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Gas Turbines: Structures and Dynamics

Lifing Requirement Based Turbine Airfoil Mass Estimation Method in Conceptual Aero-Engine Design

[+] Author and Article Information
Stefan Bretschneider1

 MTU Aero Engines, Dachauer Strasse 665, 80995 München, Germany

Meinrad Weisser

Institute of Aircraft Propulsion Systems,  Universität Stuttgart, 70569 Stuttgart, Germany

Hermann Klingels, Fabian Donus

 MTU Aero Engines, Dachauer Strasse 665, 80995 München, Germany

1

Corresponding author.

J. Eng. Gas Turbines Power 134(8), 082502 (Jun 21, 2012) (7 pages) doi:10.1115/1.4005974 History: Received August 08, 2011; Accepted August 14, 2011; Published June 21, 2012; Online June 21, 2012

The presented paper describes a method developed by MTU Aero Engines to estimate the mass of turbine blades during multidisciplinary conceptual design studies based on a prescribed airfoil lifetime (Klingels, 2009, “Vordimensionierung von Turbinenschaufeln unter Berücksichtigung der Missionsanforderungen,” MTU Aero Engines, Technical Paper No. M09TET-0028, and Weisser, M., 2010, Erstellung und Implementierung eines erweiterten regelbasierten Verfahrens zur Schaufelauslegung mit Kühlluftmengenbestimmung in der Triebwerksvorauslegung, Diploma thesis, Institute of Aircraft Propulsion Systems, Universität Stuttgart, Stuttgart). For a given material, the target lifetime can be translated into a maximally allowable material temperature and stress level. While the latter has to be maintained by an appropriate mechanical design of the turbine blades, the material temperature needs to be established by sufficient cooling air. The predominant life-limiting effects are taken into account to determine the allowable temperatures and stresses as an accumulation of the varying operating condition over a flight cycle. The applicable stress levels are then used to calculate the necessary radial area distribution of the airfoil and by this a prediction of its mass is possible. Furthermore, the methodology estimates the required amount of cooling air per airfoil cascade from the computed material temperatures. Example calculations are presented and discussed which illustrate design trends and the benefits which are gained from the proposed method.

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Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Estimation of peak gas temperature [2]

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Figure 2

Temperature, stress and area distribution [2]

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Figure 3

Airfoil radial area distribution and difference in mass and center of gravity

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Figure 4

Radial distributions and airfoil mass versus lifetime [2]

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Figure 5

Temperature and cooling air requirement versus lifetime [2]

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