首页 > 最新文献

Journal of Propulsion and Power最新文献

英文 中文
Detailed Performance Studies on a Small Electric-Powered Contra-Rotating Ducted Fan Engine 小型电动对转管道风扇发动机的详细性能研究
IF 1.9 4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-08-25 DOI: 10.2514/1.b39046
Tobias Ebus, M. Dietz, A. Hupfer
Electrical propulsion has been identified as one of the key fields of future research within the aerospace sector. This paper aims to contribute to the ongoing development of small electric-powered ducted fan engines with a thrust in the range of a few hundred newtons. A special emphasis is placed on introducing contra-rotating fans to such engines. Recently, such an innovative contra-rotating engine has been developed and put into operation on a novel test bench. This study intends to take a closer look at the performance of the engine at design speed ratio by means of experimental and numerical investigations. Global performance parameters are analyzed to validate parallel numerical simulations. Results indicate that both experiment and simulation are in good agreement. Moreover, detailed flow studies of the spanwise distribution of relevant parameters are conducted, and results are discussed. From these results, the stall behavior of the stage is identified. Finally, a comprehensive performance map is established with the help of a number of numerical simulations, which reveal a good off-design performance behavior of the engine.
电力推进已被确定为航空航天领域未来研究的关键领域之一。本文旨在为正在进行的推力在几百牛顿范围内的小型电动管道风扇发动机的开发做出贡献。特别强调在这种发动机中引入对转风扇。最近,这样一种创新的对转发动机被开发出来,并在一个新颖的试验台上投入运行。本研究旨在通过实验和数值研究的方式,更深入地研究发动机在设计速比下的性能。分析了全局性能参数,以验证并行数值模拟。结果表明,实验与仿真结果吻合良好。此外,还对相关参数的展向分布进行了详细的流动研究,并对结果进行了讨论。根据这些结果,可以识别阶段的失速行为。最后,在大量数值模拟的帮助下,建立了一个全面的性能图,揭示了发动机良好的非设计性能行为。
{"title":"Detailed Performance Studies on a Small Electric-Powered Contra-Rotating Ducted Fan Engine","authors":"Tobias Ebus, M. Dietz, A. Hupfer","doi":"10.2514/1.b39046","DOIUrl":"https://doi.org/10.2514/1.b39046","url":null,"abstract":"Electrical propulsion has been identified as one of the key fields of future research within the aerospace sector. This paper aims to contribute to the ongoing development of small electric-powered ducted fan engines with a thrust in the range of a few hundred newtons. A special emphasis is placed on introducing contra-rotating fans to such engines. Recently, such an innovative contra-rotating engine has been developed and put into operation on a novel test bench. This study intends to take a closer look at the performance of the engine at design speed ratio by means of experimental and numerical investigations. Global performance parameters are analyzed to validate parallel numerical simulations. Results indicate that both experiment and simulation are in good agreement. Moreover, detailed flow studies of the spanwise distribution of relevant parameters are conducted, and results are discussed. From these results, the stall behavior of the stage is identified. Finally, a comprehensive performance map is established with the help of a number of numerical simulations, which reveal a good off-design performance behavior of the engine.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":" ","pages":""},"PeriodicalIF":1.9,"publicationDate":"2023-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44788649","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Iodine Electric Propulsion System Thrust Validation: From Numerical Modeling to In-Space Testing 碘电力推进系统推力验证:从数值建模到太空测试
IF 1.9 4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-08-24 DOI: 10.2514/1.b39198
Oliver Jia-Richards, T. Lafleur
In this paper, we complete a full-thrust audit of an iodine-based gridded ion thruster. Prior results have demonstrated excellent agreement between indirect and direct laboratory thrust estimates. Here, thrust estimates from numerical modeling, indirect laboratory testing from diagnostic probes and propulsion system telemetry, indirect in-space testing from onboard propulsion system telemetry, and direct in-space testing by analyzing orbital maneuvers are compared to demonstrate consistency between the four methods and complete the thrust audit. Results from recent in-space testing of the iodine-based thruster demonstrate that thrust estimates from all four methods agree to within three standard deviations of uncertainty for the 11 maneuvers studied. This thrust audit represents a critical step toward improving the understanding and technological maturity of iodine-based gridded ion thrusters for future mission applications, and it demonstrates the utility of recently developed in-space thrust inference techniques for analyzing low-thrust maneuvers.
在本文中,我们完成了碘基网格离子推进器的全推力审计。先前的结果表明,间接和直接实验室推力估计之间非常一致。在这里,对数值建模的推力估计、诊断探测器和推进系统遥测的间接实验室测试、机载推进系统遥测进行的间接太空测试以及通过分析轨道机动进行的直接太空测试进行了比较,以证明四种方法之间的一致性,并完成推力审计。碘基推进器最近的太空测试结果表明,所有四种方法的推力估计值在所研究的11种机动的不确定度的三个标准偏差内一致。这次推力审计代表着朝着提高对碘基网格离子推进器的理解和技术成熟度迈出了关键一步,用于未来的任务应用,它证明了最近开发的空间推力推断技术在分析低推力机动方面的实用性。
{"title":"Iodine Electric Propulsion System Thrust Validation: From Numerical Modeling to In-Space Testing","authors":"Oliver Jia-Richards, T. Lafleur","doi":"10.2514/1.b39198","DOIUrl":"https://doi.org/10.2514/1.b39198","url":null,"abstract":"In this paper, we complete a full-thrust audit of an iodine-based gridded ion thruster. Prior results have demonstrated excellent agreement between indirect and direct laboratory thrust estimates. Here, thrust estimates from numerical modeling, indirect laboratory testing from diagnostic probes and propulsion system telemetry, indirect in-space testing from onboard propulsion system telemetry, and direct in-space testing by analyzing orbital maneuvers are compared to demonstrate consistency between the four methods and complete the thrust audit. Results from recent in-space testing of the iodine-based thruster demonstrate that thrust estimates from all four methods agree to within three standard deviations of uncertainty for the 11 maneuvers studied. This thrust audit represents a critical step toward improving the understanding and technological maturity of iodine-based gridded ion thrusters for future mission applications, and it demonstrates the utility of recently developed in-space thrust inference techniques for analyzing low-thrust maneuvers.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":" ","pages":""},"PeriodicalIF":1.9,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49336905","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Numerical and Experimental Study of an Aircraft Igniter Plasma Jet Discharge 飞机点火器等离子体射流放电的数值与实验研究
IF 1.9 4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-08-24 DOI: 10.2514/1.b38815
Yihao Tang, Joo-Heon Kim, Brandon A. Sforzo, R. Scarcelli, V. Raman
The spark discharge of an aircraft plasma jet igniter is studied using high-fidelity numerical simulations and X-ray radiography measurements. The target problem here features the thermal expansion of hot gas introduced by the electric spark within a confined igniter cavity, which eventually evolves into a pulsed jet of a high-temperature kernel. A comprehensive set of models adapted from existing strategies for internal combustion engine spark plug discharge is extended to the target problem, including the modeling of energy deposition, plasma reactions, thermodynamic properties, and heat losses. A series of validation and parameter studies are performed and presented. The kernel size is found to be sensitive to heat losses arising from radiation and hot gas remained within the discharge cavity, rather than heat conduction to the wall in the discharge cavity. Depending on the enforced shape of the post-breakdown electric arc, the spark kernel can be off-centered, tilted, and considerably asymmetric. These features have been previously not considered when studying such igniter configurations and may have a first-order impact on the ignition process. Provided a proper setup of the heat loss models and electric arc shape, the numerical results are quantitatively comparable to the experimental results in terms of the kernel size, shape, and velocity throughout different stages after the spark discharge.
采用高保真度数值模拟和X射线照相测量方法研究了飞机等离子体射流点火器的火花放电。这里的目标问题是由电火花引入的热气体在受限的点火器腔内的热膨胀,最终演变成高温内核的脉冲射流。将一套改编自现有内燃机火花塞放电策略的综合模型扩展到目标问题,包括能量沉积、等离子体反应、热力学性质和热损失的建模。进行了一系列验证和参数研究。发现内核尺寸对由辐射和留在放电腔内的热气引起的热损失敏感,而不是对放电腔内壁的热传导敏感。根据击穿后电弧的强制形状,火花核可能是偏心的、倾斜的和相当不对称的。这些特征以前在研究此类点火器配置时没有考虑过,可能对点火过程产生一阶影响。如果热损失模型和电弧形状设置得当,数值结果在火花放电后不同阶段的核尺寸、形状和速度方面与实验结果具有定量可比性。
{"title":"Numerical and Experimental Study of an Aircraft Igniter Plasma Jet Discharge","authors":"Yihao Tang, Joo-Heon Kim, Brandon A. Sforzo, R. Scarcelli, V. Raman","doi":"10.2514/1.b38815","DOIUrl":"https://doi.org/10.2514/1.b38815","url":null,"abstract":"The spark discharge of an aircraft plasma jet igniter is studied using high-fidelity numerical simulations and X-ray radiography measurements. The target problem here features the thermal expansion of hot gas introduced by the electric spark within a confined igniter cavity, which eventually evolves into a pulsed jet of a high-temperature kernel. A comprehensive set of models adapted from existing strategies for internal combustion engine spark plug discharge is extended to the target problem, including the modeling of energy deposition, plasma reactions, thermodynamic properties, and heat losses. A series of validation and parameter studies are performed and presented. The kernel size is found to be sensitive to heat losses arising from radiation and hot gas remained within the discharge cavity, rather than heat conduction to the wall in the discharge cavity. Depending on the enforced shape of the post-breakdown electric arc, the spark kernel can be off-centered, tilted, and considerably asymmetric. These features have been previously not considered when studying such igniter configurations and may have a first-order impact on the ignition process. Provided a proper setup of the heat loss models and electric arc shape, the numerical results are quantitatively comparable to the experimental results in terms of the kernel size, shape, and velocity throughout different stages after the spark discharge.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":" ","pages":""},"PeriodicalIF":1.9,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43605557","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Liquid Oxygen/Gaseous Methane Single-Element Shear Coaxial Flame Dynamics 液态氧/气态甲烷单元素剪切同轴火焰动力学
IF 1.9 4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-08-11 DOI: 10.2514/1.b39163
M. Roa, D. Talley, R. Munipalli
An experimental study was conducted to visualize the dynamics and spectra of single-element shear coaxial liquid oxygen (LOX)/gaseous methane flames at high but still subcritical pressure for the LOX, and at supercritical temperature for the methane. High-speed shadowgraphs were employed to image and track the flame and jet dynamics close to the liquid oxygen’s post region. High-speed [Formula: see text] and [Formula: see text] chemiluminescence were also simultaneously collected along the same line of sight as the shadowgraphs. The results were compared to previous LOX/hydrogen results using the same injector at the same momentum flux ratios. The initial temperature of the methane was varied between 200 and 300 K. The LOX/methane flames were found to share many features in common with the LOX/hydrogen flames previously studied, but there were notable differences. The spreading rate of the LOX/hydrogen flames was larger than that of LOX/methane flames. The amplitude of the spreading rate fluctuations for hydrogen was also larger, although the relative spreading rate fluctuations normalized by the average spreading rates were about the same. Despite the differences, a wave amplification mechanism found previously to be active for shear coaxial LOX/hydrogen flames was found to also be active for LOX/methane flames. Overall, both the LOX/methane flames and the LOX/hydrogen were both found to be spectrally fairly quiet.
实验研究了单元素剪切同轴液态氧(LOX)/气态甲烷火焰在高但仍为亚临界压力下的动力学和光谱,以及甲烷在超临界温度下的动力学和光谱。采用高速阴影成像技术对靠近液氧后区域的火焰和射流动力学进行成像和跟踪。高速[公式:见文]和[公式:见文]化学发光也同时沿着与阴影图相同的视线采集。将结果与之前使用相同注入器在相同动量通量比下的LOX/氢气结果进行了比较。甲烷的初始温度在200 ~ 300 K之间变化。我们发现液氧/甲烷火焰与之前研究的液氧/氢火焰有许多共同的特征,但也有显著的差异。液氧/氢气火焰的蔓延速度大于液氧/甲烷火焰。氢气的扩散速率波动幅度也较大,但经平均扩散速率归一化后的相对扩散速率波动幅度大致相同。尽管存在差异,但先前发现的对剪切同轴LOX/氢气火焰有效的波放大机制也被发现对LOX/甲烷火焰有效。总的来说,液氧/甲烷火焰和液氧/氢气火焰在光谱上都相当安静。
{"title":"Liquid Oxygen/Gaseous Methane Single-Element Shear Coaxial Flame Dynamics","authors":"M. Roa, D. Talley, R. Munipalli","doi":"10.2514/1.b39163","DOIUrl":"https://doi.org/10.2514/1.b39163","url":null,"abstract":"An experimental study was conducted to visualize the dynamics and spectra of single-element shear coaxial liquid oxygen (LOX)/gaseous methane flames at high but still subcritical pressure for the LOX, and at supercritical temperature for the methane. High-speed shadowgraphs were employed to image and track the flame and jet dynamics close to the liquid oxygen’s post region. High-speed [Formula: see text] and [Formula: see text] chemiluminescence were also simultaneously collected along the same line of sight as the shadowgraphs. The results were compared to previous LOX/hydrogen results using the same injector at the same momentum flux ratios. The initial temperature of the methane was varied between 200 and 300 K. The LOX/methane flames were found to share many features in common with the LOX/hydrogen flames previously studied, but there were notable differences. The spreading rate of the LOX/hydrogen flames was larger than that of LOX/methane flames. The amplitude of the spreading rate fluctuations for hydrogen was also larger, although the relative spreading rate fluctuations normalized by the average spreading rates were about the same. Despite the differences, a wave amplification mechanism found previously to be active for shear coaxial LOX/hydrogen flames was found to also be active for LOX/methane flames. Overall, both the LOX/methane flames and the LOX/hydrogen were both found to be spectrally fairly quiet.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":" ","pages":""},"PeriodicalIF":1.9,"publicationDate":"2023-08-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43251059","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Numerical Modeling to Investigate the Aerodynamics of a Boundary-Layer Ingested Transonic Fan 边界层吸入式跨音速风扇气动特性的数值模拟研究
IF 1.9 4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-08-08 DOI: 10.2514/1.b38963
Ritangshu Giri, M. Turner
Boundary-layer ingested engines have the potential to offer significantly reduced fuel burn, but the fan stage must be designed to run efficiently with a distorted inflow. It must also be able to withstand unsteady aerodynamic loads resulting from a complex nonuniform flowfield. This paper applies different numerical methods for an improved understanding of the aerodynamic interaction between a transonic fan and inlet distortion. A single-stage transonic tail cone thruster fan was designed using both in-house and commercial tools operating in an inlet distortion flowfield. This paper demonstrates that the relevant metrics required to compute the aerodynamic performance of a fan stage in distorted conditions can be reasonably modeled with a few harmonics using the nonlinear harmonic method in a fraction of time in comparison to a full annulus time marching solution. The nonlinear harmonic method also reduces the computational domain, and hence reduces the solution runtime by an order of magnitude. However, it fails to accurately resolve the wake and potential field transfer across the blade rows due to a limited number of harmonics being applied. A detailed aerodynamic description of the unsteady inflow distortion, the interacting blade-row mechanisms, the flow redistribution upstream of the rotor, the distortion transfer across the different blade rows, and the corresponding aerodynamic losses can be analyzed accurately using only a full annulus time-marching method.
边界层吸入式发动机有可能显著减少燃料消耗,但风扇级必须设计为在流入扭曲的情况下高效运行。它还必须能够承受由复杂的非均匀流场产生的非定常空气动力学载荷。本文采用不同的数值方法来更好地理解跨声速风扇和进气道畸变之间的气动相互作用。设计了一个单级跨音速尾锥推力器风扇,使用了在入口畸变流场中运行的内部和商业工具。本文证明,与全环空时间推进解决方案相比,在畸变条件下计算风扇级气动性能所需的相关指标可以在很短的时间内使用非线性谐波方法用少量谐波合理建模。非线性谐波方法还减少了计算域,从而将求解运行时间减少了一个数量级。然而,由于施加的谐波数量有限,它未能准确解决叶片排之间的尾流和势场转移。仅使用全环空时间推进法,就可以准确分析非定常流入畸变、相互作用的叶列机构、转子上游的流量再分配、不同叶列之间的畸变传递以及相应的气动损失的详细气动描述。
{"title":"Numerical Modeling to Investigate the Aerodynamics of a Boundary-Layer Ingested Transonic Fan","authors":"Ritangshu Giri, M. Turner","doi":"10.2514/1.b38963","DOIUrl":"https://doi.org/10.2514/1.b38963","url":null,"abstract":"Boundary-layer ingested engines have the potential to offer significantly reduced fuel burn, but the fan stage must be designed to run efficiently with a distorted inflow. It must also be able to withstand unsteady aerodynamic loads resulting from a complex nonuniform flowfield. This paper applies different numerical methods for an improved understanding of the aerodynamic interaction between a transonic fan and inlet distortion. A single-stage transonic tail cone thruster fan was designed using both in-house and commercial tools operating in an inlet distortion flowfield. This paper demonstrates that the relevant metrics required to compute the aerodynamic performance of a fan stage in distorted conditions can be reasonably modeled with a few harmonics using the nonlinear harmonic method in a fraction of time in comparison to a full annulus time marching solution. The nonlinear harmonic method also reduces the computational domain, and hence reduces the solution runtime by an order of magnitude. However, it fails to accurately resolve the wake and potential field transfer across the blade rows due to a limited number of harmonics being applied. A detailed aerodynamic description of the unsteady inflow distortion, the interacting blade-row mechanisms, the flow redistribution upstream of the rotor, the distortion transfer across the different blade rows, and the corresponding aerodynamic losses can be analyzed accurately using only a full annulus time-marching method.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":" ","pages":""},"PeriodicalIF":1.9,"publicationDate":"2023-08-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45723674","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","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 Aluminum-Based Water Ramjet for Propelling High-Speed Underwater Vehicles 铝基水冲压发动机用于高速水下航行器的试验研究
IF 1.9 4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-08-08 DOI: 10.2514/1.b39133
R. Murugesan, S. Chakravarthy, J. Kandasamy, R. Sarathi
Major challenges in developing and realizing a novel aluminum–water reaction-based water ramjet propulsion system for high-speed underwater vehicles and demonstration of a water-breathing jet propulsion test facility are investigated. Two stages of combustion, propellant grain combustion and subsequent water combustion, with primary combustion products are adopted. High-pressure-molded propellant grains up to 45% of micro–nano ([Formula: see text]) aluminum were prepared and combusted in the primary chamber, which exhibits mild ignition delay, and a residue of 4–6% was retained. Once water is injected into the secondary chamber, the net thrust generation is increased more than twice from the exhaust jet and improves the specific impulse by 40%. The lean fuel conditions in the secondary chamber lead to reduction in combustion propensity, which causes drop in [Formula: see text] efficiency. The ultrafine iron-oxide-catalyzed micro–nano blended propellants marginally improved the propulsive performance than the uncatalyzed compositions. The [Formula: see text] efficiency of the catalyzed propellants was enhanced up to 38.6%. Aluminum agglomeration in primary combustion considerably occurred; apparently, only a fraction of aluminum particles or agglomerates are completely burnt within the secondary chamber, and the remaining aluminum particles are either partially burnt or go unreacted.
研究了开发和实现用于高速水下航行器的新型铝-水反应水冲压发动机推进系统以及水呼吸式喷气发动机推进试验装置的主要挑战。燃烧分为两个阶段,推进剂颗粒燃烧和随后的水燃烧,燃烧产物为初级燃烧产物。制备了高达45%的微纳([公式:见正文])铝的高压成型推进剂颗粒,并在主室中燃烧,主室表现出轻微的点火延迟,并保留了4-6%的残留物。一旦将水注入二次室,排气射流产生的净推力增加了两倍以上,比冲提高了40%。副室中的贫燃料条件导致燃烧倾向降低,从而导致[公式:见正文]效率下降。超细氧化铁催化的微纳混合推进剂比未催化的推进剂略微提高了推进性能。催化推进剂的[公式:见正文]效率提高了38.6%。一次燃烧中出现了明显的铝团聚现象;显然,只有一小部分铝颗粒或团聚体在第二室中完全燃烧,其余的铝颗粒要么部分燃烧,要么未反应。
{"title":"Experimental Investigation on Aluminum-Based Water Ramjet for Propelling High-Speed Underwater Vehicles","authors":"R. Murugesan, S. Chakravarthy, J. Kandasamy, R. Sarathi","doi":"10.2514/1.b39133","DOIUrl":"https://doi.org/10.2514/1.b39133","url":null,"abstract":"Major challenges in developing and realizing a novel aluminum–water reaction-based water ramjet propulsion system for high-speed underwater vehicles and demonstration of a water-breathing jet propulsion test facility are investigated. Two stages of combustion, propellant grain combustion and subsequent water combustion, with primary combustion products are adopted. High-pressure-molded propellant grains up to 45% of micro–nano ([Formula: see text]) aluminum were prepared and combusted in the primary chamber, which exhibits mild ignition delay, and a residue of 4–6% was retained. Once water is injected into the secondary chamber, the net thrust generation is increased more than twice from the exhaust jet and improves the specific impulse by 40%. The lean fuel conditions in the secondary chamber lead to reduction in combustion propensity, which causes drop in [Formula: see text] efficiency. The ultrafine iron-oxide-catalyzed micro–nano blended propellants marginally improved the propulsive performance than the uncatalyzed compositions. The [Formula: see text] efficiency of the catalyzed propellants was enhanced up to 38.6%. Aluminum agglomeration in primary combustion considerably occurred; apparently, only a fraction of aluminum particles or agglomerates are completely burnt within the secondary chamber, and the remaining aluminum particles are either partially burnt or go unreacted.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":" ","pages":""},"PeriodicalIF":1.9,"publicationDate":"2023-08-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45551978","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Parametrical Investigation of Transverse Injection in a Dual-Bell Nozzle During Altitude-Varying Conditions 高度变化条件下双钟形喷嘴横向喷射的参数化研究
IF 1.9 4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-08-02 DOI: 10.2514/1.b39077
Brian Legros, L. Léger, A. Kourta, A. Chpoun, M. Sellam
The dual-bell nozzle (DBN) is a rocket nozzle concept that could provide a substantial payload gain. The present paper focuses on the impact of radial secondary injection on DBN behavior during its ascent and descent in the atmosphere. The influence of the secondary injection settling chamber (cavity) volume is discussed. The positive influence of the cavity volume on the DBN behavior during transition phases has been exposed, and its effects during retransition were shown to be negligible. The use of secondary injection allowed the transition nozzle pressure ratio to be increased by nearly 24%, and the lateral forces were reduced to less than 1% of the nozzle thrust. A first approach regarding secondary injection optimization is finally proposed.
双钟形喷嘴(DBN)是一种火箭喷嘴概念,可以提供可观的有效载荷增益。本文主要研究径向二次喷射对DBN在大气中上升和下降过程的影响。讨论了二次注射沉降室(腔)体积的影响。在转变阶段,空腔体积对DBN行为的积极影响已经暴露出来,而在再转变期间,它的影响被证明是可以忽略不计的。二次喷射的使用使过渡喷嘴的压力比提高了近24%,横向力降低到喷嘴推力的1%以下。最后提出了二次注入优化的第一种方法。
{"title":"Parametrical Investigation of Transverse Injection in a Dual-Bell Nozzle During Altitude-Varying Conditions","authors":"Brian Legros, L. Léger, A. Kourta, A. Chpoun, M. Sellam","doi":"10.2514/1.b39077","DOIUrl":"https://doi.org/10.2514/1.b39077","url":null,"abstract":"The dual-bell nozzle (DBN) is a rocket nozzle concept that could provide a substantial payload gain. The present paper focuses on the impact of radial secondary injection on DBN behavior during its ascent and descent in the atmosphere. The influence of the secondary injection settling chamber (cavity) volume is discussed. The positive influence of the cavity volume on the DBN behavior during transition phases has been exposed, and its effects during retransition were shown to be negligible. The use of secondary injection allowed the transition nozzle pressure ratio to be increased by nearly 24%, and the lateral forces were reduced to less than 1% of the nozzle thrust. A first approach regarding secondary injection optimization is finally proposed.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":" ","pages":""},"PeriodicalIF":1.9,"publicationDate":"2023-08-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42061567","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Dynamic Regulation Process of the Variable-Geometry Power Turbine 变几何动力涡轮机的动态调节过程
IF 1.9 4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-07-30 DOI: 10.2514/1.b39160
Ruiqing Guan, Jie Tian, Changqing Liu, Jinglei Xu
In this paper, the dynamic regulating process of a variable-geometry power turbine is investigated through wind-tunnel experiments. Particle image velocimetry is used to obtain the dynamic evolution of the flowfield in the cascade passage, including two adjustment processes of increasing and decreasing the throat area. During the test, snapshots of the clockwise/counterclockwise rotation of a blade in the range of [Formula: see text] to [Formula: see text] are processed with a piecewise time-averaged method. The results indicate that the macroscopic change in the flowfield structure mainly appears in the wake region and the high-velocity region. In this process, the velocity and flow angle change monotonously with the blade rotation. The change rate of velocity is determined by both the blade position and the dimensionless outlet location [Formula: see text]. The overall change rate of velocity when the blade approaches the design position is higher than that at other positions, and the airflow near the suction surface is more sensitive to the adjustment of the cascade geometry compared with that near the pressure surface. As for the flow angle, the specific value is mainly determined by the blade position, and the variation law is related to the blade rotation speed.
本文通过风洞试验研究了变几何动力涡轮机的动态调节过程。利用粒子图像测速技术获得叶栅通道内流场的动态演化,包括增加和减少喉部面积两个调节过程。在测试过程中,采用分段时间平均法处理[公式:见正文]至[公式:参见正文]范围内叶片顺时针/逆时针旋转的快照。结果表明,流场结构的宏观变化主要出现在尾流区和高速区。在这个过程中,速度和流动角度随着叶片的旋转而单调变化。速度的变化率由叶片位置和无量纲出口位置决定[公式:见正文]。当叶片接近设计位置时,速度的总体变化率高于其他位置,并且与压力面附近相比,吸力面附近的气流对叶栅几何形状的调整更敏感。至于流动角度,具体值主要由叶片位置决定,变化规律与叶片转速有关。
{"title":"Dynamic Regulation Process of the Variable-Geometry Power Turbine","authors":"Ruiqing Guan, Jie Tian, Changqing Liu, Jinglei Xu","doi":"10.2514/1.b39160","DOIUrl":"https://doi.org/10.2514/1.b39160","url":null,"abstract":"In this paper, the dynamic regulating process of a variable-geometry power turbine is investigated through wind-tunnel experiments. Particle image velocimetry is used to obtain the dynamic evolution of the flowfield in the cascade passage, including two adjustment processes of increasing and decreasing the throat area. During the test, snapshots of the clockwise/counterclockwise rotation of a blade in the range of [Formula: see text] to [Formula: see text] are processed with a piecewise time-averaged method. The results indicate that the macroscopic change in the flowfield structure mainly appears in the wake region and the high-velocity region. In this process, the velocity and flow angle change monotonously with the blade rotation. The change rate of velocity is determined by both the blade position and the dimensionless outlet location [Formula: see text]. The overall change rate of velocity when the blade approaches the design position is higher than that at other positions, and the airflow near the suction surface is more sensitive to the adjustment of the cascade geometry compared with that near the pressure surface. As for the flow angle, the specific value is mainly determined by the blade position, and the variation law is related to the blade rotation speed.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":" ","pages":""},"PeriodicalIF":1.9,"publicationDate":"2023-07-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49657762","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Operation and Power Generation of a Disk-Shaped Pressure Gain Combustor 盘式压力增益燃烧器的运行与发电
IF 1.9 4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-07-30 DOI: 10.2514/1.b38777
Xin Huang, P. Chang, Jiun-Ming Li, Chiang Juay Teo, Boo Cheong Khoo
The objective of this experimental study is to evaluate the power generation capability of an ethylene–air disk-shaped pressure gain combustor (DPGC). The main content of this paper focuses on discussing the DPGC testing results, consisting of detonation wave dynamics, power generation, and accompanying combustion instabilities. The experiments can be grouped into two stages. In the first stage, the DPGC was tested under atmospheric back condition. Continuous detonation wave dynamics were evaluated among various testing conditions. Evolution of the detonation wave velocity with respect to changes in the equivalence ratio has been discussed. In the second stage of the experiments, the DPGC was tested with a turbocharger installed. Shaft power extracted by the turbocharger turbine from the DPGC exhaust was used as a metric for evaluating the DPGC power output. During the operation of the DPGC and turbocharger, low- and intermediate-frequency combustion instabilities were observed, which coexisted with the high-frequency component associated with the circumferentially propagating detonation wave. The experimental results suggest that the DPGC shows superiority in compactness relative to conventional combustion power systems. However, more improvements need to be made with regard to overall thermal efficiency in order to achieve the benefits from detonation combustion.
本实验研究的目的是评估乙烯-空气盘形增压燃烧器(DPGC)的发电能力。本文的主要内容是讨论DPGC的测试结果,包括爆震波动力学、发电和伴随的燃烧不稳定性。实验可以分为两个阶段。在第一阶段中,DPGC在大气回流条件下进行了测试。对不同试验条件下的连续爆震波动力学进行了评价。讨论了爆震波速度随当量比变化的演变过程。在实验的第二阶段,DPGC在安装了涡轮增压器的情况下进行了测试。涡轮增压器涡轮从DPGC排气中提取的轴功率被用作评估DPGC功率输出的指标。在DPGC和涡轮增压器的运行过程中,观察到低频和中频燃烧不稳定性,这些不稳定性与周向传播爆震波的高频分量共存。实验结果表明,与传统的燃烧动力系统相比,DPGC在紧凑性方面表现出优势。然而,为了实现爆震燃烧的益处,需要在整体热效率方面进行更多的改进。
{"title":"Operation and Power Generation of a Disk-Shaped Pressure Gain Combustor","authors":"Xin Huang, P. Chang, Jiun-Ming Li, Chiang Juay Teo, Boo Cheong Khoo","doi":"10.2514/1.b38777","DOIUrl":"https://doi.org/10.2514/1.b38777","url":null,"abstract":"The objective of this experimental study is to evaluate the power generation capability of an ethylene–air disk-shaped pressure gain combustor (DPGC). The main content of this paper focuses on discussing the DPGC testing results, consisting of detonation wave dynamics, power generation, and accompanying combustion instabilities. The experiments can be grouped into two stages. In the first stage, the DPGC was tested under atmospheric back condition. Continuous detonation wave dynamics were evaluated among various testing conditions. Evolution of the detonation wave velocity with respect to changes in the equivalence ratio has been discussed. In the second stage of the experiments, the DPGC was tested with a turbocharger installed. Shaft power extracted by the turbocharger turbine from the DPGC exhaust was used as a metric for evaluating the DPGC power output. During the operation of the DPGC and turbocharger, low- and intermediate-frequency combustion instabilities were observed, which coexisted with the high-frequency component associated with the circumferentially propagating detonation wave. The experimental results suggest that the DPGC shows superiority in compactness relative to conventional combustion power systems. However, more improvements need to be made with regard to overall thermal efficiency in order to achieve the benefits from detonation combustion.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":" ","pages":""},"PeriodicalIF":1.9,"publicationDate":"2023-07-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44131115","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Control of Large-Amplitude Combustion Oscillations Using Nanosecond Repetitively Pulsed Plasmas 利用纳秒重复脉冲等离子体控制大振幅燃烧振荡
4区 工程技术 Q2 ENGINEERING, AEROSPACE Pub Date : 2023-07-01 DOI: 10.2514/1.b38883
Santosh J. Shanbhogue, Colin A. Pavan, Drew E. Weibel, Felipe Gomez del Campo, Carmen Guerra-Garcia, Ahmed F. Ghoniem
This paper details the use of nanosecond repetitively pulsed discharges to attenuate combustion instabilities in a 14 kW swirl-stabilized methane/air combustor. The combustor exhibits large-amplitude pressure oscillations ranging from 1 to 4% of the mean pressure during which the flame exhibits bulk motion in each instability cycle, upstream and downstream, as revealed by high-speed chemiluminescence. Control is accomplished with an electrode comprising a pin anode at the centerline of the combustor, allowing a nanosecond spark to be generated in a region spanning close to the flame base, through the shear layers of the swirling flow and ending at the metallic combustor wall. The discharges are generated using 20 kV, 9 kHz pulses; and they correspond to about 120 W of mean power. This results in a suppression of the peak amplitude of the pressure oscillations by a factor of two to four, and 5 dB in the rms value. Using phase-averaged visualizations of the flame with and without plasma, we detail the sequence of flame motion in the course of the instability. With the plasma active, this reveals significant interactions between the flame and the plasma during the suppression. Finally, we present a state-space model of the thermoacoustic system, and we demonstrate open-loop control of the instabilities.
本文详细介绍了使用纳秒重复脉冲放电来减弱14kw旋流稳定甲烷/空气燃烧器的燃烧不稳定性。高速化学发光表明,燃烧室表现出平均压力的1% ~ 4%的大振幅压力振荡,在此期间,火焰在每个不稳定循环中,上游和下游都表现出大块运动。控制是通过一个电极完成的,该电极包括位于燃烧器中心线的一个引脚阳极,允许在靠近火焰基部的区域产生纳秒级的火花,通过旋转流的剪切层,并在金属燃烧器壁上结束。放电使用20kv, 9khz脉冲产生;它们对应的平均功率约为120w。这导致压力振荡的峰值幅度被抑制了2到4倍,有效值为5 dB。利用有等离子体和没有等离子体时火焰的相位平均可视化,我们详细描述了不稳定过程中火焰运动的顺序。随着等离子体的活跃,这揭示了在抑制过程中火焰和等离子体之间的显著相互作用。最后,我们提出了热声系统的状态空间模型,并演示了不稳定性的开环控制。
{"title":"Control of Large-Amplitude Combustion Oscillations Using Nanosecond Repetitively Pulsed Plasmas","authors":"Santosh J. Shanbhogue, Colin A. Pavan, Drew E. Weibel, Felipe Gomez del Campo, Carmen Guerra-Garcia, Ahmed F. Ghoniem","doi":"10.2514/1.b38883","DOIUrl":"https://doi.org/10.2514/1.b38883","url":null,"abstract":"This paper details the use of nanosecond repetitively pulsed discharges to attenuate combustion instabilities in a 14 kW swirl-stabilized methane/air combustor. The combustor exhibits large-amplitude pressure oscillations ranging from 1 to 4% of the mean pressure during which the flame exhibits bulk motion in each instability cycle, upstream and downstream, as revealed by high-speed chemiluminescence. Control is accomplished with an electrode comprising a pin anode at the centerline of the combustor, allowing a nanosecond spark to be generated in a region spanning close to the flame base, through the shear layers of the swirling flow and ending at the metallic combustor wall. The discharges are generated using 20 kV, 9 kHz pulses; and they correspond to about 120 W of mean power. This results in a suppression of the peak amplitude of the pressure oscillations by a factor of two to four, and 5 dB in the rms value. Using phase-averaged visualizations of the flame with and without plasma, we detail the sequence of flame motion in the course of the instability. With the plasma active, this reveals significant interactions between the flame and the plasma during the suppression. Finally, we present a state-space model of the thermoacoustic system, and we demonstrate open-loop control of the instabilities.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136011724","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 1
期刊
Journal of Propulsion and Power
全部 Acc. Chem. Res. ACS Applied Bio Materials ACS Appl. Electron. Mater. ACS Appl. Energy Mater. ACS Appl. Mater. Interfaces ACS Appl. Nano Mater. ACS Appl. Polym. Mater. ACS BIOMATER-SCI ENG ACS Catal. ACS Cent. Sci. ACS Chem. Biol. ACS Chemical Health & Safety ACS Chem. Neurosci. ACS Comb. Sci. ACS Earth Space Chem. ACS Energy Lett. ACS Infect. Dis. ACS Macro Lett. ACS Mater. Lett. ACS Med. Chem. Lett. ACS Nano ACS Omega ACS Photonics ACS Sens. ACS Sustainable Chem. Eng. ACS Synth. Biol. Anal. Chem. BIOCHEMISTRY-US Bioconjugate Chem. BIOMACROMOLECULES Chem. Res. Toxicol. Chem. Rev. Chem. Mater. CRYST GROWTH DES ENERG FUEL Environ. Sci. Technol. Environ. Sci. Technol. Lett. Eur. J. Inorg. Chem. IND ENG CHEM RES Inorg. Chem. J. Agric. Food. Chem. J. Chem. Eng. Data J. Chem. Educ. J. Chem. Inf. Model. J. Chem. Theory Comput. J. Med. Chem. J. Nat. Prod. J PROTEOME RES J. Am. Chem. Soc. LANGMUIR MACROMOLECULES Mol. Pharmaceutics Nano Lett. Org. Lett. ORG PROCESS RES DEV ORGANOMETALLICS J. Org. Chem. J. Phys. Chem. J. Phys. Chem. A J. Phys. Chem. B J. Phys. Chem. C J. Phys. Chem. Lett. Analyst Anal. Methods Biomater. Sci. Catal. Sci. Technol. Chem. Commun. Chem. Soc. Rev. CHEM EDUC RES PRACT CRYSTENGCOMM Dalton Trans. Energy Environ. Sci. ENVIRON SCI-NANO ENVIRON SCI-PROC IMP ENVIRON SCI-WAT RES Faraday Discuss. Food Funct. Green Chem. Inorg. Chem. Front. Integr. Biol. J. Anal. At. Spectrom. J. Mater. Chem. A J. Mater. Chem. B J. Mater. Chem. C Lab Chip Mater. Chem. Front. Mater. Horiz. MEDCHEMCOMM Metallomics Mol. Biosyst. Mol. Syst. Des. Eng. Nanoscale Nanoscale Horiz. Nat. Prod. Rep. New J. Chem. Org. Biomol. Chem. Org. Chem. Front. PHOTOCH PHOTOBIO SCI PCCP Polym. Chem.
×
引用
GB/T 7714-2015
复制
MLA
复制
APA
复制
导出至
BibTeX EndNote RefMan NoteFirst NoteExpress
×
0
微信
客服QQ
Book学术公众号 扫码关注我们
反馈
×
意见反馈
请填写您的意见或建议
请填写您的手机或邮箱
×
提示
您的信息不完整,为了账户安全,请先补充。
现在去补充
×
提示
您因"违规操作"
具体请查看互助需知
我知道了
×
提示
现在去查看 取消
×
提示
确定
Book学术官方微信
Book学术文献互助
Book学术文献互助群
群 号:481959085
Book学术
文献互助 智能选刊 最新文献 互助须知 联系我们:info@booksci.cn
Book学术提供免费学术资源搜索服务,方便国内外学者检索中英文文献。致力于提供最便捷和优质的服务体验。
Copyright © 2023 Book学术 All rights reserved.
ghs 京公网安备 11010802042870号 京ICP备2023020795号-1