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 which 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 2-D linear cascade approximating the performance of a moderately-loaded, mid-pitch section from a modern aircraft high-pressure turbine [1–2]. The validation versus measured loading, turning, and total pressure loss is presented for a range of exit Mach numbers from ≈ 0.5 to 1.2, and across a range of incidence from −10° to +14.5° relative to design incidence.
Skip Nav Destination
ASME Turbo Expo 2007: Power for Land, Sea, and Air
May 14–17, 2007
Montreal, Canada
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
0-7918-4795-0
PROCEEDINGS PAPER
Validation of MISES 2-D Boundary Layer Code for High Pressure Turbine Aerodynamic Design
Philip L. Andrew,
Philip L. Andrew
GE Gas Turbines, Greenville, SC
Search for other works by this author on:
Harika S. Kahveci
Harika S. Kahveci
GE Gas Turbines, Greenville, SC
Search for other works by this author on:
Philip L. Andrew
GE Gas Turbines, Greenville, SC
Harika S. Kahveci
GE Gas Turbines, Greenville, SC
Paper No:
GT2007-28123, pp. 879-893; 15 pages
Published Online:
March 10, 2009
Citation
Andrew, PL, & Kahveci, HS. "Validation of MISES 2-D Boundary Layer Code for High Pressure Turbine Aerodynamic Design." Proceedings of the ASME Turbo Expo 2007: Power for Land, Sea, and Air. Volume 6: Turbo Expo 2007, Parts A and B. Montreal, Canada. May 14–17, 2007. pp. 879-893. ASME. https://doi.org/10.1115/GT2007-28123
Download citation file:
15
Views
Related Proceedings Papers
Related Articles
Validation of MISES Two-Dimensional Boundary Layer Code for High-Pressure Turbine Aerodynamic Design
J. Turbomach (July,2009)
Predicting Transition in Turbomachinery—Part II: Model Validation and Benchmarking
J. Turbomach (January,2007)
Investigation of a Novel Secondary Flow Feature in a Turbine Cascade With End Wall Profiling
J. Turbomach (January,2005)
Related Chapters
Cavitation CFD Prediction for NACA0015 Hydrofoil Flow Considering Boundary Layer Characteristics
Proceedings of the 10th International Symposium on Cavitation (CAV2018)
Combined Cycle Power Plant
Energy and Power Generation Handbook: Established and Emerging Technologies
Designing Validation into Chromatography Processes
Validation Practices for Biotechnology Products