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  • Technology Development Trend of Heavy-duty Gas Turbine Compressor
    YU Chunhua, QUE Xiaobin, WU Hong
    2024, 44(9): 1317-1327. https://doi.org/10.19805/j.cnki.jcspe.2024.240309
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    Heavy-duty gas turbine is a kind of efficient thermo-mechanical conversion equipment so far, with the combined cycle efficiency higher than 60%. As gas turbines have excellent peak shaving capability, they will play an increasingly important role in the new power network based on new energy. An overview of the working characteristics, the structural features and main technical parameters of heavy-duty gas turbine compressors were introduced. The development and technical progress of typical gas turbine compressors from major international original equipment manufacturers were reviewed. The research progress of compressor design system was summarized. Considering the development of advanced heavy-duty gas turbine technology, key technology development directions were proposed, including aerodynamic layout optimization, high performance airfoil, full 3D design of transonic stages and highly integrated design system, based on the development status of heavy-duty gas turbines in China.
  • Progress in Axial Staged Lean Premixed Combustion Technology of Gas Turbines
    LIANG Enguang, ZHANG Chenjie, YU Zhijian, ZHU Min
    2024, 44(9): 1328-1339. https://doi.org/10.19805/j.cnki.jcspe.2024.240233
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    The prospective demand for carbon reduction requires gas turbine combustion chambers to control NOx emissions, improve power regulation range and fuel adaptability while outlet temperatures are continuously increasing. To address the above challenges, gas turbine manufacturers are developing axial staged combustion technology. This paper firstly introduced the principle of axial staged combustion and analyzed the effects of axial staged parameters, jet-in-crossflow flame morphology, nozzle geometry and fuel type on pollutant emissions and combustion instability. Existing studies show that reducing the equivalence ratio of the primary combustion chamber and enhancing the mixing uniformity of the secondary stage primary combustion chamber can reduce pollutant emissions. The thermoacoustic oscillation of axial staged combustion chambers is complex, and could be inhibited by a reasonable selection of stage parameters. The emission reduction benefits and part-load flexibility of axial staged combustion chambers have been verified in commercial operation. Based on the current research status, key issues and future research directions of axial staged combustion technology are proposed.
  • Research Progress on Endwall Cooling of Gas Turbine Cascades
    FENG Zhenping, LIU Zhao, LU Yixuan, ZHANG Weixin, XIE Yehang, DING Yuqiang, SONG Yu
    2024, 44(9): 1340-1352. https://doi.org/10.19805/j.cnki.jcspe.2024.240274
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    The flow field near the endwall of gas turbine cascade presents extremely complicated three-dimensional characteristics, and the endwall cooling design needs to consider not only the effects of the strong secondary flow of the endwall on the cooling performance, but also the effects of the cooling layout on the flow and heat transfer characteristics of the proximal endwall. In view of the cooling demand for the gas turbine cascade endwall, a combination of numerical simulation and experimental test were used to systematically investigate the effects of discrete air film holes, leakage flow and endwall modification on the endwall surface film cooling, heat transfer, flow and cascade aerodynamic characteristics under different mass flow ratios. The results show that, the film cooling effectiveness of the endwall can be effectively improved by the appropriate injection angle and layout of the film holes, the geometric structure of the leakage flow cooling unit and the addition of micro-scaled ribs on the endwall surface. The leakage flow from upstream slot and rim seal can provide cooling protection for the upstream and the area near the suction surface of the upper half of the endwall, while the leakage flow from mid-passage gap will protect the rear half endwall near suction side well. The arrangement of fan-shaped air film holes and the curved assembly gap can not only improve the effectiveness of film cooling, but also effectively control the aerodynamic losses.
  • Effects of Blade Tip Clearance on Performance Degradation of the Multi-stage Axial Compressor
    XIAO Junfeng, WU He, GAO Song, LI Yuanyuan, YU Feilong, DUAN Jingyao, HE Wei, ZHANG Meng
    2024, 44(9): 1353-1360. https://doi.org/10.19805/j.cnki.jcspe.2024.240193
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    Taking the F-class gas turbine compressor as the research object, the performance degradation mechanism of multi-stage axial compressor at different states of corrosion/ware was studied by three-dimensional numerical simulation, considering the changes in blade tip clearance caused by corrosion and wear during actual operation of gas turbine. The influence of tip clearance on the performance of multi-stage axial compressor was analyzed. Results show that the increase of tip clearance causes the characteristic curves of the compressor to move towards the direction of mass flow reduction as a whole, resulting in certain degree of decline of mass flow, efficiency and pressure ratio. With the increase of tip clearance, the compressor maximum efficiency decreases gradually, and the surge margin decreases obviously. The increase of tip clearance also results in intensified flow separation inside the compressor, and the change of tip clearance of rotors has more serious impact on flow separation inside the compressor. The flow separation near the trailing edge of the suction surface of stators leads to the formation of a low Mach number region, and the loss near the stator root increases obviously due to the countercurrent low-speed vortices, resulting in the decline of compressor performance.
  • Influence of Radial Inflow Distortion on Flutter Characteristics of Gas Turbine Compressor Blades
    LIU Yupeng, LI Yunzhu, LUO Yuxuan, XIE Yonghui, ZHANG Di
    2024, 44(9): 1361-1369. https://doi.org/10.19805/j.cnki.jcspe.2024.240194
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    In order to analyze the influence of inflow distortion on flutter characteristics of gas turbine compressors, an inlet total pressure model with radial distortion was established. Based on the influence coefficient method, the effects of radial inflow total pressure distortion with different phases and distortion intensities on the flow field characteristics and aeroelastic stability of compressors were studied. Results show that the radial inflow total pressure distortion with phase angles of 90° and 180° will increase the minimum value of aerodynamic damping under dangerous conditions, and the aeroelastic stability is improved. The radial inflow total pressure distortion with phase angle of 180° can improve the aeroelastic stability of the compressor at all inter blade phase angles. However, the radial inflow total pressure distortion with phase angles of 0° and 270° will increase the risk of compressor flutter,which should be avoided.
  • Experimental Study on Hydrogen-blended Natural Gas Combustion of a New DeNOx Burner for F-class Heavy-duty Gas Turbine
    HE Lei, ZHANG Fucheng, YAN Wei, ZHANG Jin, WANG Chengwu, WANG Haotong, LIU Xiaopei, WU Keliang, CHEN Mingmin
    2024, 44(9): 1370-1377. https://doi.org/10.19805/j.cnki.jcspe.2024.240106
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    Aiming to reduce carbon emissions for environmental sustainability, hydrogen-blended combustion has emerged as a pivotal advancement in gas turbine technology. Focusing on the hydrogen-blended natural gas combustion characteristics, comprehensive full-temperature, full-pressure, and full-scale combustion tests with a hydrogen-enriched ratio were conducted on an independently developed DeNOx burner of F-class heavy-duty gas turbine. The burner's adaptability to hydrogen-blended combustion was analyzed based on performance parameters such as temperature, emissions, humming, and acceleration. Results show that within a hydrogen blending range of 30% to 40%, the NOx emissions from this burner can be controlled below 30 mg/m3 across the base load range of 55% to 100%. As the hydrogen blending ratio increases, flame transition occurs at a lower load, which is conducive to stable load increases. Furthermore, the outlet temperature of the burner rises, but no flashback occurs.
  • Experimental Study of a Certain Type of F-class Axial Staged Combustion Chamber Under Full Temperature and Full Pressure
    SUI Yongfeng, ZANG Peng, ZHANG Yuming, PENG Zhisheng, FU Yanni, GU Tingwei
    2024, 44(9): 1378-1384. https://doi.org/10.19805/j.cnki.jcspe.2024.240234
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    The axial staged combustion chamber of the self-developed F-class gas turbine was studied under full temperature and full pressure condition. In order to explore the combustion performance of the combustion chamber under the working conditions of the design point, such as pressure loss, outlet temperature distribution, wall temperature, pollutant discharge, combustion efficiency and thermoacoustic stability,etc. Results show that, the total pressure loss coefficient of the combustion chamber is 5.4% at the design point. The outlet temperature distribution factor and radial temperature distribution factor are 0.06 and 0.03, respectively. And the wall temperature of the flame barrel in the combustion chamber is below 850 ℃. The mole fraction of NOx is maintained 1.9×10-5, while the emissions of CO and unburned hydrocarbon(UHC) are basically zero. The combustion efficiency is maintained above 99.99%. The amplitude of dynamic pressure spectrum is below 3 kPa, which indicates the thermoacoustic state of the combustor is stable.
  • Experimental Study on Reignition Flame Flow and Combustion Characteristics of H2/CH4 Fuel Axial Staging Combustion
    LI Yuansen, LI Yuze, XIAO Yunlai, GE Bing
    2024, 44(9): 1385-1392. https://doi.org/10.19805/j.cnki.jcspe.2024.240206
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    Axial fuel staging (AFS) combustion technology is an advanced low pollution combustion technology for heavy gas engines at present. In order to reveal the effects of H2/CH4 fuel species and jet angle on the re-combustion zone flow field and flame structure of axial staged combustion, high-frequency particle image velocimetry (PIV) and OH*-based self luminescence techniques were used. The effects of 90° and 45° jet angles on the axial staged flow field and the flame structure of different fuels were investigated when the jet equivalence ratio was 0.6 and the momentum flux ratio was 6. Results show that when the jet angle is 90°, there will be an obvious recirculating zone at the root of the jet, and the jet flames have periodic pulsations. When the jet angle is 45°, the shear layer will not produce a significant recirculating zone at the root of the jet, the jet flame burn is more stable, and the chemical residence time of the fuel in the low-speed zone is shorter, which has better adaptability for hydrogen fuel with fast flame propagation speed and easy tempering. The doping of methane fuel with hydrogen increases the propagation speed of the jet flame. With the increase of hydrogen doping ratio, the jet flame gradually changes from a detached flame to a continuous flame, the jet flame branch appears on the windward side, the length of the reaction zone is shortened and smaller, the flame intensity is enhanced, and the flame root moves to the nozzle outlet and finally attaches to the jet nozzle outlet.
  • Study on the Effect of Hydrogen Mixing Ratio on Combustion Instability of Spiral Micro-mixing-swirl Compound Nozzle
    QIU Chengxu, LIU Jiaqi, JIANG Dongpo, FENG Yongzhi, WANG Hui
    2024, 44(9): 1393-1400. https://doi.org/10.19805/j.cnki.jcspe.2024.240205
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    In order to achieve the goal of low emission for gas turbines, the combustion instability characteristics of spiral micro-mixing-swirl composite nozzles under different hydrogen mixing ratios were experimentally studied. Under constant output power, the pressure oscillation state of combustion chamber and precombustion stage in the range of 0%-100% hydrogen mixing ratio was investigated. Results show that under equivalent ratio of main combustion stage of 0.45, the amplitude of pressure oscillation in the combustion chamber increases first and then decreases with the increase of hydrogen mixing ratio. When the hydrogen mixing ratio is 70%, two frequency pressure oscillation signals of 2 903.4 and 4 490.2 Hz appear in the combustion chamber. The two frequency pressure oscillations produced by the combustion at the hydrogen mixing ratio coincide with the natural acoustic mode frequencies of the combustion chamber, and then form standing waves. The first-order acoustic mode frequency of the precombustion stage is 5 450 Hz, and the sound waves in this frequency band generated by the combustion zone propagate to the precombustion stage to form standing waves, resulting in the peak pressure pulsation near 5 400 Hz in the precombustion stage. In contrast to the combustion chamber, the pressure pulsation amplitude is the smallest under the 70% hydrogen mixing condition. Considering the pressure pulsation of combustion chamber and precombustion stage, it is considered that the optimal hydrogen mixing ratio of main combustion stage is in the range of 30%-60%.
  • Influence of Swirl on Combustion Characteristics of Hydrogen Micro-mixing Diffusion Flame
    SHI Ting, LIU Yi, JIA Shiqi, GE Bing, DUAN Dongxia, ZANG Shusheng
    2024, 44(9): 1401-1407. https://doi.org/10.19805/j.cnki.jcspe.2024.240197
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    Experimental studies were conducted on two types of micro-mixing diffusion combustors, one with a swirl number of 0.62 and another one without swirl, under the equivalence ratio from 0.3 to 0.5. The influences of swirl on the flow field distribution, flame structure, NOx concentration, and combustion instability of micro-mixing diffusion combustion were investigated experimentally. The methods of OH* chemiluminescence and particle image velocimetry (PIV) were used to capture flames and flow structures. Results show that adding swirl can reduce the flame height by 44% and shorten the residence time by changing the flow field structure, ultimately achieving a 63.4% reduction in NOx emissions. Without swirl, the main driving factor of micro-mixed diffusion flame pulsation is the formation of radial expansion zone under high equivalent ratios, while swirling flow can inhibit the formation of radial expansion zone, so as to achieve the effect of suppressing combustion oscillation in a wide load range.
  • Numerical Study on Combustor Liner of F-class Gas Turbine Considering the Effect of Thermal Barrier Coatings and Cooling Structures
    XIAO Junfeng, GAO Song, YAN An, SHANGGUAN Bo, ZHANG Meng, HE Wei, LI Xiaofeng, ZHANG Boyao
    2024, 44(9): 1408-1415. https://doi.org/10.19805/j.cnki.jcspe.2024.240192
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    Taking the combustor liner of F-class gas turbine as the research object, analysis was carried out on the internal flow field, temperature field and stress field of the combustor liner under rating operation conditions based on fluid-thermal-solid coupling method, considering the effect of thermal barrier coatings and cooling structures on the aerodynamic heat transfer of the combustor liner. The results of numerical analysis were compared with the actual damage situation of the combustor liner. Results show that the high stress areas are basically consistent with the actual damaged regions of the combustor liner, thus the fluid-thermal-solid coupling method can be used to predict the damage situation of the combustor liner. The ceramic layers of the thermal barrier coatings at different locations have similar insulation effect. Both the substrate and the ceramic layers of the thermal barrier coatings in the vicinity of the cooling structures are areas of high stress.
  • Coupled Heat Transfer and Cooling Characteristics of High Temperature and High Humidity Turbine for Hydrogen-fired Gas Turbine
    REN Jing, LI Xueying, HUANG Xinyu, WANG Wenping, SUN Peng, LI Mingfei
    2024, 44(9): 1416-1423. https://doi.org/10.19805/j.cnki.jcspe.2024.240231
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    The flow heat transfer and cooling characteristics of hydrogen-fired gas turbine were analyzed under coupled action of heat conduction/convection/radiation. A weighted sum of gray gases (WSGG) model was developed to calculate the high ratio of water vapor and carbon dioxide partial pressure. Results show that the increase of water vapor content in the working fluid of hydrogen-fired gas turbine leads to the increase of metal wall temperature. After adding the influence of radiation, the effect of water vapor and carbon dioxide contents on heat transfer is opposite, which is mainly due to the fact that carbon dioxide has a stronger convective heat transfer capacity than water vapor, while water vapor has a stronger radiative capacity than carbon dioxide. Meanwhile, in the hydrogen-fired turbine cooling coupled system with three heat transfer modes of convection-conduction-radiation, the film cooling velocity field is almost unaffected, while the temperature field is deeply affected by coupling effect and radiation. The gas film cooling efficiency under coupled condition defined in this paper can characterize the gas film cooling performance under the condition of hydrogen combustion. Therefore, in the design of hydrogen combustion turbine cooling, the thermal load deterioration caused by hydrogen combustion should be included in the design variables.
  • Research on the Effect of Clocking Effect on the Boundary Layer Flow of Highly-loaded Low-pressure Turbines
    ZOU Zhengping, SHENG Ran, DU Pengcheng
    2024, 44(9): 1424-1436. https://doi.org/10.19805/j.cnki.jcspe.2024.240195
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    In multi-stage turbines, the clocking effect and calming effect would have significant impacts on the internal flow and aerodynamic efficiency. Taking a two-stage highly-loaded low-pressure turbine as the research object, and the high-precision large eddy simulation (LES) method was utilized to simulate the unsteady flow fields at the mid-section of the turbine blade. The time-averaged flow field, time-averaged aerodynamic performance and unsteady evolution of the boundary layer flow in the second-stage stator under five different stator clocking positions were analyzed. Results show that the different clocking positions of the first-stage stator have a significant impact on the total pressure loss of the second-stage stator, with changes in total pressure loss reaching up to 20% across different clocking positions. The differences in flows under different clocking positions are mainly attributed to the transport process of the wake in the blade rows, as well as changes in boundary layer transition induced by the interaction between the wake and boundary layer. When the wake of the first-stage stator hits the leading edge of the second-stage stator, the separation zone on the suction surface of the second-stage stator is significantly reduced, resulting in the minimum total pressure loss. Conversely, when the wake of the first-stage stator enters the blade passage from a position approximately 40% of the pitch distance from the suction side of the second-stage stator, multiple separation bubbles appear at the rear part of the suction side of the second-stage stator during a rotor passing period, leading to the maximum time-averaged total pressure loss.
  • Experimental and Numerical Study on Flow and Heat Transfer in the Outer Ring of a High-pressure Turbine
    YIN Linlin, LU Yuanli, WU Weilong, CHEN Yun
    2024, 44(9): 1437-1445. https://doi.org/10.19805/j.cnki.jcspe.2024.240219
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    In order to obtain the influence of different cold air parameters on the flow and temperature characteristics of the outer ring of a high-pressure turbine, heating and pressurization test methods were used to study the temperature field distribution and cooling efficiency of the outer ring under different cold air to gas flow ratios. The numerical simulation results were compared and analyzed with the experimental results. In addition, the influence of different gas inlet angle conditions on the flow heat transfer in the outer ring was numerically simulated. Results show that the numerical simulation results are in good agreement with the experimental results. The cooling efficiency results using temperature averaging at measure points are slightly higher than the experimental results. There is a clear separation and poor periodicity in the flow of the main gas flow in the outer ring test environment under the test conditions. By adding supporting elements on the sides of the outer ring block, the flow periodicity in the outer ring block area is effectively improved. When the inlet flow direction is consistent with the outlet flow direction of the gas film hole, the cold air coverage effect is better, and within a certain angle range, the impact on the cooling efficiency is relatively small. There is an optimal matching value between the inlet flow angle and the outlet flow direction of the gas film hole.
  • Investigations on the Film Cooling Effectiveness and Aerothermal Performance of the Turbine Blade Squealer Tip with Rib Layouts
    ZHOU Zuohong, CHENG Guoqiang, XU Chengtian, KONG Xianglin, LI Zhigang, LI Jun
    2024, 44(9): 1446-1458. https://doi.org/10.19805/j.cnki.jcspe.2024.240098
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    This study focuses on the squealer tip film cooling design of turbine blades, presenting three layouts: two with full ribs, one with a full rib and a half-rib on the pressure side, and one with a half-rib on the suction side. Using numerical simulations through three-dimensional Reynolds-Averaged Navier-Stokes (RANS) equations and a standard k-ω turbulence model,the heat transfer and cooling performance of grooved blade tips with two full rib layouts were studied under four different blowing ratios.The aerodynamic and heat transfer performance, as well as film cooling effectiveness of blade squealer tip with different rib layouts and typical squealer tip without rib layout were compared and analyzed at blow ratio 1.0 condition. Results show that the distribution of heat transfer coefficient at the blade tip predicted by numerical methods is in good agreement with the experimental measurement results, which verifies the reliability of the numerical method; at a blowing ratio of 1.0, the squealer tip with full ribs exhibits the highest average film cooling effectiveness, surpassing the typical groove design by 2.2% in effectiveness. The layout with half ribs on the pressure side shows the lowest average heat transfer coefficient and total pressure loss. Rib configurations markedly alters the flow structure over the leaf top, thereby affecting its aerothermal performance and film cooling effectiveness, with the full rib layout displaying optimal overall aerothermal performance and cooling effectiveness.
  • PINN-based Inversion Learning of Turbulence Model for Film Cooling
    ZHANG Zhen, SU Xinrong, YUAN Xin
    2024, 44(9): 1459-1465. https://doi.org/10.19805/j.cnki.jcspe.2024.240201
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    Due to the complexity of turbulent flow problems for film cooling, the traditional Reynolds average Navier-Stokes (RANS) method tends to underestimate the intensity of turbulent thermal diffusion, leading to inaccurate prediction of cooling effectiveness. A framework based on physics-informed neural network (PINN) was therefore proposed, and a data-driven neural network model of turbulent Prandtl number was built based on RANS flow data and large eddy simulation(LES) temperature data. After implementing this model into a RANS solver, the intensity of turbulent thermal diffusion could be adjusted dynamically and a temperature distribution highly consistent with LES results was obtained. Results show that PINN is an effective method to build a data-driven turbulence model and modeling of turbulent Prandtl number can effectively improve the accuracy of RANS temperature prediction.
  • Multi-scale Structural Strength Analysis of the Contact Interface of the Hirth Teeth of a Gas Turbine Rotor Disk Under Complex Loads
    ZHU Guangya, WANG Chongyu, XIE Yonghui, ZHANG Di
    2024, 44(9): 1466-1472. https://doi.org/10.19805/j.cnki.jcspe.2024.240076
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    As the heart of the gas turbine, the central rod-fastened rotor operates under harsh conditions with frequent incidents, necessitating a rigorous exploration of its strength under complex contact states across multiple scales and loads to ensure the safe functioning of the disc structure. Employing a rough surface contact model and three-dimensional finite element methods, a thermo-mechanical coupling analysis model for the gas turbine disc's Hirth tooth contact interface was developed, incorporating microscale interface dimensions and surface roughness. Results show that the maximum equivalent stress of the end face teeth decreases with the increase of the root fillet radius and the decrease of the pressure angle; the maximum equivalent stress and average contact pressure of the end face teeth decrease with the increase of surface roughness.
  • Analysis on Thermodynamic Performance of a Novel Gas Turbine System with High Effective Utilization of Bleed Air Cooling
    CHEN Qiang, WANG Kailin, JIANG Wenbin, QUE Xiaobin, YU Han, WU Wentao
    2024, 44(9): 1473-1481. https://doi.org/10.19805/j.cnki.jcspe.2024.240245
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    To improve the thermodynamic performance of the heavy duty gas turbine with bleed air, a novel gas turbine system with high effective utilization of bleed air energy was proposed, and the change of thermodynamic performance was researched. Taking the performance data of a traditional typical F-class gas turbine under different ambient temperature conditions as the comparison reference, for the novel gas turbine with high effective bleed air cooling, the changes of performance indicators of the total system were analyzed with different design parameters of cooling system by numerical simulation, while the thermodynamic performances under three operation modes were calculated and compared. Results show that the temperature of bleed air from compressor can be effectively decreased by adopting the novel gas turbine system with high effective utilization of bleed air cooling, and the thermodynamic performance of gas turbine is further improved. Under summer condition, when the inlet air temperature is cooled to 30, 20, and 15 ℃, respectively, the output power is increased by 25.92, 40.49, and 48.22 MW, and the efficiency of gas turbine is improved by 0.78, 1.19, and 1.40 percentage points.
  • Impact of Key Parameters on the Thermodynamic Performance of Heavy-duty Gas Turbine with Hydrogen Blended Fuel
    ZHU Zhijie, XU Qian, XU Wangren, SHI Jinyuan
    2024, 44(9): 1482-1492. https://doi.org/10.19805/j.cnki.jcspe.2024.240270
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    In order to investigate the impact of key parameters on the thermodynamic performance of both the overall and critical components of a hydrogen-blended heavy-duty gas turbine, a thermodynamic performance calculation model was established,and the definitions and settings of the key parameters in the moldel were explained. By examining different hydrogen blending ratios, turbine inlet temperatures, compressor pressure ratios, and cooling air volumes, the study assessed their influences on the power output and thermal efficiency of gas turbine. Additionally, changes in turbine aerodynamic parameters under different hydrogen blending ratios were analyzed, and the mechanisms behind the impact of hydrogen blending on gas turbine performance were further revealed. The results show that the mixing ratio of hydrogen, turbine inlet temperature, pressure ratio and cooling air quantity are the key parameters that affect the performance of heavy duty hydrogen blended gas turbine; and the changes in aerodynamic parameters of the turbine such as turbine flow angle and outlet Mach number caused by the hydrogen blending ratio changing will affect the aerodynamic performance of the turbine and the thermodynamic performance of the gas turbine.
  • Performance Study and Economic Analysis of Integrated Energy Systems Based on SOFC/GT and Hydrogen-blended Natural Gas
    SUN Haozhe, ZHANG Hui, SHENG Mingjun, DAI Shenhua, WANG Yuzhang
    2024, 44(9): 1493-1502. https://doi.org/10.19805/j.cnki.jcspe.2024.240266
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    An integrated energy system using solid oxide fuel cell (SOFC)/gas turbine (GT) as power generation device and hydrogen-doped natural gas as the fuel was proposed. The mathematical models of various types of energy utilization equipment, such as wind power generation, solar power generation, hydrogen production equipment, SOFC/GT system, energy conversion and storage equipment for electricity, heat, and cooling, carbon capture equipment, etc, were established. The performance and economy of the integrated energy system were studied considering various load balance constraints, equipment operation constraints and aiding in achieving the "dual carbon" targets. Results show that the power generation efficiency of SOFC/GT system increases from 60.36% to 64.79%, and the comprehensive energy utilization rate increases from 87.80% to 90.80% with the increase of fuel hydrogen blending ratio. When the system used renewable energy sources to produce hydrogen, the carbon emissions are the lowest, although carbon trading gains are considered, the high cost of hydrogen production leads to the highest operating costs.