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journal: International Journal of Turbo & Jet-Engines

Impact Factor: 0.9

Zeitschrift

International Journal of Turbo & Jet-Engines

Editor-in-Chief: Valery Sherbaum
Herausgegeben von: Vladimir Erenburg

Sprache: Englisch

Erstveröffentlichung: 1. März 1985

Erscheinungsweise: 4 Hefte pro Jahr

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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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Effect of forward swept blade on transonic high pressure ratio centrifugal compressor under different conditions

7. Oktober 2025

Boyu Tian, Qun Zheng, Bin Jiang, Qi Wang, Leichao Tao, Zuoxin Wang

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A transonic centrifugal compressor with high load and high pressure ratio is adopted as the basis of this study. The influence on the internal flow field of high-load centrifugal compressor is studied by forward-swept design of the leading edge of the main blade. Four schemes with different forward sweep angles α (5°, 10°, 15°, 20°) are numerically simulated and comparatively analyzed. By analyzing the performance of the design point, the highest efficiency point and the near-blocking point, the flow law of the internal flow field of the compressor is studied. The results show that the leading edge forward sweep of the main blade has certain advantages in improving the flow capacity and stall margin of the compressor compared with the non-forward sweep reference. Under the design condition, the compressor performance is improved when the forward sweep angle is 10°, in which the efficiency is increased by 0.379 % and the pressure ratio is increased by 1.84 %. In addition, the forward sweep angle shows a consistent improvement in the degree and intensity of low-energy fluid accumulation downstream of the impeller channel under blocking conditions.
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Effect of fin geometry on flow and heat transfer in wedge-shaped ducts: a numerical approach

23. September 2025

Venkatesh Goveraiahgari, Boorneni Suresh, Meenakshi Reddy Reddygari, Mallikarjuna Rao Pabbisetty, Jayasimha Reddy Kodandapuram

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Effective cooling of turbine blade trailing edges requires maximizing heat transfer while minimizing hydraulic losses. Conventional circular pin fins, though widely used, create large wakes and high flow resistance. In contrast, leaf slot pin fins, with streamlined shapes, can reduce wake formation, improve flow mixing, and enhance thermo-hydraulic efficiency. This study numerically analyzes flow and heat transfer in a wedge-shaped trailing edge channel with staggered arrays of circular and leaf slot fins over Reynolds numbers from 10,000 to 80,000, using 12 mm fins. Results show Nusselt number rises with Reynolds number for both cases, with leaf slot fins achieving 3–6 % higher values due to stronger mixing. The friction factor decreases with Reynolds number, but leaf slot fins provide 36–52 % lower losses. Although thermal performance factor declines with Reynolds number, leaf slot fins sustain a 22–35 % advantage. Overall, they offer superior cooling efficiency compared to circular fins.
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Influence mechanism of advance ratio on the aerodynamic performance of a contra-rotating propfan

23. September 2025

Cao Zhiyuan, Gu Qinpeng, Guo Wei, He Xiang, Peng Xuemin, Liu Bo

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Contra-rotating propfan (CRP) emerged in the context of the oil crisis in the 1970s and 1980s. The understanding of the flow mechanism of CRP has been continuously deepened with the research on the three-dimensional (3D) flow and design parameters of CRP. This paper conducts a study on the advance ratio of a CRP and explores its 3D flow characteristics. The results show that increasing the advance ratio can weaken the blade-induced acceleration effect on the flow, the thrust coefficient decrease from 0.9 to 0.31. As the advance ratio increases, the axial induction coefficient decreases, and the acceleration effect and power decrease, the circumferential induction coefficient of the front blade decreases. The circumferential induction coefficient of the rear blade is affected by the incoming flow and fluctuates at different radial positions, affecting the rotational effect of the CRP. The combined effect of these leads to a decrease in the axial vorticity of the tip vortex and the trailing edge vortex.
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Numerical investigation of the effect of self-excited sweeping jet actuator on flow separation in a compressor cascade

11. September 2025

Yanchun Shi, Cong Zeng, Shaowen Chen

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To address the issue of flow separation in an axial compressor cascade, this study explores the application of sweeping jet actuator (SJA) technology for active flow control. An unsteady numerical simulation method is employed to investigate the effect of self-excited jet injection from the blade surface on separation control. The influence of different SJA installation configurations and the resulting flow field characteristics are analyzed and discussed. Additionally, the adaptability of SJA control under various inlet conditions is examined. The results indicate that the self-excited sweeping jet can effectively reduce flow separation losses in the cascade, with a maximum reduction of up to 8.01 %. The SJA demonstrates favorable control performance across a range of inlet Mach numbers and exhibits good adaptability at positive incidence angles. However, at negative incidence, a slight increase in total pressure loss coefficient may occur.
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Numerical investigation of a novel mushroom-shaped cooling hole for enhanced film cooling performance

5. September 2025

Khadidja Boualem, Fatima Ben Ali Kouchih, Abdelhalim Soussa, Abbès Azzi

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The performance of a novel Mushroom-Shaped Cooling Hole (MSCH) configuration intended to improve the efficacy of film cooling in gas turbine components is investigated numerically in this work. Four different MSCH designs were assessed and contrasted with a standard cylindrical hole. The RNG k–ε turbulence model was used in simulations with Reynolds-Averaged Navier–Stokes (RANS) equations for a range of blowing ratios (M = 0.25–1.5). Important performance metrics were examined such as discharge coefficient flow structures and centerline and laterally averaged adiabatic film cooling effectiveness. The findings show that in comparison to the baseline MSCH configurations significantly enhance cooling performance. MSCH-3 and MSCH-4 in particular reduced discharge loss by up to 32 % and improved area-averaged film effectiveness by more than 100 %. Flow visualizations demonstrated enhanced lateral coolant spreading and the suppression of vortex pair formation. These results demonstrate how the MSCH can be a useful substitute for conventional film cooling geometries providing turbine airfoils operating under high thermal and aerodynamic loads with better thermal protection.
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Influence of creep on the modern single shaft gas turbine rotor blades durability

29. August 2025

Natalia Smetankina, Serhii Morhun, Oleksii Melnychenko

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The problem of the modern single shaft gas turbine blades durability and creep parameters determination has been studied. The refined mathematical model, taking into account the forced vibration and thermal parameters has been developed. The influence of the forced vibration frequencies has been determined for the most dangerous forced vibration modes from the point of view of blades resonance state entering. It was found that the processes of cyclic creep reduce the blades durability and taking into account only the blades fatigue strength parameters for the rotor durability prediction is not enough All calculated results are in good correlation with the experimental data, the divergence is less than 5 %. This indicates high accuracy and adequacy of the developed mathematical model. Received results can be used for the next stage of studies, concerning the rotor crack and fracture destruction problems.
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Vibration suppression design for a turboshaft engine with shared bearing cavity structure

20. August 2025

Gaiqi Li, Zhen Huan Tang, Yu Lu, Jianfang Wang, Xiaowei Jiang, Dongyang Ma

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To develop advanced civil turboshaft engine with long life and high reliability, research on vibration suppression technology was conducted for a turboshaft engine with shared bearing cavity structure. The nonlinear dynamic model of the dual-rotor system with shared bearing cavity was established with nonlinear forces of the supports considered. The presence of vibration coupling in the dual-rotor system with shared bearing cavity structure was found, which would increase the resonance opportunities of the rotor system and might lead to disastrous accidents. The mechanism of coupled vibration was revealed. Then an optimization algorithm was developed to optimize the shared bearing cavity structure. Thus the vibration of the whole engine can be reduced and isolated. After implementing the optimization measures, over 15,000 h bench test and flight tests were conducted successfully. The experimental results demonstrated that the engine’s overall vibration reduction design was reasonable, with vibration levels effectively controlled. During long-duration, multi-condition, and full-speed-range operations, the steady-state vibration amplitudes remained below 12 mm/s, exhibiting stable vibration characteristics and significantly lower than the design requirements for turboshaft engines.
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Turbojet module sizing for integration with turbine-based combined cycle engine

28. Oktober 2025

Rajashankar Subramanian, Narayan Ananthkrishnan, Anurag Sharma, Jaewon Lee, Hyuck-Joon Namkoung

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The turbojet module for a turbine-based combined cycle engine is sized subject to constraints arising from the configuration of its scramjet engine. An existing turbojet engine (TJE) core (compressor, burner, turbine) is scaled for air mass flow rate such that the desired thrust at the handover Mach number is achieved. An aerothermal model for the TJE core is integrated with a supersonic intake and nozzle, which are designed using a method of characteristics code. The intake and nozzle, which are constrained by the ramp angles selected for the scramjet module, are managed by appropriate use of splitter plates. The TJE module is sized by scaling the engine core with matching intake and nozzle designs in an iterative manner until the process converges to an acceptable value of handover thrust. A single operating point at the handover Mach could be found that met the thrust requirement while satisfying the constraints.
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A hybrid onboard model for aero-engine direct thrust predictive control

25. November 2025

Qiangang Zheng, Wei Liu, Fangze Sun, Liangliang Li, Dewei Xiang, Haibo Zhang

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Direct thrust control can markedly enhance thrust regulation accuracy and unlock the full performance potential of aero-engines. To improve both real-time capability and precision, we propose a hybrid adaptive onboard predictive modeling framework, termed DNN-PSM-SVM. In this approach, a deep neural network captures strong nonlinearities to refine accuracy, while steady- and dynamic-deviation models based on PSM and SVM reduce computational complexity. A Kalman filter further enhances adaptability, avoiding heavy nonlinear calculations and significantly improving real-time performance. Leveraging this model within a predictive control scheme, unmeasurable parameters such as thrust and surge margin are estimated in real-time, enabling accurate thrust control even under component degradation. Simulation results show that the method outperforms conventional predictive control, achieving steady-state accuracy below 0.06 % and improving real-time performance by nearly an order of magnitude. Unlike sensor-based control, it maintains precise thrust regulation despite engine degradation.
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A Parametric Investigation of Wake Loss Reduction by using Serrated Trailing Edge in a High-speed Compressor Cascade

12. Dezember 2017

Huaping Liu, Yongchuan Yu, Feipeng Yu, Dongfei Zhang, Huanlong Chen

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The influence of the serration with different widths, angles and spanwise locations on the wake of a high-speed compressor cascade is parametrically investigated by numerical simulation. The effect mechanisms of the serration on the cascade performance are discussed in detail and the potential at the off-design points is also validated. The results show that the momentum inputted by the serration jet and the fluid exchange induced by the dominant jet vortex could reenergize the low energy corner region and weaken the trailing edge shedding vortex. With the upstream shift of the serration valley, the loss reduction and pressure rise are enhanced due to the strengthened jet and counter-rotating vortex pair, whereas the flow turning is reduced by the decreased camber angle and the enhanced jet deflection. The serration at the blade height corresponding to the core of the low energy fluid could perform better for the loss reduction, whereas the serration close to the endwall could obtain higher pressure rise. For the optimal serration located at 12.5 % blade height with a width of 5 mm and an angle of 45 °, the loss is reduced by 8.9 % and the pressure rise is increased by 2.2 %, with the flow turning slightly reduced by 0.93 °
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Experimental investigation on the effect of non-circular ring tab on mixing characteristics of subsonic and underexpanded jets

19. November 2025

Thanigaiarasu Subramanian, Dhamodaran Kamalakannan

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Mixing features and potential core reduction of the jet from nozzle exit may reduce aircraft noise and improve combustion characteristics and thrust vectoring. The mixing enhancement was achieved using a non-circular ring tab in which a single 6-side star ring tab (6SSRT) arrangement with strut is fixed at the nozzle exit instead of the conventional two-tab method. The 6SSRT design creates non-uniform and counter-rotating vortices that lead to improved mass entrainment characteristics, axis switching, and differential jet spread. For nozzle exit Mach values of 0.4, 0.6, and 0.8, axial and radial jet spread is compared to the free jet, with possible core reductions of 40 %, 60 %, and 91.67 %, respectively. Radial plots and Mach contours illustrate that 6SSRT jets decay faster than free jets and flow deviation from the nozzle axis. Experimental results show that 6SSRT promotes jet mixing and shortens the potential core to lower jet noise and thrust vectoring.
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Passive movement characteristics analysis and collision risk assessment of floating ring seals of aero-engine

25. November 2025

Tingxun Hu, Wangqun Deng, Zhenhuan Tang, Jian Li, Weifeng Zhang, Feng Luo

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Research on floating ring seals of an Aero-engine, the equivalent analysis model of the dynamic characteristics was established which considering the dynamic response of the rotor, the sealing clearance, the gas buoyancy of the main sealing surface and the elasticity of the wave spring. Minimum radial distance between the graphite ring component and the rotating ring was evaluated. The results showed that the minimum radial distance of the high-pressure side of the two-stage floating ring seal was 0.027 mm, the minimum radial distance of the low-pressure side of the two-stage floating ring seal was 0.164 mm, and the minimum radial distance of the single-stage floating ring seal was 0.026 mm. The influence of friction coefficient of auxiliary sealing surface, processing error and assembly error of wave spring on the passive movement characteristics of floating ring seal was analyzed.The results showed that the risk of collision between the floating ring seal and the rotating ring was controllable when the auxiliary sealing surface of the floating ring seal has good machining accuracy and lubrication condition.
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Study on the relationship between radial flow and rotating instability characteristics under different axial clearances

2. September 2025

Hefei Li, Bin Jiang, Xinlei Du, Xinyi Ma

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This study investigates the impact of axial gap variation on throughflow characteristics and rotating instability (RI) in axial-flow compressors, focusing on the relationship between radial secondary flow (RSF) and RI behavior. Full-annulus simulations of a 1.5-stage compressor are analyzed using proper orthogonal decomposition (POD) and dynamic mode decomposition (DMD) to extract dominant flow modes. Results show that higher-order modes in the tip region are dominated by frequencies linked to RI and leakage vortex/RSF interactions. The eigenfrequencies are governed by circumferential mode structures and propagation velocities. RSF exhibits consistent modal and frequency characteristics across radial positions. Increasing the axial gap reduces RSF energy and RI frequency energy, corresponding to weaker radial flow intensity and RI perturbations. DMD analysis confirms a positive correlation between RSF frequency and RI energy, highlighting the coupling mechanism. These findings provide new insight into the flow dynamics governing RI and offer guidance for compressor stability improvement.
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Optimization design method for accelerated control law of engine life extension considering combustion chamber outlet temperature distribution

11. August 2025

Wei Liu, Yijing Hu, Qiangang Zheng, Haibo Zhang

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This paper proposes an accelerated optimization control law for extending the service life of aero-engine that takes into account the outlet temperature distribution factor (OTDF) of the combustion chamber. Based on the CFD numerical simulation method, a component-level model of a turbofan engine applicable to the entire flight envelope and all states and capable of real-time representation of the thermal pattern temperature of turbine blades is established. A thermal-mechanical fatigue life model of the high-pressure turbine guide vanes is established. The optimization principle of the accelerated control law for extending life is verified through simulation. The method proposed in this paper reduces the maximum temperature of the hot spot in front of the turbine by 15 K and increases the mechanical fatigue life of the turbine guide vanes by nearly 9.23 %. Compared with the traditional accelerated control law optimization method that does not consider extending life, it further reduces the highest temperature of the hot spot in front of the turbine, and the mechanical fatigue life of the turbine guide vanes increases from 4,793 cycles to 5,422 cycles, an increase of nearly 13.12 %.
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Numerical analysis of the sensitivity of combustion flow characteristics to key parameters in constricted cavity-jet combustor

17. Oktober 2025

Pinghua Yan, Guanlong Ren, Shucheng Yang, Xingxing Wu, Xinglong Hou, Le Tian, Haijun Sun

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Modern aero-engine and gas-turbine development imposes ever-higher demands on combustor performance. Among various combustor designs, the trapped-vortex combustor (TVC) excels in flame stability and pollutant reduction, yet suffers from insufficient heat and mass transfer between the main flow and the cavity. To address this issue, a cavity-jet combined combustor is developed by introducing a cavity structure into the jet-stabilized combustor (JSC). The aim is to preserve vortex stabilization while significantly enhancing mass and energy transfer within the combustor. Building on previous work, this paper further investigates the effects of air jet angle on the combustion flow and NO emission characteristics of a combustor with a cavity through numerical analysis. The results show that in the constricted combustor configuration, as the jet angle increases, the high-temperature zone area in the combustor decreases, while the temperature magnitude and combustion efficiency increase. The minimum NO emission occurs at a jet angle of 30°.
Open Access
Study on Influence of Diameter on Detonation Acoustic Characteristics of Pulse Detonation Engine

2. Juli 2020

Gui-yang Xu, Chun-guang Wang, Yan-fang Zhu, Hong-yan Li, Lun-kun Gong, Jiang-ning Wang

Artikelnummer: 000010151520200003

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The experiment system of pulse detonation engine is set up to investigate on influence of diameter on detonation acoustic characteristic. The research of detonation acoustic characteristic of pulse detonation engine for four different diameters in different angles is carried out. Results from the test show that as the PDE diameter increasing, there are increases in amplitudes of impact noise in all angles, and the growth rate of amplitude of impact noise in the 90° direction is generally greater than that in the 0° direction. The smaller PDE diameter is, the distance of most obvious directivity at 0° turning to most obvious directivity at 30° is shorter. When the distance is shorter, such as 200 mm, the duration of detonation acoustic is increasing with the increase of PDE diameter, however, when the distance is longer, such as 3000 mm, it is just the opposite. The maximum duration of detonation acoustic is appeared in 3000 mm under 30 mm PDE diameter which reaches to 1.44 ms.
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Experimental study of jet-tab method with different tab lengths

10. November 2025

Manikandan Subramaniyan, Asad R. Ahmed, Vijayaraja Kengaiah, Dhamodharan Saravanan

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This study examines the effectiveness of using a tab to create a significant force for altering thrust vectoring. Experiments were conducted in a high-speed jet facility to analyze the pressure distribution on tabs with different X / D ratios of 0.3, 0.5, and 0.7, which directly impact thrust vectoring. The tabs were attached at the nozzle exit. Based on the observed pressure values for these configurations, force calculations were made for nozzles operating at exit Mach numbers of 1.6, 1.8, and 2.0. All tests were performed at a fixed sector angle of 120°. The Experiment results indicate a substantial improvement in effectiveness with longer tabs and higher Mach numbers. Specifically, the force increases as the exit Mach numbers rise. An 8 % increase in force is observed when the Mach number rises from 1.6 to 1.8, followed by a subsequent 3.36 % increase when the Mach number goes from 1.8 to 2. Furthermore, a linear relationship was found between the force on the tab and the X / D ratio. There is a 93 % increase in force when the X / D ratio changes from 0.3 to 0.5 and a 14.5 % increase when it changes from 0.5 to 0.7. The maximum force occurs at Mach 2 with an X / D ratio of 0.7. The utilization of simple tabs for thrust vector control (TVC) is a subject of considerable relevance to the aerospace sector. This technique provides a mechanically simplified and mass-efficient TVC solution, which stands to confer several key benefits. These include increased agility for tactical aircraft, economical attitude control for missiles and rockets, and enhanced handling during critical flight phases such as short take-offs and landings. Consequently, the further development of tab-based TVC could yield substantial improvements in the reliability and performance of next-generation aircraft and spacecraft.
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Effects of Greitzer’s parameter and throttle valve coefficient on stall-surge transition in single-stage axial compressors

5. September 2025

Naima Meskine, Djamila Seba, Mohand Kessal, Mohamed Benghanem

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This study focuses on a single-stage compressor, examining the behavior of surge and rotating stall phenomena in detail. Based on Greitzer’s model, the progression of these instabilities was modeled using a set of four dynamical system equations, solved using the fourth-order Runge–Kutta method. The effects of throttle and Greitzer coefficients denoted respectively as K and B , on these instabilities are analyzed and compared. The principal transition conditions between these two phenomena are discussed.
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A physical-data-driven combined transfer learning method for gas turbine performance estimation

15. August 2025

Ran Ao, Lie Chen, Yunpeng Cao, Yujia Ma, Shuying Li

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Gas turbine performance estimation methods rely on historical data from the same-type gas turbine. However, due to individual differences, this knowledge cannot be directly shared. In this paper, we propose a physical-data-driven combined transfer learning method. This method enables knowledge sharing between a gas turbine with complete washing cycle data and a newly commissioned gas turbine. The physical-driven models are constructed utilizing particle swarm optimization to acquire the labels used for pretraining. A data-driven model is developed through a convolutional neural network that employs labels to extract degradation features. Then, the labels for fine-tuning the network. Historical degradation knowledge is transferred to the newly commissioned gas turbine. Experiments results demonstrate that the accuracy of this method is improved by at least about 25 % compared to other methods. The computation time is reduced by at least about 98 % compared to physical-driven methods. This method enables effective performance estimation of gas turbines.
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A review of life cycle uncertainty factors and modeling methods for aero engine high-pressure compressor

21. November 2025

Jiaxuan Zhang, Jianzhong Sun, Pengfei Tang, Jinchen Nian, Qin Liu

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This review explores life cycle uncertainty factors and modeling methods for aero engine high-pressure compressors (HPC). It examines geometric uncertainties arising from both manufacturing and operational maintenance, highlighting how these affect engine performance. The paper discusses uncertain geometric modeling and multi-level performance computation, focusing on geometric parameterization and coupled performance models. Further, it details uncertainty analysis techniques, including uncertainty quantification (UQ) processes for aero engines and specific UQ methods for HPCs. The review aims to provide a comprehensive understanding of how uncertainties impact the performance, reliability, and life cycle of aero engines, with a particular focus on the high-pressure compressor.
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Reacting flow analysis in scramjet engine: effect of mass flow rate of fuel and flight velocity

17. April 2023

Srinivas Prasad Sanaka, Ramanaiah Kandula, Khyathi Sree Chalamalasetty, Durga Rao Kappala

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The objective of the study is realizing the effect of fuel mass flow rate and flight speed on combustion in scramjet engine. DLR conical strut based scramjet combustor configuration was chosen and simulated the chemical reaction between the air and hydrogen fuel. A slot of size 40 mm × 0.295 mm provided at the center of the strut to injected hydrogen fuel from the rare side in to the downstream flow. ICEM CFD software is used for the generation of structured elements in computational domain for three dimensional flow analyses. Standard k-epsilon turbulence model and species transport equation is used in ANSYS fluent solver. The predicted temperature, velocity distribution along the axial length was compared with the experimental results and validated. The temperature distribution at different Mach numbers and mass flow rate reveals that the peak temperature increased with the flight speed and inlet fuel mass flow rate. The peak temperature noticed at the center of the combustor is around 3500 K at a flight speed of Mach 4. The predicted variation of temperature, pressure, velocity in the combustor and the flow structure for reacting flow facilitate good understanding of the combustion process in scramjet combustor.
Open Access
A Study on the Effect of Angle in Diffused Hole Film Cooling Effectiveness at Different Blowing Ratios

2. Juli 2020

Nishant Gandhi, Suresh Sivan

Artikelnummer: 000010151520190046

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Higher the turbine inlet temperature of a gas turbine, higher will be the efficiency, however the increase in the turbine inlet temperature is limited to the materials and the cooling strategies employed. This article presents a study on the effect of blowing ratio on film cooling effectiveness for a cylindrical hole and a diffused hole at different angles. The analysis was done for blowing ratios of 0.5, 1.0, 1.5 and 2.0 while the angle in the diffused hole was varied as 5°, 10° and 15°. A grid independence study was performed and the simulation was validated. The results of cylindrical and different angles of diffused holes were compared. For a cylindrical hole as well as diffused hole, a blowing ratio of 1.0 was found to have an optimal effectiveness. The diffused hole was found to improve the near hole and downstream effectiveness at higher blowing ratios.
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Computational study on heat transfer augmentation with pencil pin fins and ribbed surfaces in wedge channels

31. Oktober 2025

Venkatesh Goveraiahgari, Prakash Babu Kanakavalli, Meenakshi Reddy Reddygari, Mallikarjuna Rao Pabbisetty, Satish Kumar Vutukur

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Efficient turbine blade cooling is crucial. Conventional ribs improve heat transfer but cause pressure losses. This study introduces pencil-shaped pin fins with U- and zigzag-shaped ribs in wedge channels for improved cooling. A numerical study was performed across a Reynolds number range of 10,000–80,000 to assess the influence of U- and zigzag-shaped ribs with pencil pin fins on heat transfer, flow behavior, and pressure drop in a wedge-shaped channel. Zigzag ribs enhanced the Nusselt number by 14–21 %, while U-shaped ribs showed 12–18 % improvement over pencil pin fins, due to boundary layer disruption and secondary vortex formation. Zigzag ribs generated stronger turbulence and more complex flow, resulting in superior heat transfer. However, rib inclusion increased pressure losses. U-shaped ribs caused the highest pressure drop (35–63 %), whereas zigzag ribs showed a moderate increase (22–47 %) due to smoother flow redirection. Pencil pin fins maintained minimal flow resistance. Thermal Performance Factor (TPF) analysis revealed that zigzag ribs offered the best balance between heat transfer and pressure drop, with a 3.6–6.6 % improvement, while U-shaped ribs showed only 1.5–1.8 %. Overall, zigzag-shaped ribs provided the most efficient thermal-hydraulic performance.
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Research on real-time improvement method of on-board physical mechanism model of turboshaft engine based on neural network

23. Oktober 2025

Yuan Liu, Zhanheng Sun, Kang Li

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On-board model is the basis of aero-engine advanced control algorithm. Physical mechanism model has high modeling accuracy, but its poor real-time performance limits its on-board application. Iterative solving algorithm is an important factor leading to the poor real-time performance of the physical mechanism model. Therefore, this paper proposes an improved real-time performance method of the on-board physical mechanism model of turboshaft engine based on neural network. This method establishes a solver model of engine flow balance and pressure balance equations based on neural network. It does not need to repeatedly calculate the inlet, compressor and other component models when solving the balance equation, thus improving the real-time performance of the model. Meanwhile, the powerful nonlinear fitting ability of neural network ensures the modeling accuracy. The simulation results show that compared with the conventional physical mechanism model, the calculation time of the proposed method is reduced by 70.8 %. The maximum modeling error of the key performance parameters at the steady-state condition is no more than 0.6 %, the relative error of the key parameters at the ground point is no more than 0.3 % under the large step of fuel and the variable flight altitude, and the relative error of the key parameters at the variable flight speed is no more than 0.2 %. The effectiveness of the proposed method is verified. The maximum modeling error is less than 0.5 %, which verifies the effectiveness of the proposed method.
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Flow field characteristics of isolator with fluidic injection

10. November 2025

Lovaraju Pinnam, Ruby Kurapati, Dakshina Murthy Inturi, Ethirajan Rathakrishnan

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The present work investigates the effect of secondary fluidic injection on the flow-physics of a supersonic stream within an isolator. An isolator with a length-to-height ratio of 4.5 and an entry Mach number of 2 was chosen for this investigation. The experimental investigations were conducted at a nozzle pressure ratio of 4 and at secondary pressure ratios of 0.75, 1, 1.25 and 1.5. The secondary stream was injected at 0.75 times the length of the isolator, from its inlet. It is inferred that the extent of propagation of disturbances increases with secondary pressure ratio. The single-sided injection causes asymmetry between the pressure distributions along the wall of injection and its opposite side.
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A torsional vibration coupling dynamic modeling and analysis method for engine/power transmission systems in coaxial high-speed helicopters

17. Oktober 2025

Shicheng Zhu, Haibo Zhang

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To address the torsional vibration coupling problem in coaxial high-speed helicopters – involving dual rotors, a thrust propeller, power transmission mechanisms, and the engine under multi-source time-domain strong excitations with high and low rotor speeds – this paper proposes a dynamic modeling and analysis method based on the RK4 (Runge-Kutta fourth-order) method for the engine/power transmission system. The torsional vibration signals calculated by the model are further processed via Fourier transform to analyze the system’s natural frequency characteristics. Numerical simulation results demonstrate that the maximum relative error between the first four natural frequencies calculated by the model and reference values is 3.51 %, validating the model’s high reliability. Under high rotor speed conditions, the contributions of the 1st & 2nd, 3rd, and 4th natural frequency components in the power turbine speed signal reach 35.94 %, 14.09 %, and 11.38 %, respectively. In low rotor speed mode, these proportions are 39.84 %, 10.12 %, and 8.72 %, respectively.
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Performance study of bypass dual throat nozzle based on numerical simulation

21. November 2025

Xiaodong Liu

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This study investigates the aerodynamic performance of elliptical cross-section bypass double-throat nozzles (BDTNs) with varying short-to-long axis ratios (b/a = 1.0, 0.8, 0.6, 0.4), using an axisymmetric BDTN as a reference. Three-dimensional numerical simulations were conducted to analyze flow field structures and performance in both non-vectored and vectored states under fixed inlet conditions (300 K, throat area ratio 1:1.44). The research integrates shaped cross-section design into BDTNs, aiming to improve thrust efficiency and infrared stealth capability. Results show that in the non-vectored state, thrust coefficients peak at NPR = 6, with elliptical BDTNs outperforming axisymmetric ones as b/a decreases. In the vectored state, however, thrust coefficient and vector angle generally decline with smaller b/a. Notably, placing the bypass channel along the short axis markedly enhances vectoring performance: for b/a ≥ 0.6, vector angles exceed 8° and may reach above 20°, while thrust coefficients remain comparable to axisymmetric designs. Oblique secondary flow injection exhibits similar but weaker trends than axial injection. Overall, the b/a = 0.6 configuration offers the best balance between thrust enhancement and flow efficiency. These findings provide new insights into geometric optimization of BDTNs and offer practical guidance for the design of efficient, stealth-capable aero-vector nozzles.
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A high-dimensional and high-precision onboard modeling method for adaptive variable cycle engine

27. November 2025

Qiangang Zheng, Fangze Sun

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Adaptive variable cycle engines, capable of switching seamlessly between subsonic and supersonic modes, have become a central focus in propulsion research. Accurate and real-time onboard models are crucial for predicting performance in flight and supporting advanced functions such as control optimization, health monitoring, and fault-tolerant control. Yet, reconciling accuracy with computational efficiency remains challenging due to the engines’ inherent high dimensionality and strong nonlinearity. Here we present an NN-ΔNN-based modeling framework, where a neural network captures nonlinear dynamics, a ΔNN component represents high-dimensional features, and a Kalman filter enhances adaptability. Simulations show that this approach improves accuracy of key parameters by 0.17–1.6 times compared with NN-PSM across a wide flight envelope. It also achieves rapid thrust-tracking under single- and multi-component degradation within seconds, with low steady-state error, demonstrating strong adaptability and real-time capability.

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Journal Impact Factor	0.9	2024, Journal Citation Reports (Clarivate, 2025)
5-year Journal Impact Factor	0.9	2024, Journal Citation Reports (Clarivate, 2025)
Journal Citation Indicator	0.35	2024, Journal Citation Reports (Clarivate, 2025)
CiteScore	1.9	2024, Scopus (Elsevier B.V., 2025)
SCImago Journal Rank	0.276	2024, SJR (Scimago Lab, 2025; Data Source: Scopus)
Source Normalized Impact per Paper	0.646	2024, CWTS Journal Indicators (CWTS B.V., 2025; Data Source: Scopus)

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

Current Editorial Board Members:

Prof. Ernesto Benini, University of Padova, Italy, ernesto.benini@unipd.it
Prof. Dr. Saeed Farokhi, The University of Kansas, USA, sfarokhi@ku.edu
Prof. Dr. Rama S. R. Gorla, Cleveland State University, USA, r.gorla@yahoo.com
Prof. Changduk Kong, Chosun University, South 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, India Mishra@iitk.ac.il
Dr. R. K. Mishra, The Center for Military Airworthiness and Certification, India, rkmishra.drdo@gmail.com
Prof. Dr. Rishi S. Raj, The City College of New York, USA, raj@ccny.cuny.edu
Prof. Dr. Arvind Rao, Delft University, The Netherlands, 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), China, zhu.s.peng@gmail.com
Prof. Dr. Yasin Sohret, Suleyman Demirel University, 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.

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2191-0332

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0334-0082

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Erstveröffentlichung:

1. März 1985

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eISSN: 2191-0332

ISSN: 0334-0082

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