Article
Mechanics
Jiangchao Zhu, Mauro Madia, Michael Schurig, Bernard Fedelich, Hartmut Schlums, Uwe Zerbst
Summary: Aero-engine turbine disks are critical components that experience high thermal and mechanical stresses. Current part qualification and certification procedures involve spin-tests on production-similar disks. These tests provide reliable information on critical conditions but are costly for engine manufacturers. This study presents two alternative burst speed assessment methods based on the Failure Assessment Diagram (FAD) and a global stability criterion. The methods are compared for the failure modes hoop-burst and rim-peeling using semi-circular surface cracks modeled on the turbine disk's critical regions, demonstrating good agreement in predicting critical rotational speeds.
ENGINEERING FRACTURE MECHANICS
(2023)
Article
Engineering, Aerospace
Fernando Tejero, Robert Christie, David MacManus, Christopher Sheaf
Summary: The challenge of balancing the non-linearity of transonic flow, the 3D nature of geometry and flow field, computational cost, and accuracy in aerodynamic design tasks is further complicated by the need for high degrees of freedom to define geometry and perform 3D computations. By exploring surrogate-based adaptive methods, significant reduction in computational cost can be achieved while identifying an acceptable design space.
AEROSPACE SCIENCE AND TECHNOLOGY
(2021)
Article
Engineering, Aerospace
Andre A. V. Perpignan, Stella Grazia Tomasello, Arvind Gangoli Rao
Summary: Future energy and transport scenarios will continue to rely on gas turbines for energy conversion and propulsion, highlighting the importance of improving gas turbine performance and reducing pollutant emissions. Computational simulations were used to analyze the progression of NOx and CO species through the high-pressure turbine stator, revealing that some relevant reactions continue to occur within the turbine stator. The inclusion of turbulence-chemistry interaction significantly impacts the results, with reactions displaying dependency on residence time rather than flow structures at higher operating pressures and temperatures.
Article
Thermodynamics
Aqiang Lin, Gaowen Liu, Xiangxian Yu, Ran Chang, Qing Feng
Summary: This study comprehensively evaluates complex heat transfer problems in a high-speed rotating turbine disk cavity system, considering multiple factors. The results indicate that the main correlation factors of the system performance are the flowing Reynolds number, rotating Mach number, rotating Reynolds number, specific heat ratio, and wall temperature.
INTERNATIONAL COMMUNICATIONS IN HEAT AND MASS TRANSFER
(2022)
Article
Engineering, Aerospace
Sangjo Kim, Ju Hyun Im, Myungho Kim, Junghoe Kim, You Il Kim
Summary: A diagnostic method using a physics-based model is proposed for engine verification testing. A physics-based engine model is constructed and revised through performance adaptation, and a health parameter is defined to evaluate component performance difference. The proposed method successfully detects abnormalities in the compressor's variable guide vane, secondary air system, and variable area nozzle.
AEROSPACE SCIENCE AND TECHNOLOGY
(2023)
Article
Thermodynamics
Aqiang Lin, Jiale Ma, Guangya Fan, Zhao Lei, Hamza Fawzy, Gaowen Liu
Summary: This study evaluates the influence mechanisms of convective heat transfer in a turbine disk cavity caused by a non-uniform temperature distribution of the rotor disk. The accuracy of a numerical simulation program for turbine disk cavity prediction modelling is verified with experimental data. The results reveal that the non-uniform temperature distribution of the rotor disk affects the Nusselt number and torque coefficient, and is sensitive to thermal performance and marginally sensitive to aerodynamic performance under high rotational speed conditions. The correlation of the Nusselt number is proposed as a comprehensive performance evaluation in the case of the non-uniform temperature distribution effect of a rotor disk. It is primarily influenced by the wall heat dissipation on the rotor disk, adiabatic wall temperature, and wall suction flow rate. These observations provide references for evaluating the complex heat management of turbine disk cavities.
THERMAL SCIENCE AND ENGINEERING PROGRESS
(2023)
Article
Engineering, Aerospace
Cheng Yan, Jianfeng Zhu, Xiuli Shen, Jun Fan, Zhigang Jia, Tiefeng Chen
Summary: This paper investigated the structural design and optimization of vent holes in an industrial turbine sealing disk to reduce stress concentration and improve fatigue life. A novel non-circular vent hole design method, variable dimension sub-model method, and Multi-Island Genetic Algorithm were utilized. The results showed significant improvements in reducing von Mises stress and increasing fatigue life.
CHINESE JOURNAL OF AERONAUTICS
(2021)
Article
Energy & Fuels
Yudong Yang, Aiguo Liu, Xinci Wang, Lei Xi, Wen Zeng
Summary: This paper studies the flow and combustion characteristics of a combustor using vortex plates instead of a swirler. The results show that a nozzle mounted on the flame tube outer wall is better for fuel/air mixing and combustion performance. The cooperation between vortex plates and primary combustion holes is more effective than relying solely on either one. The number of vortex plates affects the shape of the combustor head reverse-flow zone, with an optimal value for optimizing combustion performance.
Article
Engineering, Manufacturing
N. D'Souza, S. Ravichandran, S. Donovan, P. Daum, R. Morrell, Z. Nye, R. J. Lancaster
Summary: A novel approach for down-selection of a repaired support structure design produced using LBP-DED was investigated, with a focus on the role of axial Young's modulus in out-of-plane flexure. Different LBP additive structures were compared to identify the optimum design to counter flattening/un-flattening during service.
ADDITIVE MANUFACTURING
(2022)
Article
Thermodynamics
Huwei Dai, Junhong Zhang, Yanyan Ren, Nuohao Liu, Jiewei Lin
Summary: By introducing different types of cooling holes to reduce the thermal load of thermal barrier coatings in the combustor, it is possible to increase the peak gas temperature and reduce NOx emissions. Decreasing the number of cooling holes has minimal impact on the peak working temperature of thermal barrier coatings, but can lower peak gas temperatures and NOx emissions. Cooling effectiveness is highest for console holes, followed by fan-shaped holes and conical holes.
APPLIED THERMAL ENGINEERING
(2021)
Article
Engineering, Mechanical
Debin Sun, Guoli Ma, Zhenhua Wan, Jinhai Gao
Summary: This study focuses on the creep-fatigue interaction damage failure problem of turbine blades in aeronautical engineering. The creep-fatigue life prediction model of turbine blade material was constructed based on the modified Kachanov-Rabotnov-Chaboche (MKRC) damage mechanics theory, with the experimental verification of nickel-based superalloy DZ125. The creep-fatigue interaction behavior was also investigated. Additionally, a creep-fatigue life prediction model of turbine blade structure was proposed, considering the shape, size, and microscopic defect difference effect. The research results show that creep and fatigue interact with each other in the form of effective stress, and the creep-fatigue life prediction model has a high life prediction ability.
ENGINEERING FAILURE ANALYSIS
(2023)
Article
Engineering, Aerospace
Mingyu Li, Qian Wang, Yuling Zhao, Xuan Dai, Wei Shang
Summary: In this study, a novel staged combustor concept that combines trapped-vortex and swirl combustion characteristics is proposed to achieve high combustion efficiency, low pollutant emissions, and robust stability in aero gas turbine engines. Experimental studies were conducted under atmospheric pressure to investigate the combustion efficiency, pollutant emissions, stability, and flame features of the combustor. The results indicate that improving the air temperature and equivalence ratio enhances combustion efficiency and that pressure drop has a significant influence at lower air temperatures but little influence at higher air temperatures.
AEROSPACE SCIENCE AND TECHNOLOGY
(2023)
Article
Engineering, Mechanical
K. Prabith, I. R. Praveen Krishna
Summary: This paper proposes a numerical method to capture the nonlinear dynamic characteristics of an aero-engine rotor system undergoing multi-disk rub-impact, and studies the steady-state response of the system using model reduction and semi-analytic techniques. It is found that under multi-disk rub-impact, the response characteristics and stability of the system are significantly affected, leading to various types of whirl motions.
INTERNATIONAL JOURNAL OF MECHANICAL SCIENCES
(2022)
Article
Engineering, Aerospace
Xing Yang, Yongqiang Wu, Qiang Zhao, Zhenping Feng
Summary: In this study, a novel endwall modification technique, adding small-scale ribs onto a turbine endwall surface, is proposed to reduce thermal loads on the endwall by enhancing cooling effectiveness. The feasibility of this technique is investigated using computational fluid dynamics (CFD) methods, and comprehensive comparisons are made to evaluate the cooling performance. The results show that the thermal load reduction can be improved by increasing purge air flow ratio, although slight aerodynamic penalty is generated by the introduction of additional vorticities.
AEROSPACE SCIENCE AND TECHNOLOGY
(2022)
Article
Thermodynamics
Hakan Aygun, Onder Turan
Summary: A new methodology is being developed to index the sustainability of aircraft and its power system throughout flight phases, with off-design modeling of exergetic parameters for the turbofan engine using genetic algorithm at the cruise phase. The results show that the genetic algorithm enhances the accuracy of the model compared to the least square method.
Article
Engineering, Aerospace
Andre F. P. Ribeiro, Carlos Ferreira, Damiano Casalino
Summary: This study compares a filament-based free wake panel method to experimental and validated numerical data in order to simulate propeller slipstreams and their interaction with aircraft components. The results show that the free wake panel method is able to successfully capture the slipstream deformation and shearing, making it a useful tool for propeller-wing interaction in preliminary aircraft design.
AEROSPACE SCIENCE AND TECHNOLOGY
(2024)
