International Journal of Turbo & Jet-Engines最新文献_第9页

Numerical investigation of flow control in low-pressure turbine cascade using Gurney Flaps 利用轮尼襟翼控制低压涡轮叶栅流动的数值研究

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-10-13 DOI: 10.1515/tjeng-2022-0045

Mohan Agrawal, Jai Bhan Verma, G. Joshi, S. Chandel, Ved Prakash, R. K. Mishra

{"title":"Numerical investigation of flow control in low-pressure turbine cascade using Gurney Flaps","authors":"Mohan Agrawal, Jai Bhan Verma, G. Joshi, S. Chandel, Ved Prakash, R. K. Mishra","doi":"10.1515/tjeng-2022-0045","DOIUrl":"https://doi.org/10.1515/tjeng-2022-0045","url":null,"abstract":"Abstract This paper reports the numerical investigations to analyze the effect of the application of Gurney Flaps on various configurations in a Low-Pressure Turbine (LPT) cascade in mitigating the laminar flow separation during low Reynolds number operations. T106 LPT blade of chord 60 mm has been selected for the present study. Gurney Flaps of flat type and quarter round type of a particular height of the chord length are selected. Flaps are provided near the blades’ trailing edges for numerical analysis. The numerical computations are performed using STARCCM+ software, and the K-ω SST turbulence Model is used for turbulence closure. The studies are performed at various Reynolds numbers ranging from 37,500 to 138,750 to understand the application of various configurations of Gurney Flap vis a vis turbine blade without Gurney Flap. Performance parameters such as lift coefficient, drag coefficient, aerodynamic efficiency, and static pressure distributions over the blade surface are used to analyse the alterations in the performance of aerodynamic characteristics of the LPT Blade. All the Gurney Flap configurations improved the overall blade aerodynamics. Among these configurations, the flat Gurney Flap configuration is found to be superior as it improves the aerodynamic efficiency of the blade.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-10-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46345779","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

Optimization of ACE mode transition control schedule considering geometric adjustment speed 考虑几何调整速度的ACE模式转换控制方案优化

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-10-03 DOI: 10.1515/tjeng-2022-0010

Keran Song, Linyuan Jia, Yu-chun Chen, Tian Tan, Peiyang Fan

引用次数: 0

Development and application of a profile loss model considering the low-Re effect in low-pressure turbine 考虑低压涡轮低re效应的叶型损失模型的建立与应用

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-09-23 DOI: 10.1515/tjeng-2022-0052

W. Jia, Q. Kong, Guanyun Xiao, Handong Mu

{"title":"Development and application of a profile loss model considering the low-Re effect in low-pressure turbine","authors":"W. Jia, Q. Kong, Guanyun Xiao, Handong Mu","doi":"10.1515/tjeng-2022-0052","DOIUrl":"https://doi.org/10.1515/tjeng-2022-0052","url":null,"abstract":"Abstract To improve the prediction accuracy of profile loss at low Reynolds number, a typical low-pressure turbine cascade T106D-EIZ was selected to numerically investigate the effect of Reynolds number on turbine cascade flow. A detailed analysis of profile loss was performed and a profile loss model considering the low-Re effect was developed. Results showed that the incidence angle has a great effect on the inlet and outlet Mach number at low Reynolds number, and the variation of inlet and outlet Mach number further affects the blade profile loss. A correction factor was introduced to consider the effect of incidence angle and Mach number on the profile loss. The profile loss coefficient and stalling incidence angle were both extended to lower Reynolds number based on the numerical results. A Smart Through Flow Analysis Program (STFAP) was developed using the finite volume method to solve the circumferentially averaged Euler equations of S2 surface. Aerodynamic performance of E3 5-stage low-pressure turbine was predicted by STFAP coupled with low-Re profile loss model. Compared with K-O model, the prediction accuracy of efficiency of low-pressure turbine last stage is improved by nearly 1.1 percentage points when the 5-stage low-pressure turbine is in a low Reynolds number state.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48627356","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

Vortex structure control based bleed in axial compressor cascade with tip clearance using large eddy simulation 基于大涡模拟的轴流压气机叶栅间隙排流涡结构控制

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-09-22 DOI: 10.1515/tjj-2022-0047

Yun Gong, Shaowen Chen, Cong Zeng

{"title":"Vortex structure control based bleed in axial compressor cascade with tip clearance using large eddy simulation","authors":"Yun Gong, Shaowen Chen, Cong Zeng","doi":"10.1515/tjj-2022-0047","DOIUrl":"https://doi.org/10.1515/tjj-2022-0047","url":null,"abstract":"Abstract As an essential component, the bleed system plays a critical role in supplying turbine cooling air, guaranteeing stage matching, pressurizing the cabin, and de-icing at the wing and engine inlet. However, the extraction of the bleeding air from the compressor causes the engine efficiency degradation and thrust deficit. Therefore, flow control based on bleed is conducted to compensate the bleed induced disadvantages. The influence of the circumferential bleeding slot location on the tip leakage vortex and passage vortex controlling in a compressor cascade with the tip clearance is numerically studied using large eddy simulation. Three bleed configurations and the smooth casing configuration are investigated. 17.11% loss reduction is obtained through bleeding at 10% c x upstream of the blade leading edge with a bleeding rate of 2.76%. The vortex structures and flow patterns are compared and analyzed to reveal the controlling mechanism. Subsequently, the axial vorticity and loss evolution is discussed, and the interaction between the primary flow and bleeding air is revealed. It’s found that bleeding slot placed within the blade passage is exposed into a highly static pressure gradient, and this causes the bleeding air flows into and spills out the bleeding slot and leads to unnecessary loss. Moreover, the influence of large bleeding rate and inlet boundary layer is assessed.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-09-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42372351","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

Research on the influence of honeycomb cell blockage on the seal leakage characteristics 蜂窝室堵塞对密封泄漏特性影响的研究

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-09-06 DOI: 10.1515/tjj-2022-0031

Chunrui Liu, Ze Yan, Xuezhi Wang, Lidong He, Xingyun Jia, Wenhao Wang

{"title":"Research on the influence of honeycomb cell blockage on the seal leakage characteristics","authors":"Chunrui Liu, Ze Yan, Xuezhi Wang, Lidong He, Xingyun Jia, Wenhao Wang","doi":"10.1515/tjj-2022-0031","DOIUrl":"https://doi.org/10.1515/tjj-2022-0031","url":null,"abstract":"Abstract The accumulation of catalyst dust at the honeycomb seal for a long time will lead to the honeycomb seal cell blockage, weaken the seal effect of the honeycomb seal, and directly affect the safe and stable operation of the flue gas turbine. Therefore, a research on the influence of honeycomb cell blockage on the seal leakage characteristics is carried out. The flow field model of honeycomb seal is established, and the influence of cell blockage on the leakage characteristics of honeycomb seal is analyzed. A seal leakage characteristic experiment bench is built, and the numerical simulation results are verified by the experiment bench. Compared with the honeycomb seal without blockage, the leakage of the honeycomb seal with a blockage rate of 25% increases by about 6.5%, while the leakage of the honeycomb seal with a blockage rate of 25% obtained by the experiment increases by about 6.3%. The numerical simulation results are in good agreement with the experimental results. The results of this research provide theoretical support for revealing the seal leakage characteristics of honeycomb seals under blockage faults.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-09-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46578474","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

Research on temperature rise characteristics of end V-groove ring seal 端面v型槽环密封温升特性研究

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-08-29 DOI: 10.1515/tjj-2022-0013

Le Zhang, Lidong He, Ze Yan, Weize Dai, Xingyun Jia, Chunrui Liu, Wenhao Wang

{"title":"Research on temperature rise characteristics of end V-groove ring seal","authors":"Le Zhang, Lidong He, Ze Yan, Weize Dai, Xingyun Jia, Chunrui Liu, Wenhao Wang","doi":"10.1515/tjj-2022-0013","DOIUrl":"https://doi.org/10.1515/tjj-2022-0013","url":null,"abstract":"Abstract Aiming at the problem of frictional heat generation under high pressure and high speed of the piston ring, the V-groove piston ring is proposed. The finite element analysis method is used to compare and analyze the temperature distribution law of the traditional piston ring and V-groove piston ring. The experimental study on the temperature rise of the piston ring seal is carried out by using the high-pressure and high-speed rotating sealing experimental bench. The experimental results are consistent with the simulation results. The results show that when the rotor speed increases by 1000 rpm, the temperature rise of the traditional piston ring increases by 18.4%, the V-groove piston ring increases by 17.2%. For every 0.5 MPa increase in the pressure applied to the piston ring, the temperature rise of the traditional piston ring increases by 9.2%, the V-groove piston ring increases by 5.8%. The same under the working conditions, the temperature rise of the V-groove piston ring is reduced by 21–29% compared with the traditional piston ring, and the leakage of the V-groove piston ring is reduced by 12–19% compared with the traditional piston ring. The synergistic design of low temperature rises and low leakage of the piston ring.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-08-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42275595","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 self-recirculating casing treatment on the unsteady flow and stability of counter-rotating axial-flow compressor 自循环机壳处理对对对旋轴流压缩机非定常流动及稳定性的影响

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-08-23 DOI: 10.1515/tjj-2022-0016

Yanchao Guo, Limin Gao, X. Mao

{"title":"Effect of self-recirculating casing treatment on the unsteady flow and stability of counter-rotating axial-flow compressor","authors":"Yanchao Guo, Limin Gao, X. Mao","doi":"10.1515/tjj-2022-0016","DOIUrl":"https://doi.org/10.1515/tjj-2022-0016","url":null,"abstract":"Abstract Counter-rotating axial-flow compressor (CRAC) is a promising technology to enhance the thrust-to-weight ratio of aero-engines. Self-recirculating casing treatment (SRCT) is an efficient flow control technique for increasing stall margin in conventional compressors. With the purpose of investigating the applicability and mechanism of SRCT in the CRACs, a two-stage CRAC is selected to investigate the stability enhancement mechanism of SRCT and its effect on the unsteady flow near the rotor tip, and the effect of injector location on the stability improvement capacity of SRCT is also studied. Results show that about 7.73% stall margin improvement can be achieved by configuring the SRCT on the near rotor top, and the injector location also has a significant influence on the stability expansion potential of SRCT. The SRCT delays the stall occurrence by weakening the intensity of tip leakage flow (TLF) and restraining the leading-edge spillages of TLF. The SRCT reduces the unsteady interference between the adjacent rotors by receding the disturbance of the upstream wake and inhibiting the potential flow effect of the downstream. Furthermore, the SRCT reduces the self-excited oscillation frequency of TLF and damps its fluctuation amplitude.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-08-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45649072","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: 3

The aerothermal performance of turbine blade squealer tip at various Reynolds numbers and Mach numbers with moving endwall 不同雷诺数和马赫数下涡轮叶片尖部的气动热性能

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-08-18 DOI: 10.1515/tjj-2022-0040

Shaowen Chen, Cong Zeng, Zhi-yan Zhou, Weihang Li

引用次数: 0

Numerical investigation of a variable stator vane with nonuniform partial radial gaps in an annular compressor cascade 环空压气机叶栅非均匀部分径向间隙可变静叶的数值研究

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-08-15 DOI: 10.1515/tjj-2022-0039

Yimin Zhang, Shaowen Chen, Yueqi Liu, S. Wang

引用次数: 1

Probabilistic analysis of maximum mode shape for mistuned blisk 失谐叶盘最大振型的概率分析

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2022-07-18 DOI: 10.1515/tjj-2021-0065

Bin Bai, Dongmeng Shi, Zuodong Xu, Xiangdong Liu, Chuxiong Xie, Wujin Zhang, Xinglong Zhang, Xuan Wu

{"title":"Probabilistic analysis of maximum mode shape for mistuned blisk","authors":"Bin Bai, Dongmeng Shi, Zuodong Xu, Xiangdong Liu, Chuxiong Xie, Wujin Zhang, Xinglong Zhang, Xuan Wu","doi":"10.1515/tjj-2021-0065","DOIUrl":"https://doi.org/10.1515/tjj-2021-0065","url":null,"abstract":"Abstract The high-fidelity finite element model (HFFEM) and Monte Carlo (MC) simulation of the blisk involve large number of calculations, which leads to low computational efficiency. In this case, an improved quasi-static mode compensation method (IQSMCM) and quadratic function-extremum response surface method (QF-ERSM) are proposed to investigate the probability distribution of mistuned blisk based on its vibration characteristics. The number of nodes and elements of IQSMCM relative to HFFEM are, respectively, reduced by 79.66 and 80.03%. Thus, the degrees of freedoms (DOFs) of IQSMCM are obviously reduced compared with that of HFFEM, and its computational efficiency is obviously increased. The maximum displacement shape (MDS) is investigated via IQSMCM. The computational efficiency is enhanced in the condition of ensuring the computational accuracy. Based on the investigation of maximum mode shape, the probability analysis is performed via QF-ERSM. The computational accuracy of QF-ERSM is improved by 93.80% compared with that of MC. Furthermore, the computational efficiency of QF-ERSM is higher 57.06% than that of QF-RSM. The sample history, extremum response surface function, sample history and distribution histogram of MDS are obtained via QF-ERSM, which provides an important guidance for the reliability research of the mistuned blisk. This research can be applied not only to aeroengine’s blisk but also to other large and complex mechanical structures in practical engineering.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" ","pages":""},"PeriodicalIF":0.9,"publicationDate":"2022-07-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48787074","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