| 1. | Turbine disk is one of the key parts of aero - engine
涡轮盘是航空发动机具有关键特性的核心部件之一。 |
| 2. | A low - cycle fatigue life model for simplified turbine disk simulation specimens of powder metallurgy superalloys
粉末冶金涡轮盘简单模拟件低周疲劳寿命研究 |
| 3. | So it is essential to study the effect of inclusion on the strength and life of pm superalloy turbine disks
因此研究夹杂对粉末高温合金涡轮盘强度与寿命的影响十分必要。 |
| 4. | For a turbine disk , the growth life of crack is the shortest when the inclusions are at the edge of the center hole
对某发动机涡轮盘而言，中心孔边存在夹杂时，裂纹扩展寿命最短。 |
| 5. | So it establishes the essential foundation for studying the crack ' s initiation life of powder metallurgy turbine disks with inclusions
为深入研究含夹杂粉末冶金涡轮盘裂纹萌生寿命打下必要的基础。 |
| 6. | The life of the initial crack expanding to the visible crack is the majority of the life of fgh95 pm superalloy turbine disks containing alo3 inclusions
并建议将第一阶段裂纹扩展寿命作为含al _ 2o _ 3夹杂的fgh95粉末高温合金涡轮盘的寿命。 |
| 7. | Its structure is very complex , particularly the wall of new turbine disk is thin , physical dimension mostly is arc switching . there are many dented surfaces and they need high roughness demanding
它的结构复杂,尤其是新型的涡轮盘壁薄、结构尺寸多为圆弧转接,存在多处凹陷的内表面,并且表面粗糙度要求高。 |
| 8. | This paper is based on turbine disk polishing methods to conduct research . the designing idea , construction theory and scheme realization of the turbine disk digital control copy polishing equipment have been discussed
本文基于涡轮盘的抛光方法展开研究,论述了涡轮盘数控仿形抛光设备的设计思想、结构原理和实现方案。 |
| 9. | Turbine disks will endure higher temperature and higher stress due to increasing demanding on the performance , reliability and life of aeroengines , and traditional superalloys could n ' t meet the demand
随着对航空发动机性能、可靠性、寿命等要求的不断提高，发动机涡轮盘将承受更高的温度和应力，传统高温合金已不能满足这一要求。 |
| 10. | Powder metallurgy ( pm ) superalloys has the advantage of homogeneous organization , superfine grain , high yield strength and high elevated temperature fatigue strength , so it becomes the first choice material for the new turbine disks
而粉末高温合金材料具有组织均匀、晶粒细小、屈服强度高、高温疲劳性能好等优点，已成为新型涡轮盘的首选材料。 |
