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Flow structure comparison of film cooling versus hybrid cooling: a CFD study 膜冷却与混合冷却的流动结构比较：CFD研究
IF 0.9 4区 工程技术
International Journal of Turbo & Jet-Engines Pub Date : 2023-05-10 DOI: 10.1515/tjj-2022-0058
R. Panda, A. K. Pujari, B. Gudla
{"title":"Flow structure comparison of film cooling versus hybrid cooling: a CFD study","authors":"R. Panda, A. K. Pujari, B. Gudla","doi":"10.1515/tjj-2022-0058","DOIUrl":"https://doi.org/10.1515/tjj-2022-0058","url":null,"abstract":"Abstract Film and jet impingement cooling are widely used techniques in gas turbine vane and blade cooling. The present work investigates and compares the flow structure of a film-cooled flat plate with a hybrid cooling scheme. The hybrid cooling scheme combines both impingement hole and film holes and is named combined impingement-film (IFC) cooling. Experimental validation and computational analyses are carried out on a flat plate with film holes. Different flow parameters, such as velocity pattern, Turbulent kinetic energy, and streamline flow structure, are compared for the two cases in different regions of the flat plate. It is observed that the hybrid scheme shows advantages over film cooling. The jet-to-jet interaction, jet crossflow interaction, and vortex formation are the main factors affecting film cooling performance. There is a 52 % drop in turbulent kinetic energy for the hybrid cooling compared to the film cooling at the film hole exit. More mixing in the coolant and mainstream interaction is observed for the FC case than in the IFC.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47246041","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
Frontmatter 头版头条
4区 工程技术
International Journal of Turbo & Jet-Engines Pub Date : 2023-05-01 DOI: 10.1515/tjj-2023-frontmatter2
{"title":"Frontmatter","authors":"","doi":"10.1515/tjj-2023-frontmatter2","DOIUrl":"https://doi.org/10.1515/tjj-2023-frontmatter2","url":null,"abstract":"","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"124 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136271913","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
The aerodynamic performance degradation analysis of a small high bypass turbofan engine compression system with fan rotor blade leading edge erosion 小型高涵道涡扇发动机叶片前缘受侵蚀压缩系统气动性能退化分析
IF 0.9 4区 工程技术
International Journal of Turbo & Jet-Engines Pub Date : 2023-04-21 DOI: 10.1515/tjj-2023-0031
Lei Shi, Ruilin Jiang, Chen-lei Huang, Shuhan Guo, Guoshun Chen
{"title":"The aerodynamic performance degradation analysis of a small high bypass turbofan engine compression system with fan rotor blade leading edge erosion","authors":"Lei Shi, Ruilin Jiang, Chen-lei Huang, Shuhan Guo, Guoshun Chen","doi":"10.1515/tjj-2023-0031","DOIUrl":"https://doi.org/10.1515/tjj-2023-0031","url":null,"abstract":"Abstract The entire compression system of DGEN380 was selected to study the degradation of aerodynamic characteristics caused by erosion of the leading edge. Numerical simulations under different degrees of leading edge erosion were performed. It was found that the leading edge erosion causes a significant decrease in operability from 70 % of the blade height to the tip, and mainly affects the subsequent flow field in the bypass. At 90 % of blade height, the isentropic efficiency and total pressure ratio of the blade with leading edge erosion are reduced compared to the origin blade. Afterwards, the thrust equation was introduced to analyze the effect of leading edge erosion on the thrust loss under different operating conditions of the aircraft. Among the three operating conditions, the thrust loss rate of the cruise condition was the largest, which provided a reference for the subsequent evaluation of the blade repair condition.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-04-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44986717","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
Installed performance seeking control based on supersonic variable inlet/engine coupling model 基于超音速可变进气道/发动机耦合模型的安装性能寻优控制
IF 0.9 4区 工程技术
International Journal of Turbo & Jet-Engines Pub Date : 2023-04-17 DOI: 10.1515/tjj-2023-0030
Chen Wang, Ximing Sun, Xian Du
{"title":"Installed performance seeking control based on supersonic variable inlet/engine coupling model","authors":"Chen Wang, Ximing Sun, Xian Du","doi":"10.1515/tjj-2023-0030","DOIUrl":"https://doi.org/10.1515/tjj-2023-0030","url":null,"abstract":"Abstract With the advancement of the supersonic aero propulsion system, optimizing the combined performance of inlet/engine integration has become increasingly crucial. To solve the coupling inlet/engine problem, a quasi-one-dimensional inlet modeling and drag calculation method are proposed, integrated performance seeking control (PSC) based on the neighborhood-based speciation differential evolution-grey wolf optimizer (NSDE-GWO) is presented and quantitatively analyses the influence of variable geometry inlet regulation on performance. The results reveal that the optimization effect of the ramp angle adjustment is generally better than that of the bleed adjustment, and the NSDE-GWO hybrid algorithm achieves remarkable optimization solutions in all three different modes. The PSC with variable geometry inlet adjustment provides more additional potential for optimization compared with fixed geometry inlet, and the performance can be maximized by adjusting both the bleed adjustment and the ramp angle. This study maximizes the exploitation of potential and has theoretical guidance and practical engineering significance.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-04-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42531928","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
Reacting flow analysis in scramjet engine: effect of mass flow rate of fuel and flight velocity 超燃冲压发动机反应流分析：燃料质量流量和飞行速度的影响
IF 0.9 4区 工程技术
International Journal of Turbo & Jet-Engines Pub Date : 2023-04-17 DOI: 10.1515/tjeng-2023-0029
S. P. Sanaka, Ramanaiah Kandula, Khyathi Sree Chalamalasetty, Durga Rao Kappala
{"title":"Reacting flow analysis in scramjet engine: effect of mass flow rate of fuel and flight velocity","authors":"S. P. Sanaka, Ramanaiah Kandula, Khyathi Sree Chalamalasetty, Durga Rao Kappala","doi":"10.1515/tjeng-2023-0029","DOIUrl":"https://doi.org/10.1515/tjeng-2023-0029","url":null,"abstract":"Abstract The objective of the study is realizing the effect of fuel mass flow rate and flight speed on combustion in scramjet engine. DLR conical strut based scramjet combustor configuration was chosen and simulated the chemical reaction between the air and hydrogen fuel. A slot of size 40 mm × 0.295 mm provided at the center of the strut to injected hydrogen fuel from the rare side in to the downstream flow. ICEM CFD software is used for the generation of structured elements in computational domain for three dimensional flow analyses. Standard k-epsilon turbulence model and species transport equation is used in ANSYS fluent solver. The predicted temperature, velocity distribution along the axial length was compared with the experimental results and validated. The temperature distribution at different Mach numbers and mass flow rate reveals that the peak temperature increased with the flight speed and inlet fuel mass flow rate. The peak temperature noticed at the center of the combustor is around 3500 K at a flight speed of Mach 4. The predicted variation of temperature, pressure, velocity in the combustor and the flow structure for reacting flow facilitate good understanding of the combustion process in scramjet combustor.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-04-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43841774","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
Effect of zero penetration angle chevrons in supersonic jet noise and screech tone mitigation 零贯穿角人字形对超音速喷气噪声的影响及尖声抑制
IF 0.9 4区 工程技术
International Journal of Turbo & Jet-Engines Pub Date : 2023-04-17 DOI: 10.1515/tjj-2022-0073
Kaleeswaran Periyasamy, Kadiresh P. Natarajan, Bogadi Surendra, Khandai Suresh Chandra
{"title":"Effect of zero penetration angle chevrons in supersonic jet noise and screech tone mitigation","authors":"Kaleeswaran Periyasamy, Kadiresh P. Natarajan, Bogadi Surendra, Khandai Suresh Chandra","doi":"10.1515/tjj-2022-0073","DOIUrl":"https://doi.org/10.1515/tjj-2022-0073","url":null,"abstract":"Abstract An experimental study is conducted to determine the effect of chevrons with zero penetration angles at the CD nozzle exit on an emitted noise field. The implication of passive control is to reduce the blockage of the nozzle exit area with minimal engine thrust penalty. The cold air jets issued at design Mach numbers 1.5 and 1.75 from the De Laval nozzles of the circular section were investigated. This passive control eliminates screech tones at the over and ideally expanded conditions at 60° and 90° in the azimuth plane. The acoustic data measurements have also been observed for the chosen jet Mach numbers. The schlieren images reveal the shock cell pattern to eliminate the effect of shock-associated noise levels at supersonic jets. The results show that 10 chevrons with no penetration act as an effective eliminator of screech tone and noise suppression average ∆OASPL value up to 3 dB at Mach number 1.75.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-04-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42725090","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
An efficient flow control technique based on co-flow jet and multi-stage slot circulation control applied to a supercritical airfoil 基于共流射流和多级缝隙循环控制的高效流动控制技术在超临界翼型中的应用
IF 0.9 4区 工程技术
International Journal of Turbo & Jet-Engines Pub Date : 2023-04-10 DOI: 10.1515/tjj-2023-0027
Lei Wang, Hanan Lu, Yue Xu, Q. Li
{"title":"An efficient flow control technique based on co-flow jet and multi-stage slot circulation control applied to a supercritical airfoil","authors":"Lei Wang, Hanan Lu, Yue Xu, Q. Li","doi":"10.1515/tjj-2023-0027","DOIUrl":"https://doi.org/10.1515/tjj-2023-0027","url":null,"abstract":"Abstract Circulation control is a kind of efficient flow control technology which can improve aircraft aerodynamic performance and reduce fuel consumption. However, improving the aerodynamic efficiency of a circulation device to enhance flight endurance and achieve environmentally flying is a challenging problem for the application of circulation control. This paper presents an efficient flow control technique that combines co-flow jet and multi-stage slot circulation control. The combinational flow control technique is applied to a supersonic airfoil to test its energy consumption and aerodynamic benefit achievement. Results show that both the single and double slot circulation control can improve the maximum lift-drag ratio of the baseline airfoil, with an increment of 11.3% and 19.1%, respectively. Compared with the single application of co-flow jet control which can increase the lift-drag ratio of the baseline airfoil by 16.3% and extend the stall angle of attack from 6° to 8°, the combinational flow control can obtain a more significant lift-drag ratio increment by about 27.3% and eliminate flow separations at high angle of attack. The stall angle of attack can even be increased to about 10°. Additionally, the blowing efficiency of the circulation control airfoil has been comprehensively analyzed. The results show that the maximum effective lift-drag ratio and highest blowing efficiency can be achieved at a blowing coefficient of 0.00235.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-04-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42465910","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 investigations of heat transfer characteristics using oblong fins and circular fins in a wedge channel 楔形通道中长形翅片和圆形翅片传热特性的数值研究
IF 0.9 4区 工程技术
International Journal of Turbo & Jet-Engines Pub Date : 2023-04-04 DOI: 10.1515/tjj-2022-0055
Goveraiahgari Venkatesh, R. Meenakshi Reddy, Pabbisetty Mallikarjuna Rao
{"title":"Numerical investigations of heat transfer characteristics using oblong fins and circular fins in a wedge channel","authors":"Goveraiahgari Venkatesh, R. Meenakshi Reddy, Pabbisetty Mallikarjuna Rao","doi":"10.1515/tjj-2022-0055","DOIUrl":"https://doi.org/10.1515/tjj-2022-0055","url":null,"abstract":"Abstract Turbine inlet air temperatures are extremely high, which can result in blade material damage. As a result, cooling the turbine blades is required, and a variety of cooling techniques have been introduced. The majority of the previous research on pin fins has focused on circular fins using a wedge duct to apply a constant temperature and uniform heat flux to the end wall and pin fin surfaces. The present study compares seven oblong pin-fins to seven circular pin fins in a wedge duct with a Reynolds number range of 10,000–50,000 and a constant heat flux (surface) of 3280 W/m2 applied to the endwall and surfaces of the oblong pin fin. The results indicate that the friction factor for oblong fins is 14% lower than for circular pin fins. The thermal performance factor is increased by 11.4%. The thermal performance factor can be improved by using oblong pin fins with higher Reynolds numbers.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-04-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43607522","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
Detailed investigation of supersonic film cooling performance in a convergent divergent nozzle 会聚发散喷管超声速气膜冷却性能的详细研究
IF 0.9 4区 工程技术
International Journal of Turbo & Jet-Engines Pub Date : 2023-03-27 DOI: 10.1515/tjj-2022-0080
Lingling Chen, Y. Shi, Haoqi Yang, Yalin Shi, Qingzhen Yang
{"title":"Detailed investigation of supersonic film cooling performance in a convergent divergent nozzle","authors":"Lingling Chen, Y. Shi, Haoqi Yang, Yalin Shi, Qingzhen Yang","doi":"10.1515/tjj-2022-0080","DOIUrl":"https://doi.org/10.1515/tjj-2022-0080","url":null,"abstract":"Abstract This paper numerically studied supersonic film cooling performance in a convergent divergent nozzle, for the purpose of exploring and extending the knowledge of high-efficient cooling techniques for exhaust nozzles in real working conditions. The work was conducted with a steady state RANS approach with the SST turbulence model. The boundary conditions were chosen to mimic a real engine condition. The slot height and the inlet pressure ratio were varied to investigate the effect of the geometrical condition and flow condition. The flow field was analyzed in detail to study the phenomena of the supersonic secondary flow injected into the transonic flow. Besides the cooling effectiveness, the thrust coefficient and the discharge coefficient for the cooling cases were discussed together with the baseline case, to evaluate the influence of the supersonic coolant injection on the nozzle performance. The work can be a basis for the design of cooling schemes in an aero-engine exhaust nozzle.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-03-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46450552","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
A novel design of impeller cavity pre-swirl system for efficient supercharging and low power consumption 一种新颖的叶轮腔预旋流系统设计，实现高效增压和低能耗
IF 0.9 4区 工程技术
International Journal of Turbo & Jet-Engines Pub Date : 2023-03-02 DOI: 10.1515/tjj-2022-0038
Wenlei Lian, Yu Zhu, Xiaoming Chen, Zhixiang Zhou, Yong-Yi Huang
{"title":"A novel design of impeller cavity pre-swirl system for efficient supercharging and low power consumption","authors":"Wenlei Lian, Yu Zhu, Xiaoming Chen, Zhixiang Zhou, Yong-Yi Huang","doi":"10.1515/tjj-2022-0038","DOIUrl":"https://doi.org/10.1515/tjj-2022-0038","url":null,"abstract":"Abstract A design for a turbine pre-swirl system with impeller cavity is proposed to improve the quality of cooling air supplied to the turbine blades of an aeroengine. Impeller cavity is analyzed in order to increase the system pressure ratio with a low system power consumption at the system outlet. Theoretical and numerical investigation are used to investigate the flow characteristics in an impeller cavity pre-swirl system. The conclusions in this study indicate that the impeller structure can increases the pressure ratio by changing the power consumption and distribution of the absolute velocity in the impeller cavity and system outlet. To obtain high pressure ratio and low power consumption, the impeller should have a structure with a high outlet installation radius and low outlet angle. The highest increase in the pressure ratio compared with the empty cavity pre-swirl system is 6.4% and the corresponding increase in the power consumption is 2620 W.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-03-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48359430","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
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