Mechanical Design Considerations for a Low-Speed Axial Compressor Research Facility
Abstract
This research focused on designing the mechanical components of a low-speed axial compressor with cantilevered stators to investigate endwall flow phenomena in the rear stages of industrial gas turbine compressors. The data collected from this research facility will verify and increase the fidelity of CFD models used to design modern industrial gas turbine compressors for Siemens. Siemens provided the aerodynamic design for the compressor while Purdue was responsible for the inlet, exhaust, and casing designs. At design point, the four-stage compressor has a corrected mass flow rate of 20.16 kg/s (44.44 lbm), a corrected rotational speed of 1350 RPM, and a pressure ratio of 1.09. The compressor is 1.25 m (4.1 ft.) in diameter and has a 12.5 cm (4.92 in.) annulus height. The aerodynamic and mechanical designs of the inlet and exhaust were completed during this phase of research. The inlet and exhaust systems were designed to maximize work space within the lab. The throttle is also housed within the exhaust system and is controlled by three linear actuators. In addition, preliminary airfoil root designs and a casing design with a bearing traverse system, rotor inserts, and assembly process was prepared.
Degree
M.S.A.A.
Advisors
Key, Purdue University.
Subject Area
Design|Aerospace engineering|Mechanical engineering
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