Journal of Engineering for Gas Turbines and Power最新文献_第6页

Novel Combustion Instability Diagnosis Method with Upstream Pulsation of Repetitive Laser-Induced Plasmas 利用重复激光诱导等离子体上游脉动的新型燃烧不稳定性诊断方法

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-02-13 DOI: 10.1115/1.4064727

Clémence Rubiella, Ho-June Byun, Youchan Park, Hyungrok Do

{"title":"Novel Combustion Instability Diagnosis Method with Upstream Pulsation of Repetitive Laser-Induced Plasmas","authors":"Clémence Rubiella, Ho-June Byun, Youchan Park, Hyungrok Do","doi":"10.1115/1.4064727","DOIUrl":"https://doi.org/10.1115/1.4064727","url":null,"abstract":"\u0000 In this experimental study, we are presenting the ability of laser-induced plasmas with successive pulsation to identify combustion instabilities (CI) of a premixed lab-scale combustor. An acoustic disturbance equivalent to a shockwave perturbation is generated in the main air supply line of a swirled injector prior to the fuel addition by focusing nanosecond laser pulses of 1.6 W average power at 10 Hz. The shockwaves are attenuated to be strong pressure waves when reaching the combustor and impact the pressure field for short periods. After plasma breakdowns, the system returns back to its original state after 4 ms once the added acoustic energy has been fully dissipated. Given a set geometry, it is observed that the laser-induced breakdown amplifies the characteristic frequency peaks of the combustor system when actuated in cold flow. Furthermore, when applied to reacting flows, the pulsating acoustic perturbations impact the pressure fluctuation in the combustor, e.g., reducing the amplitude of the primary characteristic frequency peak at certain conditions. The identification of the main instability modes thanks to the plasma shockwave provides proof of the potential use of this novel diagnosis strategy in various and complex combustion systems.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-02-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139840239","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Evaluation of Extreme Value Predictions for Unsteady Flow Distortion of Aero-Engine Intakes 航空发动机进气口非稳态流变形的极值预测评估

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-02-13 DOI: 10.1115/1.4064728

Matteo Migliorini, P. Zachos, D. MacManus

引用次数: 0

Novel Combustion Instability Diagnosis Method with Upstream Pulsation of Repetitive Laser-Induced Plasmas 利用重复激光诱导等离子体上游脉动的新型燃烧不稳定性诊断方法

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-02-13 DOI: 10.1115/1.4064727

Clémence Rubiella, Ho-June Byun, Youchan Park, Hyungrok Do

{"title":"Novel Combustion Instability Diagnosis Method with Upstream Pulsation of Repetitive Laser-Induced Plasmas","authors":"Clémence Rubiella, Ho-June Byun, Youchan Park, Hyungrok Do","doi":"10.1115/1.4064727","DOIUrl":"https://doi.org/10.1115/1.4064727","url":null,"abstract":"\u0000 In this experimental study, we are presenting the ability of laser-induced plasmas with successive pulsation to identify combustion instabilities (CI) of a premixed lab-scale combustor. An acoustic disturbance equivalent to a shockwave perturbation is generated in the main air supply line of a swirled injector prior to the fuel addition by focusing nanosecond laser pulses of 1.6 W average power at 10 Hz. The shockwaves are attenuated to be strong pressure waves when reaching the combustor and impact the pressure field for short periods. After plasma breakdowns, the system returns back to its original state after 4 ms once the added acoustic energy has been fully dissipated. Given a set geometry, it is observed that the laser-induced breakdown amplifies the characteristic frequency peaks of the combustor system when actuated in cold flow. Furthermore, when applied to reacting flows, the pulsating acoustic perturbations impact the pressure fluctuation in the combustor, e.g., reducing the amplitude of the primary characteristic frequency peak at certain conditions. The identification of the main instability modes thanks to the plasma shockwave provides proof of the potential use of this novel diagnosis strategy in various and complex combustion systems.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-02-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139780598","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Evaluation of Extreme Value Predictions for Unsteady Flow Distortion of Aero-Engine Intakes 航空发动机进气口非稳态流变形的极值预测评估

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-02-13 DOI: 10.1115/1.4064728

Matteo Migliorini, P. Zachos, D. MacManus

引用次数: 0

Assessment of Machine Learning Wall Modeling Approaches for Large Eddy Simulation of Gas Turbine Film Cooling Flows: An a Priori Study 评估用于燃气轮机薄膜冷却流大涡模拟的机器学习壁面建模方法：先验研究

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-01-25 DOI: 10.1115/1.4064556

Tadbhagya Kumar, Pinaki Pal, Sicong Wu, Austin Nunno, Opeoluwa Owoyele, Michael Joly, D. Tretiak

{"title":"Assessment of Machine Learning Wall Modeling Approaches for Large Eddy Simulation of Gas Turbine Film Cooling Flows: An a Priori Study","authors":"Tadbhagya Kumar, Pinaki Pal, Sicong Wu, Austin Nunno, Opeoluwa Owoyele, Michael Joly, D. Tretiak","doi":"10.1115/1.4064556","DOIUrl":"https://doi.org/10.1115/1.4064556","url":null,"abstract":"\u0000 In this work, a priori analysis of machine learning strategies is carried out with the goal of data-driven wall modeling for large eddy simulation (LES) of gas turbine film cooling flows. High-fidelity flow datasets are extracted from wall-resolved LES of flow over a flat plate interacting with the coolant flow supplied by a single row of 7-7-7 shaped cooling holes inclined at 30 degrees with the flat plate at different blowing ratios. Light Gradient Boosting Machine is employed as the ML algorithm for the data-driven wall model. Parametric tests are conducted to systematically assess the influence of a wide range of input flow features (velocity components, velocity gradients, pressure gradients, and fluid properties) on the accuracy of the ML wall model with respect to prediction of wall shear stress. In addition, the use of spatial stencil and time delay is also explored within the ML wall modeling framework. It is shown that features associated with gradients of the streamwise and spanwise velocity components have a major impact on the prediction fidelity of wall model, while the effect of gradients of the wall-normal velocity component is found to be negligible. Moreover, adding flow feature information from an x-y-z spatial stencil significantly improves the ML model accuracy and generalizability compared to just using local flow features from the matching location. Overall, best model performance is achieved when both spatial stencil and time delay features are incorporated within the data-driven wall modeling paradigm.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-01-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139597477","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Numerical Analysis of Unsteady Phenomena in a Contra-Rotating Stage Based On the Reduction of Local Entropy Production 基于减少局部熵产生的同向旋转平台非稳态现象数值分析

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-01-25 DOI: 10.1115/1.4064557

Xingyu Jia, Xi Zhang, Qiushuang Yan, Zicheng Zhao

{"title":"Numerical Analysis of Unsteady Phenomena in a Contra-Rotating Stage Based On the Reduction of Local Entropy Production","authors":"Xingyu Jia, Xi Zhang, Qiushuang Yan, Zicheng Zhao","doi":"10.1115/1.4064557","DOIUrl":"https://doi.org/10.1115/1.4064557","url":null,"abstract":"\u0000 The primary purpose of this study is the reduction of local entropy production in a contra-rotating stage. As such, the unsteady flow phenomena and the impact of radial load distribution on these phenomena and local entropy production need to be clarified. In this study, the SBES turbulence model is utilized to capture the vortices in the flow separation zone, and the γ-Reθ transition model is employed to predict the transition phenomenon within the boundary layer. Entropy production rate models suitable for different turbulence models are constructed separately to calculate local entropy production. Vortex visualization is achieved according to the Lambda_ci criterion, and the relative vorticity change rate is used to analyze the components of the tip clearance vortices. The transition phenomenon is analyzed from the perspectives of both the Euler and the Lagrange descriptions. The primary findings can be summarized as follows: The transition begins earlier and progresses more rapidly in the rear rotor. Wake propagation, occurring at double the frequency, entropy production rate within the boundary layer changes in synchrony with the wall shear stress at the same frequency. Additionally, an investigation of the tip clearance vortices concludes that the main structure of the tip clearance vortices coincides with the flow pattern of the high entropy production rate region, and the flow structure related to the high divergence area is essential for considering subsequent optimization with the aim of reducing the entropy production rate.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-01-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139596118","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

A Study On the Oil Film Thickness Between the Lower Rail of Oil Control Ring and Lower Flank of Oil Control Ring Groove of an Engine 关于发动机机油控制环下轨与机油控制环槽下翼之间油膜厚度的研究

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-01-25 DOI: 10.1115/1.4064582

Ken Miura, Akemi Ito, Yuta Nakamura, Rina Yamada, Koichi Nishibe, Miyuki Usui, Naoki Iijima

{"title":"A Study On the Oil Film Thickness Between the Lower Rail of Oil Control Ring and Lower Flank of Oil Control Ring Groove of an Engine","authors":"Ken Miura, Akemi Ito, Yuta Nakamura, Rina Yamada, Koichi Nishibe, Miyuki Usui, Naoki Iijima","doi":"10.1115/1.4064582","DOIUrl":"https://doi.org/10.1115/1.4064582","url":null,"abstract":"\u0000 Lubricating oil consumption (LOC) of engines causes particulate matter in exhaust gas and abnormal combustion like pre-ignition which becomes a serious problem in hydrogen engines. Lubricating oil transports upward into the combustion chamber of an engine via the sliding surface, the gap, and the side and back of a piston ring. The target of this study was clarifying the mechanism of oil flowing between an oil control ring lower flank and the groove which was the first entrance of lubricating oil supplied from the crank shaft. Oil film thickness at the lower flank of the oil control ring was measured by laser induced fluorescence method using optical fibers embedded in the lower flank of the ring groove. The measured oil film thickness was compared with forces acting on the lower rail of three-piece type oil control ring. The oil film thickness change was well explained using those forces and it was found that friction force at the sliding surface and pressure in the ring groove were dominant on the oil film thickness under all operating conditions tested in this study.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-01-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139595631","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

A Phenomenological Thermal Spray Wall Interaction Modeling Framework Applied to A High Temperature Ignition Assistant Device 应用于高温点火辅助装置的现象学热喷涂壁相互作用建模框架

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-01-13 DOI: 10.1115/1.4064481

S. K. Oruganti, Roberto Torelli, Kenneth Kim, Eric Mayhew, Chol-Bum M. Kweon

{"title":"A Phenomenological Thermal Spray Wall Interaction Modeling Framework Applied to A High Temperature Ignition Assistant Device","authors":"S. K. Oruganti, Roberto Torelli, Kenneth Kim, Eric Mayhew, Chol-Bum M. Kweon","doi":"10.1115/1.4064481","DOIUrl":"https://doi.org/10.1115/1.4064481","url":null,"abstract":"\u0000 Airborne compression ignition engines must operate with reliable ignition systems to achieve proper ignition at every cycle, particularly at high altitudes. Glow-plug-based ignition assistant (IA) devices can provide the necessary energy to preheat the fuel and ensure ignitability of the fuel-air mixture. Ignitability of liquid sprays can be facilitated via direct impingement onto the hot IA surface; however, this comes with adverse effects on the IA durability. Therefore, optimizing an IA's design requires detailed understanding of the physics of fuel spray impingement of superheated surfaces. To this end, this work aims to formulate a new phenomenological thermal spray-wall interaction framework for modeling the film boiling-induced heat transfer, atomization, and dispersion of fuel spray droplets impinging onto a superheated IA device. A qualitative comparison of the new phenomenological model is performed against optical experiments from the literature of an F-24 fuel spray injected onto an IA device located 12 mm away from the injector tip. The temperature of the IA was set at 1400 K. The fuel injection pressure was 400 bar, while the ambient gas pressure and temperature were 30 bar and 800 K, respectively. The performance of the phenomenological model is evaluated in comparison with two other state-of-art models from the literature. A qualitative analysis of the different spray and fuel-air mixture characteristics is performed to outline the differences in the predictions offered by the new phenomenological model and the two state-of-art spray-wall interaction models.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-01-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139530681","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

A Deep Learning Approach to Predict In-Cylinder Pressure of a Compression Ignition Engine 预测压燃式发动机缸内压力的深度学习方法

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-01-13 DOI: 10.1115/1.4064480

Rodrigo Ristow Hadlich, J. Loprete, D. Assanis

{"title":"A Deep Learning Approach to Predict In-Cylinder Pressure of a Compression Ignition Engine","authors":"Rodrigo Ristow Hadlich, J. Loprete, D. Assanis","doi":"10.1115/1.4064480","DOIUrl":"https://doi.org/10.1115/1.4064480","url":null,"abstract":"\u0000 As emissions regulations for greenhouse gas emissions become more strict, it is important to increase the efficiency of engines by improving on the design and operation. Current optimization methods involve performing large numbers of experimental investigations on physical engines or making use of detailed Computational Fluid Dynamics modeling efforts to provide visual and statistical insights on in-cylinder behavior. The latter still requires experimental data for model validation. Both of these methods share a common set of problems, that of being monetarily expensive and time consuming. Previous work has proposed an alternative method for engine optimization using machine learning (ML) models and experimental validation data to predict scalar values representing different parameters. With such models developed, one can then quickly iterate on operating conditions to find the point that maximizes an application-dependent reward function. While these ML methods provide information on individual performance parameters, they lack key information of in-cylinder indicators such as cylinder pressure traces and heat release curves that are traditionally used for performance analysis. This work details the process of implement- ing a Multilayer Perceptron (MLP) model capable of accurately predicting crank-angle resolved high-speed in-cylinder pressure using equivalence ratio, fuel injection pressure and injection timing as input features. It was demonstrated that the model was able to approximate engine behavior with mean squared error lower than 0.05 on a 1-55 range in the test set. This approach shows potential for greatly accelerating the optimization process in engine applications.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-01-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139531482","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Oversizing Novel Aircraft Propulsion Systems for Power Redundancy 超大型新型飞机推进系统的功率冗余

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-01-13 DOI: 10.1115/1.4064479

Konstantinos I. Papadopoulos, V. Gkoutzamanis, A. Kalfas

{"title":"Oversizing Novel Aircraft Propulsion Systems for Power Redundancy","authors":"Konstantinos I. Papadopoulos, V. Gkoutzamanis, A. Kalfas","doi":"10.1115/1.4064479","DOIUrl":"https://doi.org/10.1115/1.4064479","url":null,"abstract":"\u0000 This paper expands the one-engine-inoperative conventional oversizing consideration to account for aircraft propulsion systems with multiple energy sources and thrust-generating media. Components in a generic hybrid propulsion system are categorized into power-generation, power-transmission and thrust-generation. For a given architecture, each possible single component failure is simulated to identify elements affected or eliminated by the respective loss of power, through the use of connection matrices. Failures are linked to losses in supplied and propulsive power, creating a list of oversizing factors for all individual components. Each element is oversized according to its corresponding maximum oversizing rate, defining the ideally redundant propulsion system. Case studies for conventional, all-electric and hybrid-electric powertrains highlight the need for balancing the number of components between minimum excess power and increasing the probability of a failure. Additionally, it is shown that asymmetrical configurations should not have major imbalance of power to avoid significant oversizing. The proposed methodology is applied to a 19-passenger, commuter aircraft. Increasing oversizing rate close to ideal leads to lower optimum energy consumption and increases redundancy. However, payload capacity penalties are required, up to 4 passengers for ideal oversizing. Heavier variants without penalties are up to 4% more efficient in terms of energy-per-weight in their carrying capacity against counterparts of the same oversize rate with reduced payload capacity. The proposed method maintains the principles of the conventional oversizing process, and highlights the tradeoffs needed between redundancy and performance in sizing novel propulsion systems.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-01-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139531217","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0