基于累积服役2700h后某燃气轮机叶片显微组织的退化判断其服役温度
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摘要
将累积运行2 700h后DZ411合金燃气轮机叶片的显微组织与原始组织进行对比分析,结合DZ411合金棒在900℃长时热暴露和在850℃不同应力(220,260,280,300MPa)持久后组织中γ′相的变化,对燃气轮机叶片的服役温度进行评估。结果表明:累积运行2 700h后,叶片中大部分位置的显微组织退化损伤不明显,推断这些位置的运行温度低于850℃;而在近叶尖截面进气边的少量区域中γ′相发生少量退化,推断该区域可能曾经历短时高温,最高温度超过900℃。
Microstructure of gas turbine blade made of DZ411 alloy after cumulative operation for 2 700 hwas analyzed and compared with the original microstructure.Combining with change ofγ′phase in microstructure of DZ411 alloy rod after long-term thermal exposure at 900 ℃ and stress-rupture at 850 ℃ under different stresses(220,260,280,300 MPa),service temperatures of the gas turbine blade were evaluated.The results show that after cumulative operation for 2 700 h,the microstructure at most positions in the blade exhibited no obvious degradation,indicating that the operation temperature at these positions was below 850 ℃.In a small number of areas at leading edge on section near blade tip,theγ′phase degradation at early stage was observed,and therefor it was deduced that these areas might be subjected to short-term high temperatures and the maximum temperature was higher than 900℃.
Microstructure of gas turbine blade made of DZ411 alloy after cumulative operation for 2 700 hwas analyzed and compared with the original microstructure.Combining with change ofγ′phase in microstructure of DZ411 alloy rod after long-term thermal exposure at 900 ℃ and stress-rupture at 850 ℃ under different stresses(220,260,280,300 MPa),service temperatures of the gas turbine blade were evaluated.The results show that after cumulative operation for 2 700 h,the microstructure at most positions in the blade exhibited no obvious degradation,indicating that the operation temperature at these positions was below 850 ℃.In a small number of areas at leading edge on section near blade tip,theγ′phase degradation at early stage was observed,and therefor it was deduced that these areas might be subjected to short-term high temperatures and the maximum temperature was higher than 900℃.
引文
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[2]CHANG J C,YUN Y H,CHOI C,et al.Failure analysis of gas turbine buckets[J].Engineering Failure Analysis,2003,10(5):559-567.
[3]DYE D,MA A,REED R C.Numerical modelling of creep deformation in a CMSX-4 single crystal superalloy turbine blade[C]//Superalloys 2008.Warrendale,PA:TMS,2008:911-919.
[4]JIANG X W,WANG D,XIE G,et al.The effect of long-term thermal exposure on the microstructure and stress rupture property of a directionally solidified Ni-based superalloy[J].Metallurgical and Materials Transactions A,2014,45(13):6016-6026.
[5]LEE H S,YOO K B,KIM D S,et al.Effects of thermal exposure on microstructure and mechanical properties of Ni based superalloy GTD111[J].Advanced Materials Research,2011,275:31-34.
[6]QIN X Z,GUO J T,YUAN C,et al.Effects of long-term thermal exposure on the microstructure and properties of a cast Ni-base superalloy[J].Metallurgical and Materials Transactions A,2007,38(12):3014-3022.
[7]AGHAIE-KHAFRI M,FARAHANY S.Creep life prediction of thermally exposed rene 80 superalloy[J].Journal of Materials Engineering and Performance,2010,19(7):1065-1070.
[8]CHOI B G,KIM I S,KIM D H,et al.Temperature dependence of MC decomposition behavior in Ni-base superalloy GTD 111[J].Materials Science and Engineering:A,2008,478(1/2):329-335.
[9]YANG J X,ZHENG Q,SUN X F,et al.Morphological evolution ofγ′phase in K465superalloy during prolonged aging[J].Materials Science and Engineering:A,2007,457(1/2):148-155.
[10]LVOV G,LEVIT V I,KAUFMAN M J.Mechanism of primary MC carbide decomposition in Ni-base superalloys[J].Metallurgical and Materials Transactions A,2004,35(6):1669-1679.
[11]LVOVA E,NORSWORTHY D.Influence of service-induced microstructural changes on the aging kinetics of rejuvenated Ni-based superalloy gas turbine blades[J].Journal of Materials Engineering and Performance,2001,10(3):299-312.
[12]KOUL A K,CASTILLO R.Assessment of service induced microstructural damage and its rejuvenation in turbine blades[J].Metallurgical Transactions A,1988,19(8):2049-2066.
[13]KIM K M,PARK J S,LEE D H,et al.Analysis of conjugated heat transfer,stress and failure in a gas turbine blade with circular cooling passages[J].Engineering Failure Analysis,2011,18(4):1212-1222.
[14]姜祥伟.重型工业燃气轮机涡轮叶片的服役损伤与寿命预测研究[D].北京:中国科学院大学,2015:60-62.
[15]PRIKHODKO S V,ARDELL A J.Coarsening ofγ′in Ni-Al alloys aged under uniaxial compression:I.Early-stage kinetics[J].Acta Materialia,2003,51(17):5001-5012.
[16]ARDELL A J,PRIKHODKO S V.Coarsening ofγ′in Ni-Al alloys aged under uniaxial compression:II.Diffusion under stress and retardation of coarsening kinetics[J].Acta Materialia,2003,51(17):5013-5019.
[17]PRIKHODKO S V,ARDELL A J.Coarsening ofγ′in Ni-Al alloys aged under uniaxial compression:III.Characterization of the morphology[J].Acta Materialia,2003,51(17):5021-5036.
[18]ALTINCEKIC A,BALIKCI E.Precipitate size in the superalloy IN738LC during compression creep[J].Metallurgical and Materials Transactions A,2013,44(6):2487-2498.
[19]SONDHI S K,DYSON B F,MCLEAN M.Tensioncompression creep asymmetry in a turbine disc superalloy:Roles of internal stress and thermal ageing[J].Acta Materialia,2004,52(7):1761-1772.
[20]STAROSTINA N V,PRIKHODKO S V,ARDELL A J,et al.Coarsening of Ni3Ge precipitates in Ni-Ge alloys aged under uniaxial compression[J].Materials Science and Engineering:A,2005,397(1/2):264-270.