Design and Development of a 14-Stage Axial Compressor for Industrial Gas Turbine

• DOI: 10.1115/gt2012-68524
• Publication Date: 2013-07-18T19:30:39Z
• Authors: Takuya Ikeguchi; Akinori Matsuoka; Yusuke Sakai; Yoshinobu Sakano; Kenichiro Yoshiura
• Keywords: Axial Compressor; Stall (fluid mechanics); Overall pressure ratio; Industrial gas; Tip clearance

A 14-stage axial flow compressor was newly designed and tested for developing an advanced industrial gas turbine. In order to achieve a high thermal efficiency required the new turbine, needed have significantly higher pressure ratio than those of existing engines. The design methodology used this based on automated airfoil geometric optimization system combined with 3D-CFD analysis, which resulted in arbitrary shaped most blade rows. multi-stage CFD analysis effectively adjust loading distribution along stages obtain proper stage matching. Before full development approximately two-thirds scaled rig tests were conducted verify aerodynamic structural reliability. test results first build indicated satisfactory level mass flow, but lack sufficient stall margin. second re-staggered vanes its result showed improvements both margin efficiency. prototype turbine also had been conducted. measured performance up from achieved target. Consequently, considered scale effects successful.