International Journal of Turbo & Jet-Engines最新文献_第10页

Unsteady film cooling characteristics of the high-pressure turbine shroud with blade rotation in an aero-engine 航空发动机叶片旋转高压涡轮护罩的非定常膜冷却特性

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-07-11 DOI: 10.1515/tjj-2021-0032

Z. Kou, Zihao Bao, Guang-chao Li, Xunyan Yin

{"title":"Unsteady film cooling characteristics of the high-pressure turbine shroud with blade rotation in an aero-engine","authors":"Z. Kou, Zihao Bao, Guang-chao Li, Xunyan Yin","doi":"10.1515/tjj-2021-0032","DOIUrl":"https://doi.org/10.1515/tjj-2021-0032","url":null,"abstract":"Abstract Three-dimensional unsteady numerical simulations were conducted to investigate the detailed film cooling mechanism of the high-pressure turbine shroud with the first-stage turbine blade and guide vane for an aero-engine under the high-speed rotation of blades and rotor-stator interaction. The slip mesh was used to realize the relative motion between the rotating blade and the stationary turbine shroud. It is found that the coolant jet is alternately influenced by the hot mainstream, tip clearance leakage flow and leakage vortex due to the high rotational speed of blades. The film cooling characteristics of the turbine shroud significantly present an unsteady and periodic flow and heat transfer phenomenon. The insufficient cooling margin for film holes at the upstream of the blade leading edge can occur not only under high blowing ratios due to the coolant jet liftoff, but also at low blowing ratios due to the insufficient coolant flow rate as a result of the high exit pressure. A novel shroud cooling structure with coolant supply by the added throttle chamber is put forward, and expected to provide better thermal protection for the high-pressure turbine shroud near the leading edge of blades with no extra increase in the total mass flow rate of coolant.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-07-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49344481","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

Influence of leading edge point on aerodynamic performance of asymmetric leading edge compressor airfoils 前缘点对非对称前缘压气机翼型气动性能的影响

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-05-27 DOI: 10.1515/tjj-2021-0054

Guanhua Yang, Limin Gao, Haohao Wang, Longrui Chang

引用次数: 2

Gas dynamic analysis of the modern single shaft gas turbine engine flow path 现代单轴燃气轮机流道气体动力学分析

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-05-26 DOI: 10.1515/tjeng-2022-0019

S. Morhun, S. Vilkul

{"title":"Gas dynamic analysis of the modern single shaft gas turbine engine flow path","authors":"S. Morhun, S. Vilkul","doi":"10.1515/tjeng-2022-0019","DOIUrl":"https://doi.org/10.1515/tjeng-2022-0019","url":null,"abstract":"Abstract The paper outlines a finite volumes refined mathematical model of the working gas flow in the flow path of the three stage modern single shaft gas turbine engine that can be used in floating power plants. Such mathematical model based on the finite volumes of hexagonal-type was constructed using the three-dimensional Navier–Stokes equations for the case of viscous working fluid flow. For the problem solution such boundary conditions as “inlet’, “outlet” and “wall” have been used. The calculation is carried out in a non-stationary setting with a time step of 1.5974 × 10−6 s, which corresponds to the angle of rotation of the rotor, relative to the stator, of 0.09°. The total number of time iterations is 350. Also, it was shown that the variation field of pressure on the blades feather surfaces and the gas flow velocity due to rotation are the critical factors, causing the blades vibration. The result was confirmed with the experiment. The obtained results would be used as a base for further investigations of gas flow pressure field on the blades surface, because the gas flow pressure are key factors, causing the rotor forced vibration, and as initial data for their fatigue strength and crack study.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-05-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42158372","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

Aero engine health monitoring, diagnostics and prognostics for condition-based maintenance: an overview 基于状态维护的航空发动机健康监测、诊断和预测:概述

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-05-12 DOI: 10.1515/tjeng-2022-0020

Narahari Rath, R. Mishra, A. Kushari

{"title":"Aero engine health monitoring, diagnostics and prognostics for condition-based maintenance: an overview","authors":"Narahari Rath, R. Mishra, A. Kushari","doi":"10.1515/tjeng-2022-0020","DOIUrl":"https://doi.org/10.1515/tjeng-2022-0020","url":null,"abstract":"Abstract Aero engine performance deterioration highly influences its reliability, availability and life cycle. Predictive maintenance is therefore a key figure within Industry 4.0, which guarantees high availability and reduced downtime thus reduced operational costs for both military and civil engines. This leads to maintenance on demand and needs an effective engine health monitoring system. This paper overviews the work carried out on aero engine health monitoring, diagnostic and prognostic techniques based on gas path performance parameters. The inception of performance monitoring and its evolution over time, techniques used to establish a high-quality data base using engine model performance adaptation, and effects of computationally intelligent techniques on promoting the implementation of engine fault diagnosis are reviewed. Generating dependable information about the health condition of the engine is therefore a requisite for a successful implementation of condition-based maintenance. Based on this study, further research can be attempted to predict residual life of critical components using degradation pattern from aero engine performance data bank which will be an invaluable asset for engine designers as well as for operators.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-05-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47590035","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: 12

Performance enhancement and flow separation control in an S-duct by air injection 空气喷射增强S型管道的性能和流分离控制

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-05-12 DOI: 10.1515/tjj-2021-0063

Xi Gao, Zhiyuan Cao, Xiang Zhang, Fei Zhang, Jing Yang, Bo Liu

{"title":"Performance enhancement and flow separation control in an S-duct by air injection","authors":"Xi Gao, Zhiyuan Cao, Xiang Zhang, Fei Zhang, Jing Yang, Bo Liu","doi":"10.1515/tjj-2021-0063","DOIUrl":"https://doi.org/10.1515/tjj-2021-0063","url":null,"abstract":"Abstract With the purpose of investigating the effect mechanism of injection on flow separation of the S-duct, different single-hole schemes were investigated and compared with double-hole schemes. Results show that, the performance of S-duct can be improved by using injection. The optimal scheme in this study is a double-hole injection scheme with two holes located at the same axial position. Flow separation reduction and a 16.9% reduction of loss coefficient were achieved by injection with an injection coefficient of 0.46% in each hole. The flow mechanisms are that, firstly, high momentum fluid is injected to separated flow by air injection; secondary, high momentum flow is transported to flow near downside wall by injection vortex. The position effect, injection flow rate effect and hole shape effect were also discussed. For double-hole scheme, the scheme with two holes located different axial positions generates a stronger vortex by mixing two injection vortexes and enhances secondary flow. Though the flow separation is reduced, a severe nonuniform flow field at outlet is formed. Due to the less swirling flow achieved at outlet of S-duct by Double-y scheme, it can offer a more uniform flow field for downstream compressor and has a better control effectiveness.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-05-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49652196","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

Heat transfer distribution of single oblique jet impingement in crossflow under different inlet conditions 不同进口条件下单斜射流在横流中的换热分布

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-04-13 DOI: 10.1515/tjeng-2021-0029

Juan He, Qinghua Deng, K. Xiao, Z. Feng

引用次数: 0

Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft 涡轮螺旋桨发动机废气撞击对推进飞机影响的实验与数值研究

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-04-04 DOI: 10.1515/tjj-2022-0011

C. Vinay, Kumar Gottegere Narayanappa, Y. Giridhara Babu

{"title":"Experimental and numerical investigation on the effect of turboprop engine exhaust gas impingement on pusher aircraft","authors":"C. Vinay, Kumar Gottegere Narayanappa, Y. Giridhara Babu","doi":"10.1515/tjj-2022-0011","DOIUrl":"https://doi.org/10.1515/tjj-2022-0011","url":null,"abstract":"Abstract Turboprop engines require an exhaust nozzle or stub to duct the engine exhaust flue gas outboard of the aircraft. The design of these exhaust stubs are dictated primarily by the aircraft’s configuration. In pusher aircraft, the exhaust stubs are designed to minimize the exposure of the flue gases from the engine exhaust on the propeller blades and fuselage. A fluid-thermal-structure coupling analysis is performed to understand the thermal effects of the engine exhaust jet flow on the thermo-mechanical behavior of pusher configured light transport aircraft propeller and structure. The steady thermal flow field of the aircraft with forward and reverse thrust, in which propeller blade angle variations were analyzed for different aircraft speed. The present work investigates a three-dimensional analysis of flow around the nacelle-airframe and the effect of exhaust flue gas impingement on the propeller blade surface. Based on the insights from the numerical results, the designed exhaust duct was integrated on the aircraft and carried out ground static and flight testing for various flight operating conditions in which propeller blade and fuselage surface temperature were measured. Numerical and experimental results are compared and validated for certain flight conditions and found satisfactory.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-04-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46147717","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

Numerical and experimental investigations of tip clearance effects in a high-flow-coefficient centrifugal compressor 大流量系数离心压气机叶顶间隙效应的数值与实验研究

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-03-28 DOI: 10.1515/tjj-2022-0002

Chenxi Zhao, Chang-Hyun Yang, Chenqing Zhang, Xiaotian Zhang, G. Xi

引用次数: 0

Effect of G-type integral squeeze film damper on the dynamic characteristics in rotor system g型整体挤压膜阻尼器对转子系统动态特性的影响

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-03-21 DOI: 10.1515/tjj-2021-0046

Wei Yan, Lidong He, Gang Zhu, Xingyun Jia

{"title":"Effect of G-type integral squeeze film damper on the dynamic characteristics in rotor system","authors":"Wei Yan, Lidong He, Gang Zhu, Xingyun Jia","doi":"10.1515/tjj-2021-0046","DOIUrl":"https://doi.org/10.1515/tjj-2021-0046","url":null,"abstract":"Abstract To solve the problems of the nonlinear damping force in the traditional squeeze film damper (SFD), a novel structure of G-type integral squeeze film damper (GISFD) based on ISFD is proposed for the first time. The finite element model and test rig of the ball bearing-rotor system are established to explore the influence of GISFD and ISFD on the dynamic characteristics of the unbalanced rotor system. The results show that both GISFD and ISFD can change the critical speed of the rotor system, reduce the bending strain energy of the shaft, and reduce the bearing dynamic load of the rotor system. Through comparison, it is found that the effect of GISFD is more obvious. The experimental results show that, compared with the unbalanced rotor system without damper, the peak-peak value of amplitude in the rotor system with GISFD and ISFD at 3000 rpm is reduced by 25.53 and 15.81%. The amplitude in the disk at the first-order critical speed is effectively reduced, and the reduction range reach 52.01 and 35.44%, respectively. GISFD has a more significant effect of suppressing unbalanced vibration, and has superior vibration damping performance when compared with ISFD.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-03-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44308420","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

Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage 微型燃气轮机混流式压缩机级初始设计一维代码的开发

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-03-15 DOI: 10.1515/tjj-2022-0008

Hano van Eck, S. J. van der Spuy, T. von Backström

{"title":"Development of a one-dimensional code for the initial design of a micro gas turbine mixed flow compressor stage","authors":"Hano van Eck, S. J. van der Spuy, T. von Backström","doi":"10.1515/tjj-2022-0008","DOIUrl":"https://doi.org/10.1515/tjj-2022-0008","url":null,"abstract":"Abstract The use of micro gas turbines (MGTs) for once-off and unique applications means that a rapid turnaround design process is required. The development of a MATLAB® application-based program for the initial design and performance analysis of radial and mixed flow compressors is discussed. The program code is based on one dimensional (1D) mean line flow and loss model theory. For verification, 18 test compressors were developed, covering a wide range of design velocities, mass flow rates and meridional exit angles. Predicted performance results were verified using Numeca/FINE™ Turbo software. Initial comparisons between 1D and Computational Fluid Dynamics (CFD) results did not match well. The 1D software over-predicted compressor performance and provided poor choke prediction. Consequently, empirical models to correct these deviations were derived and implemented into the 1D Application code. The updated 1D code provided a mean choke prediction difference of 1.59% compared to an initial 14.98% difference at the design point. Mean total-to-total isentropic efficiency and pressure ratio reduced to differences of 0.74 and 1.24% from values of 11.23 and 9.31% respectively.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-03-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43775797","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: 2