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Research Papers

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

[+] Author and Article Information
Philip L. Andrew, Harika S. Kahveci

 GE Energy, Greenville, SC 29615

J. Turbomach 131(3), 031013 (Apr 10, 2009) (11 pages) doi:10.1115/1.2988165 History: Received April 05, 2008; Revised April 21, 2008; Published April 10, 2009

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 0.5 to 1.2 and across a range of incidence from 10deg to +14.5deg relative to design incidence.

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Copyright © 2009 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Grid type selection in MISES

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Figure 2

Blade loading at M2=1.14 and at design incidence (ie=0 deg) with different type grids

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Figure 3

Blade loading at M2=1.14 and at design incidence (ie=0 deg) with different node counts

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Figure 4

(a) Blade loading at the design incidence (ie=0 deg) for M2=0.96. (b) Blade loading at the design incidence (ie=0 deg) for M2=1.06. (c) Blade loading at design incidence (ie=0 deg) for M2=1.14. (d) Blade loading around the design exit Mach number (M2=1.08) with an incidence level of +10.0 deg. (e) Blade loading at the design exit Mach number (M2=1.05) with an incidence level of +14.5 deg. (f) Incidence sensitivity study around the design incidence (ie=0 deg, M2=1.14). (g) Incidence sensitivity study around the incidence level of +4.5 deg, M2=1.12.

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Figure 5

(a) The effect of AVDR on blade performance. (b) Sensitivity to AVDR on blade loading at low incidence level (ie=0 deg, M2=1.14). (c) Sensitivity to AVDR on blade loading at high incidence level (ie=+14.5 deg, M2=1.10).

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Figure 6

Error in Mach number predictions

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Figure 7

(a) Error in exit flow angle predictions. (b) Error trends in exit flow angle predictions at incidence levels of −10 deg, 0 deg, and +4.5 deg. (c) Error trends in exit flow angle predictions at high incidence.

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Figure 8

(a) Loss prediction at incidence levels of −10 deg, 0 deg, and +4.5 deg. (b) Loss prediction for the highest negative incidence, −10 deg. (c) Loss prediction at high incidence.

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Figure 9

(a) Comparison of two blade geometries, HS1A and HS1B. (b) HS1B blade loading for design incidence (ie=0 deg) at M2=1.14. (c) Comparison of MISES predictions for HS1A and HS1B at design incidence ie=0 deg, at M2=1.14. (d) HS1B blade loading for design incidence (ie=0 deg) at M2=0.50.

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Figure 10

(a) Reynolds number effect on performance at design incidence, ie=0 deg. (b) Reynolds number effect on transition onset on suction side at M2=1.14, ie=0 deg. (c) Reynolds number effect on transition, separation, and reattachment location on the pressure side at M2=1.14, ie=0 deg.

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Figure 11

Dawes code predictions (14)

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