摘要
由法国SNECMA公司和美国GEAE集团组成的CFM国际公司在CFM56发动机研制一开始就努力缩小单级高压涡轮叶片的叶尖间隙而又使其摩擦最小。各型CFM56发动机的验证试验表明,叶尖间隙增大对发动机性能不利。 现在,美国通用电气(GE)公司研制了一种小型不冷却的间隙测量装置,它可以在运转条件下测量高温环境下的高压涡轮叶片的叶尖间隙。该工具与新的分析技术相结合,导致CFM56发动机及其短舱的某些设计更改,通过机匣圆度与转子同心度的改善,发动机性能和性能保持能力得到提高。
Since the launch of the CFM56 engine program there has been an'ongoing effort to minimize the single stage high pressure turbine blade tip clearance and tip rubs . Loss of blade tip clearance has been demonstrated on all CFM56 models to have a significant impact on engine performance. Today, GE is better able to optimize clearance with newly developed, small uncooled devices capable of measuring running blade clearance in high temperature environment. These measurement tools and new analytical technigues have led to several design changes to CFM56 engine / nacelle systems which improve casing roundness and rotor concentricity. The changes improve new engine performance and performance retention and provide better understanding of non-axisymmetric effects . Here, J . J . Stow and D . Leach let us into the secret for centering the rotor and rounding up the shroud .
出处
《国际航空》
北大核心
1994年第4期53-55,共3页
International Aviation
