Query：
学者姓名：丰镇平
Refining：
Year
Type
Indexed by
Source
Complex
Co-Author
Language
Clean All
Abstract ：
In the gas turbines, the blade tip is difficult to be cooled down due to the complex flow and the intense heat transfer process here. Phantom cooling has been considered a kind of second-order cooling effect to help protect the tip using upstream spent cooling air. In this work, the blade tip phantom cooling performance of four different tip configurations (the flat tip (FT), the squealer tip with suction-side rim (SSRST), the squealer tip with pressure-side rim (PSRST), and the squealer tip with double-side rims (DSRST)) was compared under four different cooling air blowing ratios (M), with two different tip gaps (tau = 1.32% C (chord), and 3.22% C). Pressure sensitive paint technique was adopted to obtain the cooling effectiveness contours. The turbulence-validated computational predictions were performed to help analyze the flow characteristics near the tip. Results indicated that the FT case presents the best phantom cooling performance than others, and phantom cooling traces can be detected on most portions of the tip. The eta values of the SSRST case are a little bit lower than the FT case, and the PSRST and DSRST cases perform the worst for almost no phantom cooling traces can be observed on the cavity surface. Additionally, a bigger tip gap would reduce the tip phantom cooling effectiveness for any tip configuration. Moreover, from the computational results (tau = 1.32% C, M = 1.5), relatively lower aerodynamic losses are obtained in SSRST and DSRST cases, while the PSRST case shows the highest loss.
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | Li, Feng , Jia, Zhe , Wang, Haifeng et al. Experimental and Numerical Investigations Into the Blade Tip Phantom Cooling Performance [J]. | JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME , 2022 , 144 (7) . |
| MLA | Li, Feng et al. "Experimental and Numerical Investigations Into the Blade Tip Phantom Cooling Performance" . | JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME 144 . 7 (2022) . |
| APA | Li, Feng , Jia, Zhe , Wang, Haifeng , Liu, Zhao , Feng, Zhenping . Experimental and Numerical Investigations Into the Blade Tip Phantom Cooling Performance . | JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER-TRANSACTIONS OF THE ASME , 2022 , 144 (7) . |
| Export to | NoteExpress RIS BibTex |
Abstract ：
Characteristics of particle migration and deposition were numerically investigated in presence of aggressive swirl at the turbine inlet. The isolated effects of the inlet swirl were considered in detail by shifting the circumferential position of the swirl and by implementing positive and negative swirling directions. Particles were released from the turbine inlet and the resulting deposition on the vanes was determined by using the critical velocity model in a range of particle diameters from 1 to 25 lm. Results show that the particles are more likely to move outwards to the boundary walls of the passage by the action of the swirling flow. However, this could be relieved by increasing the particle size. An imbalance problem of the deposition is found between the adjacent vanes, which could introduce additional inlet non-uniformities towards the downstream rotor and thus accelerate performance degradation of the turbine stage. Overall, the negative swirl case has higher overall capture efficiency within the entire turbine than the positive swirl case for larger particles, and when the inlet swirl is shifted to the mid-passage of the turbine, more deposits could be produced in comparison with the case in which the swirl aims at the vane leading edge.(c) 2021 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).
Keyword ：
Combustor-turbine interac-tion Gas turbine Inlet swirl Numerical simulation Particle deposition
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | Yang, Xing , Hao, Zihan , Feng, Zhenping . Particle deposition patterns on high-pressure turbine vanes with aggressive inlet swirl [J]. | CHINESE JOURNAL OF AERONAUTICS , 2022 , 35 (3) : 75-89 . |
| MLA | Yang, Xing et al. "Particle deposition patterns on high-pressure turbine vanes with aggressive inlet swirl" . | CHINESE JOURNAL OF AERONAUTICS 35 . 3 (2022) : 75-89 . |
| APA | Yang, Xing , Hao, Zihan , Feng, Zhenping . Particle deposition patterns on high-pressure turbine vanes with aggressive inlet swirl . | CHINESE JOURNAL OF AERONAUTICS , 2022 , 35 (3) , 75-89 . |
| Export to | NoteExpress RIS BibTex |
Abstract ：
The leading edge is the critical portion for a gas turbine blade and is often insufficiently cooled due to the adverse effect of Crossflow in the cooling chamber. A novel internal cooling structure, wall jet cooling, can suppress Crossflow effect by changing the coolant flow direction. In this paper, the conjugate heat transfer and aerodynamic characteristics of blades with three different internal cooling structures, including impingement with a single row of jets, swirl cooling, and wall jet cooling, are investigated through RANS simulations. The results show that wall jet cooling combines the advantages of impingement cooling and swirl cooling, and has a 19-54% higher laterally-averaged overall cooling effectiveness than the conventional methods at different positions on the suction side. In the blade with wall jet cooling, the spent coolant at the leading edge is extracted away through the downstream channels so that the jet could accurately impinge the target surface without unnecessary mixing, and the high turbulence generated by the separation vortex enhances the heat transfer intensity. The Coriolis force induces the coolant air to adhere to the pressure side's inner wall surface, preventing the jet from leaving the target surface. The parallel cooling channels eliminate the common Crossflow effect and make the flow distribution of the orifices more uniform. The trailing edge outlet reduces the entire cooling structure's pressure to a low level, which means less penalty on power output and engine efficiency.
Keyword ：
conjugate heat transfer gas turbine blade impingement and swirl cooling
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | Deng, Qinghua , Wang, Huihui , He, Wei et al. Cooling Characteristic of a Wall Jet for Suppressing Crossflow Effect under Conjugate Heat Transfer Condition [J]. | AEROSPACE , 2022 , 9 (1) . |
| MLA | Deng, Qinghua et al. "Cooling Characteristic of a Wall Jet for Suppressing Crossflow Effect under Conjugate Heat Transfer Condition" . | AEROSPACE 9 . 1 (2022) . |
| APA | Deng, Qinghua , Wang, Huihui , He, Wei , Feng, Zhenping . Cooling Characteristic of a Wall Jet for Suppressing Crossflow Effect under Conjugate Heat Transfer Condition . | AEROSPACE , 2022 , 9 (1) . |
| Export to | NoteExpress RIS BibTex |
Abstract ：
A jet impingement system equipped with extended jet holes was experimentally evaluated in this study. To reproduce a strong crossflow condition, the jet impingement configuration featured a multiple-jet array of 16 x 5 rows in the streamwise and pitchwise directions, respectively, and the crossflow was exhausted from one open side of the impingement channel only. The transient thermochromic liquid crystal (TLC) technique was used to measure heat transfer on the target surface for different extended lengths of 1.0-2.5 jet hole diameters with Reynolds numbers from 1.0 x 10(4) to 3.0 x 10(4). To provide complementary flow physics for elaborating the heat transfer patterns observed from the experiments, well-validated numerical simulations were carried out. Comparisons with a baseline jet hole configuration showed that the extended jet holes helped to significantly improve the heat transfer levels as well as to generate a more uniform distribution pattern by suppressing the crossflow. Despite an aerodynamic penalty, the extended jet holes provided much higher heat transfer levels at equal pumping power consumption. The flow fields obtained by the numerical simulations revealed that the jets issued from the extended jet holes were straighter and had less mixing with the crossflow, resulting in a higher jet momentum impinging onto the target. Most importantly, it was found that the dominated flow mechanism of the extended jet holes was to prevent the jets from being redirected by the crossflow in strong crossflow conditions, rather than reducing the jet-to-target distance.
Keyword ：
experimental extended jet hole gas turbine gas turbine heat transfer heat transfer heat transfer enhancement jet impingement cooling measurement techniques thermochromic liquid crystal
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | Yang, Xing , Wu, Hang , Feng, Zhenping . Experimental and Numerical Investigations of Extended Jet Effects on Multiple-Jet Impingement Heat Transfer Characteristics [J]. | JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS , 2022 , 14 (10) . |
| MLA | Yang, Xing et al. "Experimental and Numerical Investigations of Extended Jet Effects on Multiple-Jet Impingement Heat Transfer Characteristics" . | JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS 14 . 10 (2022) . |
| APA | Yang, Xing , Wu, Hang , Feng, Zhenping . Experimental and Numerical Investigations of Extended Jet Effects on Multiple-Jet Impingement Heat Transfer Characteristics . | JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS , 2022 , 14 (10) . |
| Export to | NoteExpress RIS BibTex |
Abstract ：
In this paper, detailed flow patterns and heat transfer characteristics of a jet impingement system with extended jet holes are experimentally and numerically studied. The jet holes in the jet plate present an inline array of 16 x 5 rows in the streamwise (i.e., the crossflow direction) and spanwise directions, where the streamwise and spanwise distances between adjacent holes, which are normalized by the jet hole diameter (x(n)/d and y(n)/d), are 8 and 5, respectively. The jets impinge onto a smooth target plate with a normalized distance (z(n)/d) of 3.5 apart from the jet plate. The jet holes are extended by inserting stainless tubes throughout the jet holes and the extended lengths are varied in a range of 1.0d-2.5d, depending on the jet position in the streamwise direction. The experimental data is obtained by using the transient thermochromic liquid crystal (TLC) technique for wide operating jet Reynolds numbers of (1.0 x 10(4))-(3.0 x 10(4)). The numerical simulations are well-validated using the experimental data and provide further insight into the flow physics within the jet impingement system. Comparisons with a traditional baseline jet impingement scheme show that the extended jet holes generate much higher local heat transfer levels and provide more uniform heat transfer distributions over the target plate, resulting in the highest improvement of approximately 36% in the Nusselt number. Although the extended jet hole configuration requires a higher pumping power to drive the flow through the impingement system, the gain of heat transfer prevails over the penalty of flow losses. At the same pumping power consumption, the extended jet hole design also has more than 10% higher heat transfer than the baseline scheme.
Keyword ：
extended jet hole gas turbine heat transfer jet impingement cooling thermochromic liquid crystal (TLC)
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | Yang, Xing , Wu, Hang , Feng, Zhenping . Jet Impingement Heat Transfer Characteristics with Variable Extended Jet Holes under Strong Crossflow Conditions [J]. | AEROSPACE , 2022 , 9 (1) . |
| MLA | Yang, Xing et al. "Jet Impingement Heat Transfer Characteristics with Variable Extended Jet Holes under Strong Crossflow Conditions" . | AEROSPACE 9 . 1 (2022) . |
| APA | Yang, Xing , Wu, Hang , Feng, Zhenping . Jet Impingement Heat Transfer Characteristics with Variable Extended Jet Holes under Strong Crossflow Conditions . | AEROSPACE , 2022 , 9 (1) . |
| Export to | NoteExpress RIS BibTex |
Abstract ：
In this paper, cooling characteristics of a novel film hole are experimentally evaluated over a linear turbine endwall for enhancing the endwall film cooling. The novel hole features a bean-shaped exit and cooling effectiveness over the endwall cooled by the bean-shaped holes is measured by using the pressure-sensitive paint technique for a wide range of coolant flow rates that cover typical engine conditions. For direct comparisons, measurements are also undertaken on the same endwall film-protected by traditional cylindrical holes with the equal hole distribution pattern at the same coolant consumption. Particularly, residual swirl from upstream combustors is considered in this study for increasing the adaptability of the novel holes in complex approaching flow conditions that are typically seen in today's advanced aircraft engines. Results reveal that the bean-shaped holes present superior cooling effectiveness to the cylindrical holes and the outperformance of the shaped holes becomes more prominent at higher coolant flow rates. The superiority is diminished when the shaped holes are positioned close to the passage suction side. Overall, effectiveness can be generally augmented more than two times by the novel holes. The inclusion of the swirl has adverse effects on both the bean-shaped and cylindrical holes. Despite this, the bean-shaped holes still outperform the cylindrical holes. An important finding is that inlet negative swirl is much more detrimental to the cooling over the endwall than the inlet positive swirl, regardless of the hole shapes. This is expected to provide guidelines for the arrangement of swirlers within the combustors.
Keyword ：
Aero-engine turbine endwall Film cooling Inlet swirl Novel shaped hole Pressure-sensitive paint technique
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | Yang, Xing , Zhao, Qiang , Feng, Zhenping . Experimental evaluation of cooling effectiveness from novel film holes over turbine endwalls with inlet swirl [J]. | INTERNATIONAL JOURNAL OF THERMAL SCIENCES , 2022 , 174 . |
| MLA | Yang, Xing et al. "Experimental evaluation of cooling effectiveness from novel film holes over turbine endwalls with inlet swirl" . | INTERNATIONAL JOURNAL OF THERMAL SCIENCES 174 (2022) . |
| APA | Yang, Xing , Zhao, Qiang , Feng, Zhenping . Experimental evaluation of cooling effectiveness from novel film holes over turbine endwalls with inlet swirl . | INTERNATIONAL JOURNAL OF THERMAL SCIENCES , 2022 , 174 . |
| Export to | NoteExpress RIS BibTex |
Abstract ：
In this study, a novel endwall modification by adding small-scale ribs onto a turbine endwall surface is proposed to reduce thermal loads on the endwall. The small-scale ribs are positioned in a streamline curved and an axially-straight array patterns and, square and triangular shapes are imposed to the cross section of the ribs. The feasibility of improving purge air cooling by the ribs is investigated by using well-validated computational fluid dynamics (CFD) methods. Comprehensive comparisons of cooling performance among the ribbed endwall cases are made by examining cooling effectiveness, heat transfer, and aerodynamic losses. Detailed flow topologies are presented to reveal flow mechanisms involved in the actions of the ribs within the turbine passage flow. Particularly, secondary-order effects of the ribs on the turbine airfoil surfaces are also documented, which is expected to provide three-dimensional boundary conditions for the turbine aerodynamic and thermal analyses. Comparisons between the ribbed endwall cases and a smooth endwall case show that the endwall modification by adding small-scale ribs is effective in reducing thermal loads on the endwall via enhancing cooling effectiveness and, in some cases, reducing heat transfer levels. The thermal load reduction can be further improved by increasing purge air flow ratio. However, as additional vorticities are introduced by the ribs, slight aerodynamic penalty is generated. Among the four rib cases, the straight triangular-shaped rib case has the lowest overall cooling performance for the endwall. Additionally, secondary-order cooling effects are visible on the airfoil suction surface for all rib cases but only the straight rib cases can generate additional purge air coverage on the airfoil pressure surface, without significantly changing pressures in that region. This work offers a new option of thermal management techniques for the turbine endwall and the results provide guidelines regarding endwall modifications of such sort.(c) 2022 Elsevier Masson SAS. All rights reserved.
Keyword ：
Aero-engine turbine endwall Endwall modification Film cooling Heat transfer Numerical simulation
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | Yang, Xing , Wu, Yongqiang , Zhao, Qiang et al. Study on film cooling for aero-engine turbine endwalls with various small-scale surface structures [J]. | AEROSPACE SCIENCE AND TECHNOLOGY , 2022 , 123 . |
| MLA | Yang, Xing et al. "Study on film cooling for aero-engine turbine endwalls with various small-scale surface structures" . | AEROSPACE SCIENCE AND TECHNOLOGY 123 (2022) . |
| APA | Yang, Xing , Wu, Yongqiang , Zhao, Qiang , Feng, Zhenping . Study on film cooling for aero-engine turbine endwalls with various small-scale surface structures . | AEROSPACE SCIENCE AND TECHNOLOGY , 2022 , 123 . |
| Export to | NoteExpress RIS BibTex |
Abstract ：
本文基于网格节点位置坐标变分技术,针对固体导热问题推导了导热伴随方程及其对应的边界条件,并应用有限体积法求解了导热与伴随方程.给出了固体域表面温度分布反设计问题和固体域平均温度正设计问题对应的目标泛函变分的具体表达式,应用拟牛顿算法构建了优化设计系统.针对空心圆环导热问题,计算了目标函数关于内径的梯度,并将计算结果与有限差分方法和理论值进行对比,验证了导热伴随系统的有效性.最后给出了空心圆柱内壁面形状反设计、空心叶片壁面厚度反设计的计算结果以及叶片型线保持不变,以降低叶片固体域平均温度为目标,对冷却通道隔板位置与厚度进行的优化设计结果.优化结构平均温度与初始结构相比降低了11.1K.
Keyword ：
导热优化 反设计 连续伴随方法 内部冷却
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | 阮有钢 , 刘战胜 , 丰镇平 . 基于伴随方法的叶片冷却通道导热优化研究 [J]. | 工程热物理学报 , 2021 , 42 (6) : 1431-1437 . |
| MLA | 阮有钢 et al. "基于伴随方法的叶片冷却通道导热优化研究" . | 工程热物理学报 42 . 6 (2021) : 1431-1437 . |
| APA | 阮有钢 , 刘战胜 , 丰镇平 . 基于伴随方法的叶片冷却通道导热优化研究 . | 工程热物理学报 , 2021 , 42 (6) , 1431-1437 . |
| Export to | NoteExpress RIS BibTex |
Abstract ：
The rectification characteristics of a tab-type elbow flow conditioner under three incoming flow conditions are investigated by numerical methods, and the flow mechanism, rectification performance, application range and pressure loss characteristics are analyzed. The results show that the elbow tabs form a counter-rotating induced vortex through the influence of pressure difference, and guide the outside fluid to the inside in elbows, thus greatly enhancing the momentum exchange between the fluids, and achieving the effect of disturbing the original velocity distribution and forming a uniform flow. Compared with the smooth tube elbow, the tab-type flow conditioner has little effect on the pressure uniformity, but increases the velocity uniformity by 21%-36%, and the influence on the flow angle uniformity varies with the inlet conditions. The flow resistance of the tab-type flow conditioner is higher than that of the blade-type flow conditioner, lower than that of the orifice-plate flow conditioner, and equivalent to the tube bundle flow conditioner. © 2021, Editorial Office of Journal of Xi'an Jiaotong University. All right reserved.
Keyword ：
Numerical methods Pressure effects
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | Deng, Qinghua , He, Wei , Zhang, Liang et al. Rectification Characteristics of Tab-Type Elbow Flow Conditioner [J]. | Journal of Xi'an Jiaotong University , 2021 , 55 (6) : 92-101 . |
| MLA | Deng, Qinghua et al. "Rectification Characteristics of Tab-Type Elbow Flow Conditioner" . | Journal of Xi'an Jiaotong University 55 . 6 (2021) : 92-101 . |
| APA | Deng, Qinghua , He, Wei , Zhang, Liang , Peng, Aoran , Zhao, Zhuobin , Feng, Zhenping . Rectification Characteristics of Tab-Type Elbow Flow Conditioner . | Journal of Xi'an Jiaotong University , 2021 , 55 (6) , 92-101 . |
| Export to | NoteExpress RIS BibTex |
Abstract ：
Heat conduction adjoint equation as well as corresponding adjoint boundary conditions were derived based on grid coordinate variation technique. The adjoint equation was solved adopting the finite volume method successfully. The formulas for the variation of augmented objective functions were induced in detail for surface temperature distribution inverse design and average temperature optimization problems. An optimization system was built based on quasi-newton methods. Derivatives of the objective function to the radius were calculated for conduction within a hollow cylinder. The values were compared with analytical and finite difference method gradients to validate the correctness of the method. Results of the inverse design cases for hollow cylinder inner wall shape and hollow blade thickness were given. Finally, the parameters of the cooling passage struts were designed for average temperature within the hollow blade. The average temperature of the optimal structure decreased 11.1 K compared to the original one. © 2021, Science Press. All right reserved.
Keyword ：
Cylinders (shapes) Finite difference method Finite volume method Heat conduction Inverse problems Newton-Raphson method Structural optimization
Cite：
Copy from the list or Export to your reference management。
| GB/T 7714 | Ruan, You-Gang , Liu, Zhan-Sheng , Feng, Zhen-Ping . Study on Adjoint-based Conduction Optimization Method for Blade Internal Cooling Passages [J]. | Journal of Engineering Thermophysics , 2021 , 42 (6) : 1431-1437 . |
| MLA | Ruan, You-Gang et al. "Study on Adjoint-based Conduction Optimization Method for Blade Internal Cooling Passages" . | Journal of Engineering Thermophysics 42 . 6 (2021) : 1431-1437 . |
| APA | Ruan, You-Gang , Liu, Zhan-Sheng , Feng, Zhen-Ping . Study on Adjoint-based Conduction Optimization Method for Blade Internal Cooling Passages . | Journal of Engineering Thermophysics , 2021 , 42 (6) , 1431-1437 . |
| Export to | NoteExpress RIS BibTex |
Export
| Results： |
Selected to |
| Format： |
