Validation of MISES Two-Dimensional Boundary Layer Code for High-Pressure Turbine Aerodynamic Design

Date

2009-07-01

Author

ANDREW, PHILIP
Kahveci, Harika Senem

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Avoiding aerodynamic separation and excessive shock losses in gas turbine turbomachinery components can reduce fuel usage and thus reduce operating cost. In order to achieve this, blading designs should be made robust to a wide range of operating conditions. Consequently, a design tool is needed-one that can be executed quickly for each of many operating conditions and on each of several design sections, which will accurately capture loss, turning, and loading. This paper presents the validation of a boundary layer code, MISES, versus experimental data from a 2D linear cascade approximating the performance of a moderately loaded mid-pitch section from a modern aircraft high-pressure turbine. The validation versus measured loading, turning, and total pressure loss is presented for a range of exit Mach numbers from approximate to 0.5 to 1.2 and across a range of incidence from -10 deg to +14.5 deg relative to design incidence. [DOI: 10.1115/1.2988165]

Subject Keywords

Mechanical Engineering

URI

https://hdl.handle.net/11511/38882

Journal

JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME

DOI

https://doi.org/10.1115/1.2988165

Collections

Department of Aerospace Engineering, Article

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Citation Formats

P. ANDREW and H. S. Kahveci, “Validation of MISES Two-Dimensional Boundary Layer Code for High-Pressure Turbine Aerodynamic Design,” JOURNAL OF TURBOMACHINERY-TRANSACTIONS OF THE ASME, pp. 0–0, 2009, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/38882.