Journal of Engineering for Gas Turbines and Power最新文献_第4页

Analysis of Unburned Methane Emission Mechanisms in Large-Bore Natural Gas Engines with Prechamber Ignition 带预室点火装置的大口径天然气发动机未燃烧甲烷排放机理分析

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-04-12 DOI: 10.1115/1.4065313

Mark Patterson, Nelson Xie, Kyle Beurlot, Timothy J. Jacobs, Daniel B. Olsen

{"title":"Analysis of Unburned Methane Emission Mechanisms in Large-Bore Natural Gas Engines with Prechamber Ignition","authors":"Mark Patterson, Nelson Xie, Kyle Beurlot, Timothy J. Jacobs, Daniel B. Olsen","doi":"10.1115/1.4065313","DOIUrl":"https://doi.org/10.1115/1.4065313","url":null,"abstract":"\u0000 Although pre-combustion chambers, or prechambers, have long been employed for improving large-bore two-stroke natural gas engine ignition and combustion stability, their design predates modern analysis techniques. Employing the latest CFD modeling techniques, this study investigates the importance of temperature and chemistry for ignition of the main chamber, with an emphasis on eliminating unburned methane. The sensitivity of the ignition and complete combustion to main chamber air/fuel mixture homogeneity was also explored. This study compares the effect of purely thermal ignition, purely chemical ignition, and how their interplay can influence the complete combustion of methane in typical mixtures and in homogeneous distributions of fuel in the combustion chamber. The CFD results demonstrated that temperature and chemistry are equally important in the ignition mechanism, and combining the two phenomena is effective at igniting the main chamber. Reduction of residual methane in the main combustion chamber is most effective when chemical intermediates and thermal ignition are combined. A rudimentary analysis of the effect of fuel/air stratification was also conducted, and it demonstrated that a dramatic reduction in methane emissions is observed for homogeneous mixtures. The flow field in the main combustion chamber was shown to create detrimental stratification of the fuel/air mixture, which inhibited complete combustion of the methane in the main chamber. By contrast, in the extreme case of a perfectly homogeneous distribution of both chemical intermediates and fuel in the combustion chamber, it is possible to completely eliminate unburned methane in the main combustion chamber.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-04-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140709706","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

The Effect of Swirl Number On Lean Blow Out Limits of Lean Direct Injection Combustors 漩涡数对贫油直喷燃烧器吹出极限的影响

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-04-01 DOI: 10.1115/1.4065218

Yogesh Aradhey, Zackary Stroud, Joseph Meadows

{"title":"The Effect of Swirl Number On Lean Blow Out Limits of Lean Direct Injection Combustors","authors":"Yogesh Aradhey, Zackary Stroud, Joseph Meadows","doi":"10.1115/1.4065218","DOIUrl":"https://doi.org/10.1115/1.4065218","url":null,"abstract":"\u0000 This is the first study where a single variable sweep of swirl number (SN) is conducted to assess its impact on lean blowout limits (LBO) in a liquid fueled Lean Direct Injection (LDI) combustor. This study uses a scaled NASA SV-LDI (Swirl Venturi - Lean Direct Injection) hardware and is concerned with the impact of swirl number on the lean blow out limit of a single element LDI system at atmospheric pressure. The SN was varied from 0.31 to 0.66 using continuously variable active SN control system that was developed in-house. It is shown that the minimum operating equivalence ratio is a linearly increasing function of swirl number. While previous literature agrees with the positive slope for this correlation, past work has insisted that the LBO limit is proportional to the swirler vane angle of swirl cup flame holders which is shown to be untrue for LDI systems. By actively varying the swirl number, it is proven that LBO is proportional to SN, and it is well known that SN is not proportional to swirler vane angle. Increased SN reduces LBO margin because the better-mixed, high swirl cases dilute locally rich pockets of fuel air mixture. In addition to a baseline venturi, which was scaled from NASA's geometry, two other venturis were tested. A low pressure loss venturi with a large throat diameter showed poor blow out performance where as a parabolically profiled venturi improved LBO over the baseline for the same swirl number.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140763902","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

Analysis of In-cylinder Flow in a Small-Bore Spark-Ignition Engine Using Computational Fluid Dynamics Simulations and Zero-Dimensional-Based Modeling 利用计算流体动力学模拟和零维建模分析小排量火花点火发动机的气缸内气流

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-03-26 DOI: 10.1115/1.4065168

Chandra Kumar Chandrakar, Kartheeswaran A, Varunkumar S, Tnc Anand, Mayank Mittal

{"title":"Analysis of In-cylinder Flow in a Small-Bore Spark-Ignition Engine Using Computational Fluid Dynamics Simulations and Zero-Dimensional-Based Modeling","authors":"Chandra Kumar Chandrakar, Kartheeswaran A, Varunkumar S, Tnc Anand, Mayank Mittal","doi":"10.1115/1.4065168","DOIUrl":"https://doi.org/10.1115/1.4065168","url":null,"abstract":"\u0000 The evolution of in-cylinder flow involves small and large-scale structures during the intake and compression strokes, significantly influencing the fuel-air mixing and combustion processes. Extensive research has been conducted to investigate the flow evolution in medium to large-sized engines using laser-based diagnostic methods, computational fluid dynamics (CFD) simulations, and zero-dimensional (0-D) based modeling. However, in the present study, we provide a detailed analysis of the evolution of flow fields in a small-bore spark ignition engine with a displacement volume of 110 cm3. This analysis employs a unique methodology where CFD simulation is performed and validated using measured particle image velocimetry (PIV) data. Subsequently, the validated CFD results are utilized to develop and validate a 0-D-based model as it is computationally more efficient. The validated CFD simulation and 0-D-based model are used to evaluate the quantified strength of the flow fields by calculating the tumble ratio and turbulent kinetic energy (TKE). The streamlines and velocity vectors of the flow fields obtained from CFD simulations are utilized to explain the evolution of these parameters during intake and compression strokes. The study is further extended to analyze the effect of engine speed on the evolution of flow fields. With an increase in engine speed, relatively higher values of tumble ratio and TKE at the end of the compression stroke are observed, which is expected to improve the fuel-air mixing and combustion efficiency.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140380315","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 Multi-Stage Nonlinear Method for Aeroengine Health Parameter Estimation Based on Adjacent Operating Points 基于相邻工作点的多阶段航空发动机健康参数估计非线性方法

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-03-26 DOI: 10.1115/1.4065191

Kai Liu, Quanyong Xu, Jihong Zhu

{"title":"A Multi-Stage Nonlinear Method for Aeroengine Health Parameter Estimation Based on Adjacent Operating Points","authors":"Kai Liu, Quanyong Xu, Jihong Zhu","doi":"10.1115/1.4065191","DOIUrl":"https://doi.org/10.1115/1.4065191","url":null,"abstract":"\u0000 Health parameter estimation is the core of engine Gas Path Analysis (GPA), which is widely adopted for engine safety improvement, as well as for operation and maintenance cost reduction. The major challenge of GPA lies in the contradiction between the high dimensions of parameters under estimation, e.g., health parameters, and the limited measurements obtainable from a small number of sensors. Existent GPA methods for health parameters commonly apply dimension reduction before estimation, leading to information loss and hence inaccurate estimation. To tackle the challenge of limited sensor measurements and to have more system outputs than parameters under estimation, we proposed to augment the output vector of the system model by combining the measurements from multiple adjacent operating points. But the engine model can face the problem of homogenization if using data from adjacent operating points. This can in turn leads to a low identifiability of parameters. We analyze the internal mechanism of such large deviation of the parameter estimation results based on linear models and argue for the need of nonlinear method. Hence, we propose a multi-stage nonlinear parameter estimation method for health parameters, combining biased and unbiased estimation. In our extensive simulations based on 10 output measurements of a JT9D engine, our method can estimate 130% more parameters than the widely-used GPA method, while reducing the maximum estimation error of health parameters from 2.2% to 0.1%.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140378148","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

Vibration Characteristics Investigation of Hard-Coated Mistuned Blisk With Multi-Packets By Lumped Parameter Model 用集合参数模型研究多包硬涂层雾化叶盘的振动特性

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-03-21 DOI: 10.1115/1.4065141

Bin Bai, Xiang Li, Xingzhong Zeng, Minghui Yao, Niu Yan, Junfeng Man, Zhiqiang Tao

{"title":"Vibration Characteristics Investigation of Hard-Coated Mistuned Blisk With Multi-Packets By Lumped Parameter Model","authors":"Bin Bai, Xiang Li, Xingzhong Zeng, Minghui Yao, Niu Yan, Junfeng Man, Zhiqiang Tao","doi":"10.1115/1.4065141","DOIUrl":"https://doi.org/10.1115/1.4065141","url":null,"abstract":"\u0000 To improve the performance and reduce the vibration of the mistuned blisk, a novel approach combining the hard-coating and multi-packets is presented. Firstly, the dynamical models of the blisk without hard-coating and multi-packets, the hard-coated mistuned blisk without multi-packets, and the hard-coated mistuned blisk with multi-packets, are established based on the lumped parameter model (LPM). Then, the solved results are compared with that of previous literature to validate the feasibility and correctness of the proposed models. Furthermore, the characteristics of the natural frequencies and the vibration responses for the mistuned blisk are investigated by proposed LPMs. Finally, the effect of the hard-coating and multi-packets on the vibration characteristics for the mistuned blisk are discussed. The obtained results manifest that the vibration response of the mistuned blisk can be further suppressed when the hard-coating and the multi-packets are considered simultaneously compared with only the hard-coating or multi-packets considered, which provides useful guidance on the vibration reduction for the mistuned blisk.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-03-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140223223","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

Simulation Based Thermal Fatigue Validation Test Development for Exhaust Manifold 基于模拟的排气歧管热疲劳验证试验开发

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-03-19 DOI: 10.1115/1.4065112

Ambikapathy Naganathan, Billy G Holland, C. Demirdogen

引用次数: 0

Estimation of Piston Surface Temperature During Engine Transient Operation for Emissions Reduction 估算发动机瞬态运行期间的活塞表面温度以减少排放

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-03-13 DOI: 10.1115/1.4065061

Zhijia Yang, Byron Mason, Brian Wooyeol Bae, Fabrizio Bonatesta, E. Winward, Richard Burke, Ed Chappell

{"title":"Estimation of Piston Surface Temperature During Engine Transient Operation for Emissions Reduction","authors":"Zhijia Yang, Byron Mason, Brian Wooyeol Bae, Fabrizio Bonatesta, E. Winward, Richard Burke, Ed Chappell","doi":"10.1115/1.4065061","DOIUrl":"https://doi.org/10.1115/1.4065061","url":null,"abstract":"\u0000 Piston surface temperature is an important factor in reducing harmful emissions in modern Gasoline Direct Injection engines. In transient operation, the piston surface temperature can change rapidly, increasing the risk of fuel puddling. The prediction of the piston surface temperature provides the means to significantly improve multiple-pulse fuel injection strategies by avoiding fuel puddling. It can also be used to intelligently control the Piston Cooling Jet (PCJ) which are common on modern engines. Considerable research has been undertaken to identify generalized engine heat transfer correlations and to predict piston and cylinder wall surface temperatures during operation. Most of these correlations require in-cylinder combustion pressure as an input, as well as the identification of numerous model parameters, these render such an approach impractical. In this study, the authors have developed a thermodynamic model of piston surface temperature based on the Global Energy Balance (GEB) methodology, which includes the effect of PCJ activation. The advantages are the simple structure, no requirement for in-cylinder pressure data, and only limited experimental tests are needed for model parameter identification. Moreover, the proposed model works well during engine transient operation, with maximum average error of 6.68% during rapid transients. A detailed identification procedure is given. This, and the model performance, have been demonstrated using experimental piston crown surface temperature data from a prototype 1-liter 3-cylinder turbocharged GDI engine, operated in both engine steady-state and transient conditions with an oil jet used for piston cooling turned both on and off.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-03-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140245698","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

Oxygen Storage Incorporated Into Net Power And The Allam-Fetvedt Oxy-Fuel Sco2 Power Cycle - Technoeconomic Analysis 将储氧纳入净发电和 Allam-Fetvedt 纯氧燃料 Sco2 发电循环 - 技术经济分析

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-03-12 DOI: 10.1115/1.4065048

J. J. Moore, Owen Pryor, Ian Cormier, J. Fetvedt

{"title":"Oxygen Storage Incorporated Into Net Power And The Allam-Fetvedt Oxy-Fuel Sco2 Power Cycle - Technoeconomic Analysis","authors":"J. J. Moore, Owen Pryor, Ian Cormier, J. Fetvedt","doi":"10.1115/1.4065048","DOIUrl":"https://doi.org/10.1115/1.4065048","url":null,"abstract":"\u0000 With the planned future reliance on variable renewable energy, the ability to store energy for prolonged time periods will be required to reduce the disruption of market fluctuations. This paper presents a method to analyze a hybrid liquid-oxygen (LOx) storage / direct-fired sCO2 power cycle and optimize the economic performance over a diverse range of scenarios. The system utilizes a modified version of the NET Power process to produce energy when energy demand exceeds the supply while displacing much of the cost of the ASU energy requirements through cryogenic storage of oxygen. The model uses marginal cost of energy data to determine the optimal times to charge and discharge the system over a given scenario. The model then applies ramp rates and other time-dependent factors to generate an economic model for the system without storage considerations. The size of the storage system is then applied to create a realistic model of the plant operation. From the real plant operation model, the amount of energy charged and discharged, the CAPEX of each system, energy costs and revenue and other parameters can be calculated. The economic parameters are then combined to calculate the net present value (NPV) of the system for the given scenario. The model was then run through the SMPSO genetic algorithm in Python for a variety of geographic regions and large-scale scenarios (high solar penetration) to maximize the NPV based on multiple parameters for each subsystem. The LOx storage requirements will also be discussed.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-03-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140250394","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

Comprehensive Flow Path Design Method for the Adaptive Cycle Engine Considering the Coupling Relation of Multiple Components 考虑多组件耦合关系的自适应循环发动机综合流路设计方法

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-03-12 DOI: 10.1115/1.4065049

Zhewen Xu, Xin Lin, Min Chen, Hailong Tang, Jiyuan Zhang

{"title":"Comprehensive Flow Path Design Method for the Adaptive Cycle Engine Considering the Coupling Relation of Multiple Components","authors":"Zhewen Xu, Xin Lin, Min Chen, Hailong Tang, Jiyuan Zhang","doi":"10.1115/1.4065049","DOIUrl":"https://doi.org/10.1115/1.4065049","url":null,"abstract":"\u0000 The Adaptive Cycle Engine (ACE) has multiple coupled components on the same spool and complex bypass system, which makes it have more complex inter-component coupling relation and hard to coordinate in the flow path design. In this study, the coupling relation of the ACE components and the component reference conditions are analyzed and determined, a multi-component collaborative optimization design method is proposed to enable the quantitative evaluation of flow path design solutions. In this method, two optimization strategies are presented based on the different priorities of the inter-component size coupling parameters, the inter-component aerodynamic coupling parameter and the component performance in the optimization problem. ACE flow path solutions for various feasible design speed combinations are generated automatically considering the component performance and inter-component coupling relation. According to an ACE flow path design case study, the design physical rotational speeds of low-pressure spool (NL,d) and high-pressure spool (NH,d) should be 7000 to 7600 r/min and 10000 to 15000 r/min, respectively. At NH,d=12000 r/min and NL,d=7200 r/min, the high-pressure compression components and the fan components could be designed with the lowest aerodynamic load, respectively. NH,d is the key factor affecting the axial length of ACE. This method can be applied to other gas power plant designs.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-03-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140250675","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

Experimental Investigation on the Aerodynamic Instability Process of a High-Speed Axial-Centrifugal Compressor 高速轴向离心压缩机气动不稳定过程的实验研究

Journal of Engineering for Gas Turbines and Power Pub Date : 2024-03-11 DOI: 10.1115/1.4064624

Jiaan Li, Baotong Wang, Xuedong Zheng, Zhiheng Wang, Xinqian Zheng

{"title":"Experimental Investigation on the Aerodynamic Instability Process of a High-Speed Axial-Centrifugal Compressor","authors":"Jiaan Li, Baotong Wang, Xuedong Zheng, Zhiheng Wang, Xinqian Zheng","doi":"10.1115/1.4064624","DOIUrl":"https://doi.org/10.1115/1.4064624","url":null,"abstract":"\u0000 Aerodynamic instability plays an important role in compressor design and may cause performance degradation and fatigue damage. In this paper, an experimental study on the evolution of aerodynamic instability is carried out on a compressor that combines the performance benefits of an axial stage and centrifugal stage. The spatiotemporal characteristics of unsteady wall pressure were obtained using fast-responding pressure transducers over a range of operating conditions. The results show that the axial stage works on the positive slope of the performance characteristic curve from choke to stall at low-speed operating conditions, and mainly features rotating instability. Rotating stall is also observed in the impeller (IMP) and diffuser passages. At medium-speed operating conditions, the centrifugal stage suffers a high-frequency mild surge, alternating with rotating stall. With the increase in back pressure, the mild surge diminishes, and rotating stall persists. This behavior is similar to a two-regime-surge, which has been reported for centrifugal compressors. At high-speed operating conditions, the compressor directly reaches surge without other instabilities. Further analysis of the spatial pattern of the rotating stall revealed the existence of a high-pressure region near the volute tongue, resulting in obvious pressure distortion along the circumferential direction at the volute inlet. This induced the amplitude difference of stall cells in corresponding diffuser passages. The disturbance caused by stall cells propagates upstream through the blade passage, and the largest pressure disturbance induced by the stall cell propagation appears in a circumferential position 45 deg downstream of the volute tongue at the impeller inlet and the axial stage inlet.","PeriodicalId":508252,"journal":{"name":"Journal of Engineering for Gas Turbines and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2024-03-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140253700","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