International Journal of Turbo & Jet-Engines最新文献_第6页

Frontmatter 头版头条

4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-03-01 DOI: 10.1515/tjj-2023-frontmatter1

引用次数: 0

Supersonic jet mixing in the presence of two annular co-flow streams 两个环形共流存在下的超音速射流混合

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-02-28 DOI: 10.1515/tjj-2022-0048

R. S., P. Vasanthakumar, Aravindh Kumar Suseela Moorthi, E. Rathakrishnan

{"title":"Supersonic jet mixing in the presence of two annular co-flow streams","authors":"R. S., P. Vasanthakumar, Aravindh Kumar Suseela Moorthi, E. Rathakrishnan","doi":"10.1515/tjj-2022-0048","DOIUrl":"https://doi.org/10.1515/tjj-2022-0048","url":null,"abstract":"Abstract The mixing characteristics of a Mach 1.9 jet at three levels of overexpansion, corresponding to nozzle pressure ratio (NPR) 3, 4 and 5, in the presence of a sonic co-flow (secondary flow), which was submerged in a subsonic co-flow (tertiary flow) was studied experimentally. For these NPRs the secondary co-flow is sonic with underexpanded levels and the tertiary flow Mach number was found to be 0.41, 0.71 and 0.85, respectively. The centerline decay results of the primary jet show that the jet mixing is abated by the co-flow, at all levels of expansion. However, in spite of the reduced mixing encountered by the supersonic primary jet, the waves in the jet core are found to be weaker in the presence of co-flows. This may be regarded as an advantage from the shock associated noise point of view, in accordance with Tam’s theory; which states weaker the waves in the core, the lesser is the shock associated noise. The results show that the reduced mixing environment caused by the sonic co-flow alone leads to the jet core elongation of about 20%, 23% and 49%, at NPRs 3, 4 and 5, respectively. The core length of the jet is found to increase by 29%, 46% and 62%, respectively, at NPRs 3, 4 and 5, when both sonic and subsonic co-flow streams are present.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46087389","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

Expanding the choke margin of a mixed flow compressor stage for a micro gas turbine engine 微型燃气涡轮发动机混流压气机级节流裕度的扩大

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-02-22 DOI: 10.1515/tjj-2022-0060

Hano van Eck, S. J. van der Spuy, A. Gannon

引用次数: 0

Prediction of compressor nominal characteristics of a turboprop engine using artificial neural networks for build standard assessment 基于人工神经网络的涡桨发动机压气机标称特性预测

4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-02-21 DOI: 10.1515/tjj-2020-0015

C. Jagadish Babu, Mathews P. Samuel, Antonio Davis, R. K. Mishra

{"title":"Prediction of compressor nominal characteristics of a turboprop engine using artificial neural networks for build standard assessment","authors":"C. Jagadish Babu, Mathews P. Samuel, Antonio Davis, R. K. Mishra","doi":"10.1515/tjj-2020-0015","DOIUrl":"https://doi.org/10.1515/tjj-2020-0015","url":null,"abstract":"Abstract Compressor characteristics of a single spool turboprop engine have been studied in this paper. It has been brought outhow constant power lines in the compressor characteristics of these compressors make them different from others. Constant speed lines and constant power lines have also been highlighted. A novel method of modeling of compressorof a single spool turboprop engine has also been studied in this paper. Application of neural networks in prediction of compressor characteristics has been investigated. Multilayer Perceptron feed forward neural network has been considered with different transfer functions to assess the potential capability of network in extrapolation and interpolation. Effectiveness of prediction with and without engine bleed valve open and anti-ice valve open situations have been assessed. Network Predictionshas been compared with engine test data to assess the accuracy of prediction and to quantify the build variation in the manufacture of engines. Capability of network with limited test data to predict the complete performance has also been assessed and presented in this paper.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"96 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-02-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136389487","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

Integration of a transonic high-pressure turbine with a rotating detonation combustor and a diffuser 带旋转爆轰燃烧室和扩压器的跨音速高压涡轮的集成

4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-02-21 DOI: 10.1515/tjj-2020-0016

Zhe Liu, James Braun, Guillermo Paniagua

{"title":"Integration of a transonic high-pressure turbine with a rotating detonation combustor and a diffuser","authors":"Zhe Liu, James Braun, Guillermo Paniagua","doi":"10.1515/tjj-2020-0016","DOIUrl":"https://doi.org/10.1515/tjj-2020-0016","url":null,"abstract":"Abstract In this paper, a diffuser is used to integrate a transonic high-pressure turbine with a rotating detonation combustor (RDC). The paper focuses on the required design modifications to the turbine endwalls (EW) to enable high efficiency, while preserving the airfoil blade-to-blade geometry. The main challenge is the stator passage unstarting, due to the high inlet Mach number. First of all, steady Reynolds Averaged Navier Stokes simulations were performed to compare the efficiency of turbines with constant-radius EWs to turbines with axisymmetric EWs. A modified EW design prevented the unstarting of the stator passage, enabling a significant gain in performance. Afterward, the influence on the turbine efficiency and damping due to the unsteadiness from the diffuser-like fluctuations of the RDC was evaluated with unsteady Reynolds Averaged Navier Stokes simulations with a mixing plane approach (MPA). Full unsteady simulations were carried out on selected inlet conditions and compared to the mixing plane results. This parametric study provides turbine designers with recommended diffusion rates along the vane EWs. Additionally, we provide guidance on the upstream diffuser design, specifically the required damping and outlet Mach number.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"294 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-02-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135031426","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

Endwall-pulsed blowing of different excitation models to control flow separation on a highly-loaded compressor cascade 不同激励模式的端壁脉冲吹气控制高负荷压气机叶栅流动分离

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-02-16 DOI: 10.1515/tjj-2023-0009

Hongxin Zhang, Jian-Jun Ye, Bo Jin, C. Xu, Guoping Huang

引用次数: 0

Ground effects on the aerodynamics of a wing with slot type distributed propulsion system for VTOL applications 地面效应对垂直起降狭缝式分布式推进系统机翼气动特性的影响

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-02-15 DOI: 10.1515/tjj-2022-0065

Cheng'an Bai, Chao Zhou

{"title":"Ground effects on the aerodynamics of a wing with slot type distributed propulsion system for VTOL applications","authors":"Cheng'an Bai, Chao Zhou","doi":"10.1515/tjj-2022-0065","DOIUrl":"https://doi.org/10.1515/tjj-2022-0065","url":null,"abstract":"Abstract During take-off of a vertical take-off and landing (VTOL) aircraft, ground effects can cause a downward force on the aircraft body and wings. The downward force could substantially reduce the payload of the aircraft, which is undesirable. This paper investigates the ground effects related to VTOL applications with distributed propulsion. A slot jet is used to simulate the distributed propulsion system. A model of a wing with a slot jet placed near the trailing edge of the wing is investigated. The slot jet is almost perpendicular to the ground to provide a vertical thrust. Experimental and numerical methods are used to investigate the aerodynamic performance of this model. Theoretical analysis is carried out to understand the formation mechanism of the low pressure region on the lower surface of the wing, which causes the downward force. The flow physics of the jet inducing ground vortex is investigated. It is found that the convection term in the ground vortex area is the main source of the pressure reduction. Based on the flow mechanism, a redesigned configuration is proposed to reduce the negative effect of the ground vortex. The flow structures such as the tip vortex are also investigated.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-02-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45308044","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

Study of a new effervescent atomizer design 一种新型泡腾雾化器的设计研究

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-02-10 DOI: 10.1515/tjj-2023-0007

I. Levitsky, Nikolay Razoronov

引用次数: 0

Study of a new effervescent atomizer design 一种新型泡腾雾化器的设计研究

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-02-10 DOI: 10.1515/tjeng-2023-0007

I. Levitsky, Nikolay Razoronov

引用次数: 0

A cooled turbine airfoil performance prediction method with two-dimensional CFD computation and loss models 基于二维CFD计算和损失模型的冷却涡轮翼型性能预测方法

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-02-03 DOI: 10.1515/tjj-2022-0044

Xiaodong Zhang, J. Liu, Chen Li

{"title":"A cooled turbine airfoil performance prediction method with two-dimensional CFD computation and loss models","authors":"Xiaodong Zhang, J. Liu, Chen Li","doi":"10.1515/tjj-2022-0044","DOIUrl":"https://doi.org/10.1515/tjj-2022-0044","url":null,"abstract":"Abstract The role of turbine blade cooling and coolants are significant factors in modern gas turbine aerodynamic design. This paper presents an effective and rapid airfoil design method based on CFD computation of the S1 surface and the existing loss correlations. The method can assess the coolant mixing loss by identifying each cooling hole separately and obtain the overall mainflow aerodynamic loss for cooled airfoil. The CFD computation code of the S1 surface is powered by a two-dimensional Euler equation, which is inviscid. Typical Kacker–Okapuu empirical correlations are then used to assess the airfoil friction loss, trailing edge loss, and shock loss. A novel form of the Hartsel model for coolant mixing loss is developed and employed in the CFD codes. In the reformed model, the mixing loss coefficient is directly associated with the blowing ratio and the total pressure/temperature ratio of mainstream-to-coolant, making it more convenient than the original model in the airfoil design process. Based on a transonic turbine vane airfoil, the influences of the film outflow location and outflow Mach number on the coolant mixing loss are investigated using the above prediction method and the cascade blowing test.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-02-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42550019","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