INVESTIGATION OF ROTOR BLADE ROUGHNESS EFFECTS ON TURBINE PERFORMANCE

被引：39

作者：

BOYNTON, JL ^{[1
]}

TABIBZADEH, R ^{[1
]}

HUDSON, ST ^{[1
]}

机构：

[1] NASA,GEORGE C MARSHALL SPACE FLIGHT CTR,HUNTSVILLE,AL 35812

来源：

JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME | 1993年 / 115卷 / 03期

关键词：

D O I：

10.1115/1.2929298

中图分类号：

TH [机械、仪表工业];

学科分类号：

0802 ;

摘要：

The cold air test program was completed on the SSME (Space Shuttle Main Engine) HPFTP (High-Pressure Fuel Turbopump) turbine with production nozzle vane rings and polished coated rotor blades with a smooth surface finish of 30 muin. (0.76 mum) rms (root mean square). The smooth blades were polished by an abrasive flow machining process. The test results were compared with the air test results from production rough-coated rotor blades with a surface finish of up to 400 muin. (10.16 mum) rms. Turbine efficiency was higher for the smooth blades over the entire range tested. Efficiency increased 2.1 percentage points at the SSME 104 percent RPL (Rated Power Level) conditions. This efficiency improvement could reduce the SSME HPFTP turbine inlet temperature by 57 R (32 K), increasing turbine durability. The turbine flow parameter increased and the midspan outlet swirl angle became more axial with the smooth rotor blades.

引用

页码：614 / 620

页数：7