Thermal fatigue behavior of nickle based superalloy GH536

陈静; 石多奇; 苗国磊; 易靖钦; 杨晓光

doi:10.13224/j.cnki.jasp.2017.06.014

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Thermal fatigue behavior of nickle based superalloy GH536

更新时间：2026-07-07

- Thermal fatigue behavior of nickle based superalloy GH536
- Vol. 32, Issue 6, Pages: 1381-1387(2017)
- 作者机构：
  
  1. 北京航空航天大学能源与动力工程学院,北京,100191
  2. 先进航空发动机协同创新中心,北京,100191
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2017.06.014
  CLC：
- Published：2017
- 稿件说明：
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陈静, 石多奇, 苗国磊, 易靖钦, 杨晓光. 镍基高温合金GH536的热疲劳行为[J]. 航空动力学报, 2017, 32(6): 1381-1387.

doi: 10.13224/j.cnki.jasp.2017.06.014
陈静, 石多奇, 苗国磊, 易靖钦, 杨晓光. 镍基高温合金GH536的热疲劳行为[J]. 航空动力学报, 2017, 32(6): 1381-1387. DOI： 10.13224/j.cnki.jasp.2017.06.014.

doi: 10.13224/j.cnki.jasp.2017.06.014 DOI：

摘要

燃烧室火焰筒作为航空发动机的热端关键结构件，在工作过程中受到复杂的循环温度载荷，使其承受热疲劳损伤.对火焰筒常用镍基高温合金GH536的热疲劳行为进行试验研究.根据火焰筒结构和载荷特征，设计了中心孔平板试样以及热疲劳试验，研究了热疲劳载荷条件下GH536平板的裂纹萌生及扩展规律，揭示了GH536的热疲劳破坏机理.研究发现：①热疲劳裂纹以穿晶模式萌生，以沿晶方式扩展并断裂；②随着热疲劳试验中上限温度的升高，裂纹的萌生寿命缩短，裂纹扩展速率加快，试样在800℃时的热疲劳裂纹萌生寿命是900℃裂纹萌生寿命的4.5倍.

Abstract

The flame tube of combustion chamber is the key structure of the aero-engine

and subjected to complex cyclic temperature load which will cause thermal fatigue. The thermal fatigue behavior of nickle based superalloy GH536 always used in flame tube was investigated. According to the characteristic load and structure of the flame tube

the specimen of a flat plate with a central hole and the thermal fatigue test were designed to study the crack initiation

crack propagation and thermal fatigue damage mechanism of the GH536 plate specimen under the thermal fatigue load condition. The study indicates: (1) the thermal fatigue cracks initiate transgranularly

develop and propagate intergranularly; (2) the crack propagation rate becomes faster and the crack initiation life becomes shorter with the increase of upper temperature in the thermal fatigue test. Thermal fatigue crack initiation life at 800℃ is 4.5 times of the crack initiation life at 900℃.

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