journal: International Journal of Turbo & Jet-Engines

Impact Factor: 0.9

Veröffentlicht seit 1. März 1985

International Journal of Turbo & Jet-Engines

ISSN: 2191-0332

Editor-in-Chief: Valery Sherbaum

Herausgegeben von: Vladimir Erenburg

Über diese Zeitschrift

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

Ihre Vorteile

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

Geschichte

Previously published by Freund Publishing House Ltd.

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Band 40 Heft 3

August 2023

Öffentlich zugänglich 7. August 2023

Frontmatter

Seiten: i-iii

PDF downloaden

12. Februar 2021

Natural frequency analysis of a functionally graded rotor-bearing system with a slant crack subjected to thermal gradients

Arnab Bose, Prabhakar Sathujoda, Giacomo Canale

Seiten: 243-255

Mehr

Abstract

The present work aims to analyze the natural and whirl frequencies of a slant-cracked functionally graded rotor-bearing system using finite element analysis for the flexural vibrations. The functionally graded shaft is modelled using two nodded beam elements formulated using the Timoshenko beam theory. The flexibility matrix of a slant-cracked functionally graded shaft element has been derived using fracture mechanics concepts, which is further used to develop the stiffness matrix of a cracked element. Material properties are temperature and position-dependent and graded in a radial direction following power-law gradation. A Python code has been developed to carry out the complete finite element analysis to determine the Eigenvalues and Eigenvectors of a slant-cracked rotor subjected to different thermal gradients. The analysis investigates and further reveals significant effect of the power-law index and thermal gradients on the local flexibility coefficients of slant-cracked element and whirl natural frequencies of the cracked functionally graded rotor system.

15. Februar 2021

Evaluation of exit pattern factors of an annular aero gas turbine combustor at altitude off-design conditions

Saroj Kumar Muduli, R. K. Mishra, Purna Chandra Mishra

Seiten: 257-263

Mehr

Abstract

This paper presents the experimental results of an annular combustor. A full scale full annular combustion chamber is tested at ground test stand simulating altitude off-design operating conditions. Traversing thermocouple rakes are used to measure temperatures over the entire annulus at combustor exit. The radial temperature profile is found to be a strong function of operating parameters while the circumferential pattern factor is within the design goal. Increase in reference Mach number at these off-design conditions has caused the redial temperature profiles to deviate and increase from the intended profile. These results will be used for benchmarking the computational model. The computational model will be used for detail study of the temperature non-uniformity over the entire flight envelope and also for modification of combustor liner for performance improvement.

12. Februar 2021

Research on quasi-one-dimensional modeling and performance analysis of RBCC propulsion system

Dong Zhang, Feng Cheng, Shuo Tang, Chun-lin Gong, Bin Xu

Seiten: 265-280

Mehr

Abstract

Quasi-one-dimensional model is the most effective way to realize the rapid iterative design of the overall scheme and control system of RBCC aircraft and has become a research hotspot. In the current research, the quasi-one-dimensional model of RBCC propulsion system is simplified. The model does not include physical characteristics such as wall heat transfer, boundary layer change, specific heat ratio change and transonic flow singularity, which makes the accuracy of the model low and cannot adapt to flight control in large airspace. A RBCC model with high accuracy and adaptability to wide-speed fly is established in this paper. Firstly, based on the laws of kinetic energy conservation and energy conservation, the thrust model of ejection mode is established. Secondly, the quasi-one-dimensional flow control equation is deduced, and the physical mechanism models of core flow area, transonic flow, pre-combustion shock train, heat release law and mixing efficiency are established. On this basis, the quasi-one-dimensional flow model of RBCC dual-mode ramjet is established. Thirdly, based on the law of momentum conservation, the mathematical model of rocket mode is deduced, and the thrust model of rocket mode is established. Finally, the accuracy of the quasi-one-dimensional model is verified by CFD numerical simulation and direct-connect experiment. Taking a typical RBCC launch vehicle as an example, the wide-speed performance of the RBCC propulsion system is calculated and analyzed.

15. Februar 2021

Performance characteristics of flow in annular diffuser using CFD

Hardial Singh, Bharat Bhushan Arora

Seiten: 281-291

Mehr

Abstract

An annular diffuser is a critical component of the turbomachinery, and its prime function is to reduce the flow velocity. The current work is carried to study the effect of four different geometrical designs of an annular diffuser using the ANSYS Fluent. The numerical simulations were carried out to examine the effect of fully developed turbulent swirling and non-swirling flow. The flow behavior of the annular diffuser is analyzed at Reynolds number 2.5 × 10 5 . The simulated results reveal pressure recovery improvement at the casing wall with adequate swirl intensity at the diffuser inlet. Swirl intensity suppresses the flow separation on the casing and moves the flow from the hub wall to the casing wall of the annulus region. The results also show that the Equal Hub and Diverging Casing (EHDC) annular diffuser in comparison to other diffusers has a higher static pressure recovery ( C p = 0.76) and a lower total pressure loss coefficient of ( C L = 0.12) at a 17° swirl angle.

14. April 2021

Control-oriented quasi-one dimensional modeling method for scramjet

Zhihua Xi, Yuan Gao, Minglei Liu, Haibo Zhang

Seiten: 293-303

Mehr

Abstract

The scramjet model used in the control system needs to consider both accuracy and real-time requirements. In this paper, a quasi-one dimensional component level model method for scramjet is proposed. Under the premise of meeting the real-time requirement, this modeling method has higher calculation accuracy, and can obtain higher thrust performance without exceeding the limits. In order to improve the calculation accuracy of the scramjet model, the boundary layer correction and the interaction between shock wave and boundary layer are considered in the inlet and isolator modeling process by using reference temperature method. For the scramjet compression components, the inlet and isolator models are simplified based on shock train theory to improve real-time performance. Meanwhile, the combustor model and nozzle model are established and the combustor model is established with the combination of equal area and isothermal based on temperature limitation. Considering the boundary layer correction, the accuracy of the inlet and isolator model is improved by 8.79 and 7.9% respectively. Compared with the equal area combustion mode, the combined combustion mode can get higher thrust. In the C + + simulation environment, the average calculation time of each state point is about 25 ms which meets the real-time requirements.

20. Mai 2021

Effect of rotor–stator rim cavity flow on the turbine

Xingyun Jia, Wenhao Wang, Hongrui Shi, Le Zhang, Lidong He

Seiten: 305-316

Mehr

Abstract

Relative high pressure in the rotor–stator (RS) cavity helps to improve its seal effectiveness. However, every 1% increase in the cavity flow results in a decrease of the stage power of turbine by about 0.32% and a decrease in the aerodynamic efficiency by about 0.33%. With rim cavity flow, the pressure distribution in the suction side of rotor blade domain and the turbine flow structure show obvious circumferential differences, which are caused by the interactions between the RS cavity flow and the mainstream. The flow characteristic in the false externally-induced ingress in rim clearance is proposed for the first time to reveal the flow mechanism in the effect of RS rim cavity flow on the turbine.

20. Mai 2021

An improved aerodynamic performance optimization method of 3-D low Reynolds number rotor blade

Shuyi Zhang, Bo Yang

Seiten: 317-328

Mehr

Abstract

In this paper, an improved aerodynamic performance optimization method for 3-D low Reynolds number (Re) rotor blade is proposed. A conventional optimization procedure of blade is usually divided into three parts, such as the parameterization method, the fitness value evaluation and the optimization algorithm. This work is mainly focused on the first two parts. The parametrization method, Camber-FFD, is presented based on the camber parametrization method and the free-form deformation algorithm (FFD). The shape of 3-D blade is parameterized by the incidence angles and the coordinates of the maximum camber points. The fitness value evaluation has been realized with the help of an adaptive topological back propagation multi-layer forward artificial neural network (BP-MLFANN). During the training of BP-MLFANN, the hybrid particle swarm optimization method combined with the modified very fast simulate annealing algorithm (HPSO-MVFSA) is adopted to determine the neural network topology adaptively. To verify the effectiveness of this aerodynamic optimization method, the aerodynamic performance of a 3-D low-Re blade, such as Blade D900, is optimized, and the results are compared and analyzed based on the experiments and simulations. It is proved that this aerodynamic optimization method is feasible.

26. Mai 2021

Hot gas ingestion in chute rim seal clearance of gas turbine

Xingyun Jia, Huaiyu Dong, Yuzhou Ming, Yue Wu, Lidong He

Seiten: 329-339

Mehr

Abstract

The Reynolds-averaged Navier–Stokes (RANS) solver was used to calculate, using a test rig to verify the accuracy. The interaction mechanism between different sealed cooling air and gas ingestion at the rotor-stator cavity and chute rim clearance has been investigated. Several groups of representative sealed cooling air flow were selected to explore the cooling efficiency, flow characteristics, tangential and radial velocity ratios in the cavity and the pressure potential field characteristics of trailing edge. The conclusions are obtained: the sealed cooling air flow rate has a significant marginal effect on the sealing effect. The gas ingestion behavior under the small sealed cooling air flow belongs to the disc cavity intrusion, and the intrusion and outflow regions at the of rim clearance are obviously divided into the intrusion characteristic section and the outflow characteristic section. The ingestion behavior under large sealed cooling air flow belongs to clearance ingestion, and the intrusion flow is limited to the chute rim clearance position, which cannot be further penetrated into the cavity. At this time, the clearance area and the cavity area become independent, and the gas ingestion characteristics depend more on the internal flow of the clearance and the vortex structure formed.

25. Mai 2021

An improved compact propulsion system model based on batch normalize deep neural network

Juan Fang, Qiangang Zheng, Haibo Zhang, Chongwen Jin

Seiten: 341-350

Mehr

Abstract

Aero-engine on-board steady state model is an important part of many advanced engine control algorithms. In order to build a high accuracy and real-time steady-state onboard model in a large envelope, an ICPSM (improved compact propulsion system model) based on batch normalize neural network is proposed in this paper. Compared with piecewise linearization model and support vector machine model, conventional CPSM which is mainly composed of baseline model and nonlinear sub model has the advantages of high real-time performance and small data storage. However, as the similarity conversion error increases with the distance from the design point, the cumulative error of the conventional baseline model also increases, which makes the model unable to maintain high accuracy in the full envelope. Thus, a high accuracy baseline model in full envelope based on batch normalize neural network is proposed in this paper. The simulation result shows that compared with the conventional compact propulsion system model, the percentage error of parameters of the improved compact propulsion system model based on the batch neural network is reduced by two times, the single step operation time is reduced by 18%, and the data storage of the onboard model is reduced as well.

1. Juni 2021

Study of the vortex chamber and its application for the development of novel measurement and control devices

Inna Levitsky

Seiten: 351-362

Mehr

Abstract

Based on studies of the flow structure in a short cylindrical vortex chamber, the dependence of the flow rate coefficient on its geometric parameters is proposed. It is shown that the liquid flow form in the chamber’s axial vortex the pressure on which surface is corresponds to the pressure of the outflow cavity. These results are used to measure pressure in high-temperature cavities, using a sleeve with a diameter equal to or slightly larger than the diameter of the axial vortex. The sleeve is installed in the vortex chamber, and connects the pressure on its surface to the pressure sensor. The possibility of using a vortex chamber as a damper of pressure fluctuations has been substantiated. The design of the vortex damper and its tests results are presented; these show the possibility of increasing the stabilization time of the outlet pressure more than three-fold. Variants of regulating devices with a vortex chamber, functioning without changing the flow cross-sections, are proposed and the results of their tests are presented. This is achieved either by introducing an obstacle into the chamber cavity or by displacing the axis of the outlet nozzle position.

4. Juni 2021

Effect of equivalence ratio on the detonation noise characteristics of pulse detonation engine

Gui-Yang Xu, Bao-Xing Li, Hong-Yan Li, Yan-Fang Zhu, Yi-Wen Guan, Jian-Xiong Zhang

Seiten: 363-369

Mehr

Abstract

The experimental system of pulse detonation engine (PDE) is set up to investigate the influence of equivalence ratios on detonation noise characteristics. The research results show that as the equivalence ratio increasing, the amplitudes of detonation noise in all angles and locations increase, and the t B also increases simultaneously, while the t A increases first and then decreases. The equivalence ratio also has a great influence on the intensity of the detonation noise signal in the frequency band of 10–100 Hz, which increases firstly and then decreases with the increase of the equivalence ratio, and the maximum value is obtained at equivalence ratio of 1.1. The results are of great significance to study the mechanism of detonation noise and promote the process of the engineering application.

4. Juni 2021

Simulation and analysis of hot plume infrared signature based on SNB model

Yue Zhou, Jie Wu, Liang Li, Qisheng Guo, Xijuan Zhu, Jing Ma

Seiten: 371-377

Mehr

Abstract

Numerical calculation of infrared emission from hot plume is of great significance for flight monitoring and detections. In this paper, the SNB (statistical narrow band) model established with parameters derived from the high-resolution spectral database HITEMP 2010 is used to perform the hot plume infrared signature simulations. Accuracy of the model is examined by the exact LBL (line by line) method, which proves the model’s reliability to predict radiative properties of combustion gases. In the application part, the SNB model is used to analyze infrared signatures of aircraft plumes cruising at different flight altitudes. The results show that cruising at a higher-altitude will obviously reduce the plume infrared emission. Besides, the plume infrared emissive energy mainly concentrates in a special wavenumber interval and can be strongly absorbed by atmosphere.

Ahead-of-Print / Just-Accepted

Ahead-of-Print / Just-Accepted

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Journal Impact Factor	0.9	2022, Journal Citation Reports (Clarivate, 2023)
5-year Journal Impact Factor	1.1	2022, Journal Citation Reports (Clarivate, 2023)
Journal Citation Indicator	0.39	2022, Journal Citation Reports (Clarivate, 2023)
CiteScore	2.4	2022, Scopus (Elsevier B.V., 2023)
SCImago Journal Rank	0.260	2022, SJR (Scimago Lab, 2023; Data Source: Scopus)
Source Normalized Impact per Paper	0.751	2022, CWTS Journal Indicators (CWTS B.V., 2023; Data Source: Scopus)

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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

(English)

Online ISSN: 2191-0332
Print ISSN: 0334-0082
Typ: Zeitschrift
Sprache: Englisch
Verlag: De Gruyter
Erstveröffentlichung: 1. März 1985
Erscheinungsweise: 4 Hefte pro Jahr
Zielgruppe: Researchers, engineers, constructors and designers of turbo and jet engines