journal: International Journal of Turbo & Jet-Engines

Impact Factor: 1.923

Published since March 1, 1985

International Journal of Turbo & Jet-Engines

ISSN: 2191-0332

Editor-in-chief: Valery Sherbaum

Edited by: Vladimir Erenburg

About this journal

Objective
The Main aim and scope of this Journal is to help improve each separate components R&D and superimpose separated results to get integrated systems by striving to reach the overall advanced design and benefits by integrating: (a) Physics, Aero, and Stealth Thermodynamics in simulations by flying unmanned or manned prototypes supported by integrated Computer Simulations based on: (b) Component R&D of: (i) Turbo and Jet-Engines, (ii) Airframe, (iii) Helmet-Aiming-Systems and Ammunition based on: (c) Anticipated New Programs Missions based on (d) IMPROVED RELIABILITY, DURABILITY, ECONOMICS, TACTICS, STRATEGIES and EDUCATION in both the civil and military domains of Turbo and Jet Engines.

The　International Journal of Turbo & Jet Engines　is devoted to cutting edge research in theory and design of propagation of jet aircraft. It serves as an international publication organ for new ideas, insights and results from industry and academic research on thermodynamics, combustion, behavior of related materials at high temperatures, turbine and engine design, thrust vectoring and flight control as well as energy and environmental issues.

Topics

Turbo and jet engines
Theory and design of propagation of (advanced) jet aircraft
Thermodynamics
Combustion
Behavior of materials at High temperatures
Turbine and engine design
Thrust vectoring or Jet-Engine-Steering in effecting improved Flight control
Energy and environmental issue
Stealth in Integrated Systems Design, including jet-engine inlets and exhausts
Vectoring and safety in air, sea and land jet systems

Article formats
The journal welcomes scholarly research papers, invited review articles, and short communications

Your Benefits

Cutting edge researches in theory and design of propagation of jet aircraft
New ideas crossing bridges between science and engineering
Special attention to environmental and safety issues
Top authors and reviewers
Internationally recognized editorial board

History

Previously published by Freund Publishing House Ltd.

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Volume 40 Issue 1

March 2023

Publicly Available March 7, 2023

Frontmatter

Page range: i-iii

Download PDF

February 21, 2023

Integration of a transonic high-pressure turbine with a rotating detonation combustor and a diffuser

Zhe Liu, James Braun, Guillermo Paniagua

Page range: 1-10

Abstract

In this paper, a diffuser is used to integrate a transonic high-pressure turbine with a rotating detonation combustor (RDC). The paper focuses on the required design modifications to the turbine endwalls (EW) to enable high efficiency, while preserving the airfoil blade-to-blade geometry. The main challenge is the stator passage unstarting, due to the high inlet Mach number. First of all, steady Reynolds Averaged Navier Stokes simulations were performed to compare the efficiency of turbines with constant-radius EWs to turbines with axisymmetric EWs. A modified EW design prevented the unstarting of the stator passage, enabling a significant gain in performance. Afterward, the influence on the turbine efficiency and damping due to the unsteadiness from the diffuser-like fluctuations of the RDC was evaluated with unsteady Reynolds Averaged Navier Stokes simulations with a mixing plane approach (MPA). Full unsteady simulations were carried out on selected inlet conditions and compared to the mixing plane results. This parametric study provides turbine designers with recommended diffusion rates along the vane EWs. Additionally, we provide guidance on the upstream diffuser design, specifically the required damping and outlet Mach number.

February 21, 2023

Prediction of compressor nominal characteristics of a turboprop engine using artificial neural networks for build standard assessment

C. Jagadish Babu, Mathews P. Samuel, Antonio Davis, R. K. Mishra

Page range: 11-20

Abstract

Compressor characteristics of a single spool turboprop engine have been studied in this paper. It has been brought outhow constant power lines in the compressor characteristics of these compressors make them different from others. Constant speed lines and constant power lines have also been highlighted. A novel method of modeling of compressorof a single spool turboprop engine has also been studied in this paper. Application of neural networks in prediction of compressor characteristics has been investigated. Multilayer Perceptron feed forward neural network has been considered with different transfer functions to assess the potential capability of network in extrapolation and interpolation. Effectiveness of prediction with and without engine bleed valve open and anti-ice valve open situations have been assessed. Network Predictionshas been compared with engine test data to assess the accuracy of prediction and to quantify the build variation in the manufacture of engines. Capability of network with limited test data to predict the complete performance has also been assessed and presented in this paper.

August 8, 2020

Study on inversion control for integrated helicopter/engine system with variable rotor speed based on state variable model

Yong Wang, Qiangang Zheng, Haibo Zhang, Haoying Chen

Page range: 21-29

Abstract

In order to realize the fast response control for turboshaft engine with variable rotor speed, a dynamic inversion (DI) control method based on state variable model of turboshaft engine is proposed. Meanwhile, in order to expand the application of dynamic inversion controller, the linear parameter varying (LPV) model of turboshaft engine is applied, which constitutes the LPV/DI controller together. The simulation results shows that compared with the conventional PID controller, the LPV/DI controller can effectively reduce the overshoot/droop of the power turbine speed to less than 1% under different flight conditions. The control effect is remarkable and the robust performance is superior.

Open Access August 17, 2020

Effects of casing angle on the performance of parallel hub axial annular diffuser

Hardial Singh, B.B. Arora

Page range: 31-41

More Download PDF

Abstract

In this paper, the effects of non-swirling and swirling flow on the performance of parallel hub axial annular diffuser has been investigated. The study was conducted on a fully developed swirling flow and non-swirling flow to predict the separation of the flow from the wall. Three different annular diffusers were used with casing wall angles of 3°, 6°, and 9°. Furthermore, various swirl angles (0–25°) at the inlet of diffusers have been investigated to analyze the performance across the length. It was found that parallel hub axial annular diffuser performance increases up to a certain length as the inlet swirl angle increases. However, the performance also improves as the diffuser area ratio (AR) increases. The performance is evaluated based on the static pressure recovery coefficient (C p ) and the total pressure loss coefficient (C TL ). The highest possible pressure recovery is achieved by the 12° swirl angle with a casing angle of 6°.

August 17, 2020

Experimental research on the performance of the forward variable area bypass injector for variable cycle engines

Binglong Zhang, He Liu, Jianhua Zhou, Hui Liu

Page range: 43-47

Abstract

The forward variable area bypass injector (FVABI) is a key component of double bypass variable cycle engine (VCE) to achieve mode transition and bypass ratio adjustment. In this paper, an experimental system for FVABI was constructed based on the analysis of relevant experimental theories, and then the experiments on FVABI were carried out for a specific working state in double bypass mode of VCE and for the comparison working states with different area ratios and different back pressure ratios. The results showed that the FVABI designed in this paper meets the requirements of VCE at this working state. The analysis of the influence of area ratio and back pressure ratio on the injection coefficient showed that the first bypass valve and back pressure were effective means to control the mass flow of FVABI.

August 17, 2020

Film cooling characteristics on a grooved surface with different injection orientation angles

Peng Yang, Guangchao Li, Jianyong Zhu

Page range: 49-57

Abstract

The film effectiveness was investigated on a grooved surface with the injection orientation angles of 30°, 90°, and 150° at the blowing ratios of 0.5, 0.8, 1.1, and 1.4. The injection orientation angle and the groove on the surface caused the effect of the various and irregular shaped hole injection due to the different orientation injection. The results showed that the new phenomenon of film effectiveness distributions was found on the grooved surface compared with the flat plate case. Film effectiveness distributions for the β = 30° were found to be the discontinuous strips. The surface averaged film effectiveness with the orientation angle of 30° was found to decrease with the increase of the blowing ratio. Additionally, the reverse trend was observed with the orientation angle of 150°. The film effectiveness with the orientation angle of 90° only slightly changed with the increase of the blowing ratio.

June 28, 2021

Aero-thermal optimization of the rim seal cavity to enhance rotor platform thermal protection

Paht Juangphanich, Guillermo Paniagua

Page range: 59-70

Abstract

The flow field in the rotor-stator rim cavity is controlled by both the instantaneous distortion caused by rotor and stator airfoils. Naturally one would then assume that the design of optimal rim seal geometries would require full unsteady turbine stage simulations, that would then require an experimental assessment. This manuscript presents a reduced-order approach, neglecting the obvious unsteady interaction effects, to optimize the cavity geometry with a two-dimensional axisymmetric approach, making it possible to explore a wide range of geometries followed by an experimental assessment in a linear cascade. Two parameterization strategies are presented, coupled with a genetic optimizer to maximize thermal protection to the rotor rear platform while minimizing the cooling massflow required. This reduced-order optimization scheme was then assessed at different levels of sophistication to assess the effect of rotation, the vanes, and the rotor geometry with a series of increasing levels of fidelity to the real turbine conditions. Finally, this paper demonstrated the sensitivity of the optimal geometries to variations in the axial gap and purge coolant total pressure.

September 16, 2020

Numerical study of the parameters of a gas turbine combustion chamber with steam injection operating on distillate fuel

Serhiy Serbin, Kateryna Burunsuz

Page range: 71-80

Abstract

Investigations of the working process in a gas turbine combustion chamber with ecological and energy steam injection operating on liquid fuel are conducted. The mathematical model of the aerodynamic processes and liquid fuel combustion in similar burning devices based on the numerical solution of the system of conservation and transport equations for a multi-component chemically reactive turbulent system is developed. The influence of the relative steam mass flow rate (the ratio of the sum of the mass flow rates of ecological and energy steam to the fuel consumption) on the combustion chamber’s emission characteristics is determined. The obtained results can be used for parameter selection and optimization of promising high-temperature gas turbine combustion chambers with steam injection operating on liquid fuels.

September 16, 2020

An active fault-tolerant control strategy of aircraft engines based on multi-model predictive control

Xian Du, Yan-Hua Ma

Page range: 81-91

Abstract

In order to mitigate or even eliminate the adverse effects caused by typical components faults of aircraft engines, an active fault-tolerant strategy based on multi-model predictive control is proposed, which consists of a pre-established multi-model library, a judgement module, and corresponding predictive controllers with smooth transition switching logic. Multiple dynamic nonlinear or linear models are firstly established by means of system identification methods, based on the component-level nonlinear engine model or historical data in faults cases. The judgement module is utilized to online compare the engine measured outputs with that of all models in the pattern library and select the best matched dynamic model on the basis of outputs error quadratic performance index, thus determining the most appropriate predictive controller for the next control sample period. When a certain fault occurs, the fault model in the library could be identified and fault-model based predictive controller is activated. Finally, two kinds of pre-considered high-pressure compressor and high-pressure turbine component-level faults are taken as an example to design the active fault-tolerant controller. Simulation results show that the judgement module owns the ability to sense the fault and gives smooth switching signal to the suitable predictive controller, verifying the effectiveness of the proposed technique.

October 7, 2020

Conjugate heat transfer analysis of a radially cooled nozzle guide vane in an aero gas turbine engine

G. L. Arunkumar, Balachandra P. Shetty, R. K. Mishra

Page range: 93-100

Abstract

This paper presents a computational method to investigate cooling performance of NASA-C3X cascade vane coated with thermal barrier coating (TBC), for which experimental data are available. The vane was cooled internally by air flows through radially oriented 10 channels. A three-dimensional conjugate heat transfer simulation has been performed which allows the conduction-convection on metal vane by eliminating need of multiple boundary solutions. The predicted aerodynamic and thermal loads with the effect of turbulent intensity is found to be good agreement with experimental data and inclusion of TBC leads to quantitative reduction in vane metal temperature.

October 14, 2020

A new method to improve the real-time performance of aero-engine component level model

Changpeng Cai, Qiangang Zheng, Haibo Zhang

Page range: 101-109

Abstract

In order to improve the real-time performance of aero-engine component-level models, an automatic fast positioning interpolation method is proposed. Based on the maximum parameter slope, this method can automatically determine the interpolation cut in point, change the disadvantage of low efficiency of traditional sequential interpolation from the starting point, effectively reduce the interpolation interval, thus greatly improving the efficiency of interpolation. The method is applied to the calculation of gas thermodynamic parameters and the interpolation of the characteristic of rotating parts ,so as to ameliorate the real-time performance of the single-stage flow path calculation of the component-level model. Simulation results show that, compared with the traditional method, the method proposed in this paper improves the fan characteristic calculation efficiency by 47.5%, reduces the time of single complete flow calculation by 74.3% when the dynamic and steady-state accuracy changes are less than 0.4%, which greatly improves the real-time performance of the component-level model.

October 20, 2020

Experimental and numerical investigation of expansion corner effects on isolator performance

Jaimon D. Quadros, Sher Afghan Khan, T. Prashanth

Page range: 111-118

Abstract

In the present study, the effect of expansion corner on suddenly expanded flow process has been studied. Experimental investigations have been carried out on a convergent-divergent (C-D) nozzle and isolator duct, where the expansion of the channel is formed through the presence of a 1, 2 and 3 expansion corners (EC) respectively. Flow from nozzle exit of the nozzle of Mach, M = 2.0 was suddenly expanded into the axi-symmetric duct having a cross sectional area of 4.84 times the nozzle exit area. The wall static pressure along the length of the duct and the Pitot pressure at the exit plane of the duct were measured for all the configurations. Computational fluid dynamics (CFD) technique was employed for visualizing the shock-train in the expanded duct. The isolator with one expansion corner was found to be more efficient in achieving a high static pressure rise. The experimental and numerical wall static pressure distribution values were compared for isolators with EC = 2 and found to be in good agreement with each other with a maximum absolute percentage deviation of 11%.

Ahead of Print / Just Accepted

Ahead of Print / Just Accepted

Volume 40 (2023)

Issue 1

Volume 39 (2022)

Volume 38 (2021)

Volume 37 (2020)

Volume 36 (2019)

Volume 35 (2018)

Volume 34 (2017)

Volume 33 (2016)

Volume 32 (2015)

Volume 31 (2014)

Volume 30 (2013)

Volume 29 (2012)

Volume 28 (2011)

Volume 27 (2010)

Volume 26 (2009)

Volume 25 (2008)

Volume 24 (2007)

Volume 23 (2006)

Volume 22 (2005)

Volume 21 (2004)

Volume 20 (2003)

Volume 19 (2002)

Volume 18 (2001)

Volume 17 (2000)

Volume 16 (1999)

Volume 15 (1998)

Volume 14 (1997)

Volume 13 (1996)

Volume 12 (1995)

Volume 11 (1994)

Volume 10 (1993)

Volume 9 (1992)

Volume 8 (1991)

Volume 7 (1990)

Volume 6 (1989)

Volume 5 (1988)

Issue 1-4

Volume 4 (1987)

Volume 3 (1986)

Issue 2-3

Volume 2 (1985)

5-year Impact Factor	1.511
Cite Score	2.1
Impact Factor	1.923
Journal Citation Indicator	0.46
SCImago Journal Rank	0.281
Source Normalized Impact per Paper	0.765

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Editorial

Editor-In-Chief
Valery Sherbaum, Technion, Haifa, Israel; valerys@technion.ac.il

Current Editorial Board Members:

Prof. Ernesto Benini, Universita di Padova, ernesto.benini@unipd.it
Prof. Dr. Saeed Farokhi,The University of Kansas,sfarokhi@ku.edu
Prof. Dr. Rama S. R. Gorla,Cleveland State University, Cleveland, Ohio, r.gorla@yahoo.com
Prof. Changduk Kong, Korea, cdgong@Chosun.ac.kr
Prof. Yeshayahou Levy,Technion, Israel,levyy.tecnion@gmail.com
Prof. Gao Limin, Northwestern Polytechnical University, China
Prof. Dr.Debi Prasad Mishra, Combustion Lab, Indian Institute of Technology,Mishra@iitk.ac.il
Dr. R. K. Mishra,The Center for Military Airworthiness and Certification,rkmishra.drdo@gmail.com
Prof. Dr. Rishi S. Raj,The City College of New York,raj@ccny.cuny.edu
Prof. Dr. Arvind Rao,Delft University, Holland,A.GangoliRao@tudelft.nl
Prof. Dr.Matsuo Shigeru, Department of Science and Engineering, Saga University, Japan,matsuo@me.saga-u.ac.jp
Prof. Dr. Shun-Peng Zhu,Center for System Reliability & Safety, University of Electronic Science and Technology of China (UESTC),zhu.s.peng@gmail.com
Prof. Dr. Yasin Sohret, Suleyman Demirel University, Isparta/Turkey, ysohret@gmail.com, sinsohret@sdu.edu.tr
Dr. Yuan Wei, Shanghai University, China,weiyuan0315@sina.com

Original Editorial Board Members:
E. Benstein, A. Brooks, Z. Goraj, R.D. Halverstadt, M.J. Ivanov, J. Sasion, Changduk Kong. C. Kuintzle, L. Larson, Shigeru Matso, D.P. Mishra, R.K. Mishra, M.V. Narasimhan, Youry A. Noznitsky, Noel Penny, C.R. Peterson, M.F. Platzer, A. Rao, Risshi S. Raj, Brian Spalding, W. Tabakoff, E. Tjonneland, P.J. Torvik, P.C. Tramm, Mitch Wolff, S. Yu, J. Zierep.

Reviewers

Professor IGOR LOBODA
iloboda@ipn.mx
INSTITUTO POLITCNICO NACIONAL Mexico
Gas turbine design
Systems and accessories of gas turbines
Gas turbine diagnostics

Dr. JUAN LUIS PREZ RUIZ
perezruiz305@gmail.com
INSTITUTO POLITCNICO NACIONAL Mexico
Gas turbine condition monitoring and diagnostics
Gas turbine performance simulation
Data-driven and physics-based approaches for gas turbine diagnostics
Artificial neural networks and machine learning techniques
Pattern recognition

PROF. YUAN WEI

weiyuan0315@sina.com

Renmin University of China Beijing Municipality , China

Bristle pack thickness,

Fence height and clearance size on aerodynamic force,

Stiffness and damping of internal brush seals under different operating conditions

PROF. DR. HSIAO-WEI D. CHIANG , Taiwan
hwchiang@pme.nthu.edu.tw
aeromechanics,
aeroacoustics,
rotor dynamics,
turbomolecular pumps,
dental air turbines, green energy,
clean air to power, SOFC/MGT, micro power,
microturbine generator system,
hybrid vehicle, and ocean
current turbine generation.

PROF. ONDER TURAN
onderturan@anadolu.edu.tr
Anadolu University, Turkey
Propulsion,
Exergy,
Thermodynamics,
Gas Turbines And Ecology Technology.

PROF. YASIN SOHRET
yasinsohret@sdu.edu.tr
Sleyman Demirel University School of Civil Aviation
Gas turbine engine measurements,
Combustion and fuels,
Energy and exergy analysis of thermal systems.

PROF. TOLGA BAKLACIO
tbaklacioglu@anadolu.edu.tr
Anadolu University, Turkey
Optimization of Non-linear and Dynamic Systems in Aeronautics, Fuel Flow Rate Modeling of Turbofan Engines,
Modeling of Exergy and Energy Efficiency and Sustainability Parameters of Aero-Engines, Aircraft Trajectory Prediction Models, Aircraft Emissions Index Estimation Modeling for Turbojet/Turbofan Aircraft,
Thrust Models for Turbofan Engines,
Artificial Neural Networks,
Learning Algorithms,
Deep Learning and Extreme Learning Techniques,
Genetic Algorithms,
Ant Colony Optimization,
Particle Swarm Optimization,
Evolutionary Algorithms, Stochastic Algorithms,
Simulated Annealing

Prof. Dr.S.Thanigaiarasu
sthanigaiarasu@mitindia.edu, thanigaiarasus@annauniv.edu
Anna UniversityChennai, Tamilnadu India
High Speed Jets,
Populsion
Aerodynamics
Jet Acoustics
Heat transfer
Computational fluid dynamics

Prof. S.Elangovan
subelango@yahoo.co.in
Bharath Institute of Higher Education and Research, Chennai-73, INDIA
Jet Mixing, Passive Control Of Jets, Bluff Body Aerodynamics

Dr. Valeriu Dragan
valeriu.dragan@comoti.ro
INCDT Comoti,, Bucuresti (Romania)
Centrifugal compressor design, CFD and testing
Axial compressors and fan design, CFD and testing
Surge and Stall in compressors and fans
Design optimization methods and practices (Genetic Algorithms, Artificial Neural Networks, Adjoint Method)
Radial turbine design, CFD and testing
Generic CFD of aviation components

Dr. Chong Zhong
cz29@zips.uakron.edu
The University of Akron, Akron, OH
fluid dynamics analysis,
lubrication/fuel system modeling (FEA&CFD),
non-contact measurement systems design /calibration /testing,
signal acquisition/processing.

Dr. Hai Zhang
zhanghai83821@163.com
College of Power and Energy Engineering,
Harbin Engineering University, Harbin, China
Turbomachinery sealing technology
Two-phase flow in turbomachinery
MIPCC technique
Water Ingestion
Wet compression
Spent fuel reprocessing

Dr. D. Ragni
D.Ragni@tudelft.nl
Delft University of Technology, Netherlands
Aerodynamics
Aeroacoustics
Aerospace Engineering
Mechanincal Engineering

Prof. Dr. S. Jeyakumar
sjeyakumar1974@gmail.com
Kalasalingam Academy of Research and Education Krishnankoil, India
High-speed flow mixing and combustion,
Supersonic combustion,
Dual combustion ramjet engine,
Flow diagnostics,
Ramjet and scramjet engine flow analysis,
Aero acoustics,
Performance analysis of jet engines.

Dr. D. Crunteanu
crunti_dani@hotmail.com
Politechnika University of Bucharest, Romania
Gas Dynamics,
Combustion theory and numerical methods,
Combustion with shock waves
Fundamentals of Aero-Thermochemistry
Turbomachinery
Air breathing engines for aircraft,
Advanced mathematics for engineers

Prof. Dr Jun Hashimoto,
hashimoto-jun@oita-u.ac.jp
Faculty of Science and Technology, Oita University, JapanTopics
Premixed Combustion,
non-Premixed Combustion,
Turbulent Combustion
Combustion Characteristics of Conventional and Alternative Fuels

Dr. Ali Dinc,
alidinc@yahoo.com
College of Engineering and Technology,
American University of the Middle East, Kuwait
Jet engines
Unmanned Aerial Vehicles
UAV preliminary design and sizing,
Turbofan, turbojet turboprop engine performances
Gas turbine cycle analysis
NOx emission
Global warming potential
Generic algorithm optimization

Dr. Baofeng Tu
tubaofeng@126.com
College of Energy and Power Engineering,
Nanjing University of Aeronautics and Astronautics
Nanjing, China
Fluid mechanics
Aeroengine aerodynamics
Turbomachinery aerodynamics

Prof. Xinjun Wang
xinjun_wang@outlook.com
Institute of Turbomachinery, Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment, Xian Jiatong University, Xian, China
Turbomachinery
Heat transfer
Fluid dynamics

Prof. Kazhan
kazhank@gmail.com
NAU, Kyiv, Ukraine
Environment Engineering
Civil Engineering
Energy and Environment issue
Entropy Optimization
Airport Environmental Issues
Aircraft Noise
Airport environmental noise mapping and forecasting

Dr. Vivek Sanghi
viveksanghi@hotmail.com
Consultant and Visiting Professor
Bangalore, India
Cycle analyses of aero engines
Thermodynamic modeling and performance prediction (steady state and transient) of aero engines
Modeling engine starting and shut down phases
Novel/Futuristic engine concept and their impact on system performance.
Engine cycle selection/ Engine cycle optimization/Engine-Aircraft performance matching for a given mission application (or for given requirements)
Technology impact forecasting
Analysis of engine test results, fine tuning simulation models to match test results.
Engine health monitoring (condition trend monitoring), fault analysis, diagnostics and prognostics
Real time engine simulations and their use in control system development, testing and verification.
Preliminary design of aero engine/ Engine gas flow path sizing

Prof. Antonio Davis
antonio9davisgmail.com
Int. Institute for Aerospace Engineering and Management, Jain University, Bangalore, India
Aircraft Propulsion,
Heat Transfer,
Computational Fluid Dynamics

Dr. Lei Sun
sunlei1988@buaa.edu.cn
Beijing University of Aeronautics and Astronautics
Gas turbine/Aero engine combustor and combustion
Atomizer
Atomization and spray

Prof. Yepifanov Sergiy
Yepif_khai@ukr.net
Kharkov National Aerospace University, Ukraine
Gas turbines and piston engines theory
Design, strength and dynamics
Cooling system design
Automatic control, diagnostics and health monitoring
Life time analysis

Dr. Cuneyt Uysal
cuneytuysal@karabuk.edu.tr
Karabuk University, Turkey
Thermodynamics
Fluid dynamics
Exergy
Thermoeconomics

Dr. Bin Hu
hubin@iet.cn
Institute of Engineering Thermophysics (IET)
Chinese Academy Sciences (CAS), China P. R.
Fuel atomization
Flame stability
Low NOx combustion

Prof. C. Bibin
umailbibin@gmail.com, drcbibin@gmail.com
RMK College of Engineering and Technology
Thermodynamics,
Combustion,
Turbine and engine design

Dr. Chen Jie
chenj_nuaa@163.com
College of Energy and Power Engineering
Nanjing University of Aeronautics and Astronautics
Compressor Aerodynamic Design,
Mixed-flow Compressor,
Radial Compressor,
Blade Modeling Method

(Deutsch)

Online ISSN: 2191-0332
Print ISSN: 0334-0082
Type: Journal
Language: English
Publisher: De Gruyter
First published: March 1, 1985
Publication Frequency: 4 Issues per Year
Audience: Researchers, engineers, constructors and designers of turbo and jet engines