热购娱乐网址gm777.top是一家集热购娱乐网址,热购娱乐网址,热购娱乐网址于一体的综合性娱乐公司,为玩家提供全方位的游戏体验,诚邀您的体验。

[1]林阿強,鄭群,張海,等.射流冷卻對航空發動機壓氣機的特性分析[J].哈爾濱工程大學學報,2019,40(09):1608-1615.[doi:10.11990/jheu.201804021]
 LIN Aqiang,ZHENG Qun,ZHANG Hai,et al.Analysis of mass injection cooling on aero-engine compressor characteristics[J].hebgcdxxb,2019,40(09):1608-1615.[doi:10.11990/jheu.201804021]
點擊復制

射流冷卻對航空發動機壓氣機的特性分析(/HTML)
分享到:

《哈爾濱工程大學學報》[ISSN:1006-6977/CN:61-1281/TN]

卷:
40
期數:
2019年09期
頁碼:
1608-1615
欄目:
出版日期:
2019-09-05

文章信息/Info

Title:
Analysis of mass injection cooling on aero-engine compressor characteristics
作者:
林阿強 鄭群 張海 姜玉廷
哈爾濱工程大學 動力與能源工程學院, 黑龍江 哈爾濱 150001
Author(s):
LIN Aqiang ZHENG Qun ZHANG Hai JIANG Yuting
College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, China
關鍵詞:
高馬赫數航空發動機壓氣機特性預冷段蒸發冷卻高溫進氣
分類號:
V235.1
DOI:
10.11990/jheu.201804021
文獻標志碼:
A
摘要:
針對高馬赫數下航空發動機高溫進氣問題,本文建立了高空環境下預冷段-壓氣機內氣霧蒸發冷卻的數學模型;跉W拉-拉格朗日多相流數值方法分析了不同噴霧條件和高空環境時壓氣機特性變化。結果表明:在高空高馬赫數環境下,噴水冷卻可以增加進氣流量、抑制溫升、增大總壓比;在一定范圍內較大的噴水量和較小的液滴尺寸,有利于降低總溫比、提高總壓比,同時有利于降低壓氣機壓縮耗功及增加效率。因此,航空發動機壓氣機前增設進氣預冷段進行射流冷卻,可以有效改善壓氣機的工作特性。

參考文獻/References:

[1] 鄒正平, 劉火星, 唐海龍, 等. 高超聲速航空發動機強預冷技術研究[J]. 航空學報, 2015, 36(8):2544-2562.ZOU Zhengping, LIU Huoxing, TANG Hailong, et al. Precooling technology study of hypersonic aeroengine[J]. Acta aeronautica et astronautica sinica, 2015, 36(8):2544-2562.
[2] WANG Zhenguo, WANG Yuan, ZHANG Jianqiang, et al. Overview of the key technologies of combined cycle engine precooling systems and the advanced applications of micro-channel heat transfer[J]. Aerospace science and technology, 2014, 39:31-39.
[3] PRESTON C, VLADIMIR B, TERRY S, et al. MIPCC technology development[C]//12th AIAA International Space Planes and Hypersonic Systems and Technologies. Reston, 2003.
[4] SIVO J N, WANHAINEN J P, JONES W L. The effect of compressor-inlet water injection on engine and afterburner performance. NACA-RM-E58d03b[R]. Cleveland, Ohio:Lewis Flight Propulsion Laboratory, 1958.
[5] KELLE D E, KUCZERA H. Saenger space transportation system - progress report[J]. Space technology, 1992, 12(4):353-367.
[6] CARTER P, BALEPIN V. Mass injection and precompressor cooling engines analyses[C]//38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Indianapolis, Indiana, 2002.
[7] BALEPIN V, LISTON G. The steamJetTM:Mach 6+ turbine engine with inlet air conditioning[C]//37th Joint Propulsion Conference and Exhibit. Salt Lake City, UT, 2001.
[8] LIN Aqiang, ZHENG Qun, JIANG Yuting, et al. Sensitivity of air/mist non-equilibrium phase transition cooling to transient characteristics in a compressor of gas turbine[J]. International journal of heat and mass transfer, 2019, 137:882-894.
[9] 柴柏青, 徐國印, 鄭群, 等. 濕壓縮過程中水滴的運動分析[J]. 哈爾濱工程大學學報, 2017, 38(2):222-229.CHAI Baiqing, XU Guoyin, ZHENG Qun, et al. Motion analysis of water droplets during wet compression[J]. Journal of Harbin Engineering University, 2017, 38(2):222-229.
[10] WHITE A J, MEACOCK A J. Wet compression analysis including velocity slip effects[C]//Proceedings of ASME Turbo Expo 2010:Power for Land, Sea, and Air. Glasgow, UK, 2010:953-963.
[11] NEUPERT N, OBER B, JOOS F. Experimental investigation on droplet behavior in a transonic compressor cascade[J]. Journal of turbomachinery, 2014, 137(3):031009.
[12] LIN Aqiang, SUN Yonggang, ZHANG Hai, et al. Fluctuating characteristics of air-mist mixture flow with conjugate wall-film motion in a compressor of gas turbine[J]. Applied thermal engineering, 2018, 142:779-792.
[13] KIM K H, PEREZ-BLANCO H. An assessment of high-fogging potential for enhanced compressor performance[C]//ASME Turbo Expo 2006:Power for Land, Sea, and Air. Barcelona, Spain, 2006.
[14] WHITE A J, MEACOCK A J. An evaluation of the effects of water injection on compressor performance[J]. Journal of engineering for gas turbines and power, 2004, 126(4):748-754.
[15] LIN Aqiang, ZHOU Jie, FAWZY H, et al. Evaluation of mass injection cooling on flow and heat transfer characteristics for high-temperature inlet air in a MIPCC engine[J]. International journal of heat and mass transfer, 2019, 135:620-630.
[16] MOORE R D, REID L. Performance of single-stage axial-flow transonic compressor rotor and stator aspect ratios of 1.19 and 1.26 respectively, and with design pressure ratio of 2.05. NASA TP-1659[R]. NASA, 1980.
[17] LIU Chunlei, ZHENG Qun, WANG Qi, et al. Sensitivity analysis of multistage compressor characteristics under the spray atomization effect using a CFD model[J]. Energies, 2019, 12(2):301.
[18] JIANG Yuting, ZHENG Qun, DONG Ping, et al. Conjugate heat transfer analysis of leading edge and downstream mist-air film cooling on turbine vane[J]. International journal of heat and mass transfer, 2015, 90:613-626.
[19] LIN A Q, ZHOU J, TIAN X J, et al. Effective boundary conditions and numerical method for flow characteristics of aeroengine compressor at high Mach flight[J]. Journal of applied fluid mechanics, 2019, 12(3):845-855.

相似文獻/References:

[1]胡杰鑫,謝里陽,邢宇,等.基于FMECA的自動繪制故障樹方法[J].哈爾濱工程大學學報,2017,38(07):1162.[doi:10.11990/jheu.201604024]
 HU Jiexin,XIE Liyang,XING Yu,et al.FMECA-based FTA automatic fault tree drafting[J].hebgcdxxb,2017,38(09):1162.[doi:10.11990/jheu.201604024]
[2]金業壯,王德友,聞邦椿.航空發動機雙轉子系統碰摩故障的仿真研究[J].哈爾濱工程大學學報,2017,38(12):1872.[doi:10.11990/jheu.201703060]
 JIN Yezhuang,WANG Deyou,WEN Bangchun.Dynamic simulation on double-rotor system of aeroengine with rubbing fault[J].hebgcdxxb,2017,38(09):1872.[doi:10.11990/jheu.201703060]

備注/Memo

備注/Memo:
收稿日期:2018-04-08。
基金項目:國家自然科學基金項目(51809065);中央高;究蒲袠I務費專項資金項目(3072019GIP0304;3072019CFJ0309).
作者簡介:林阿強,男,博士研究生;鄭群,男,教授,博士生導師.
通訊作者:鄭群,E-mail:zhengqun@hrbeu.edu.cn.
更新日期/Last Update: 2019-09-06
热购娱乐网址