Compact high speed turbomachines are complicated in aerodynamic design, mechanical construction, and fabrication. Design choices made during the aerodynamic design are strongly coupled to the mechanical integrity due to high rotational speeds and thermal gradients. In the present paper, aerodynamic design of a turbine with a low pressure ratio of 2:1 is presented. The turbine designed is a compact single stage machine, intended to be used in a 1 kN thrust small gas turbine engine. For the present work, the flow path is a constant hub and shroud radius rotor design, with a hub-tip ratio of 0.72. Overall guidelines used for parameter selection in velocity triangles, mean-line design and blade geometry are discussed. The turbine is designed for a mean section reaction of about 25%. Performance evaluation and flowfield analysis for the turbine geometries are carried out using a three-dimensional RANS solver. Performance characteristics of the turbine are generated for a range of pressure ratio at design speed. The intended efficiency of the turbine stage at design point is 88%. Challenges during the design process to obtain blade geometries with wide blade passage throat are put forth. The choices made in aerodynamic design which affect the ease of machining of the stator and rotor components are also brought out.
Aerodynamic Design of a Axial Turbine Stage for a Small Gas Turbine Engine
Lect.Notes Mechanical Engineering
24.07.2022
17 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch
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