Ideas and Investigating Flow Distribution Characteristics

Contact Info

Product

Resources

About