NDLI: Preliminary Design Optimization of Impingement Cooled Turbine Airfoils

Content Provider	The American Society of Mechanical Engineers (ASME) Digital Collection
Author	Robert, F. Bergholz
Copyright Year	2008
Abstract	Generally, the objective of the turbine cooling design process is to minimize the amount of cooling flow required to achieve component life goals, including creep rupture, low-cycle (thermal-mechanical) fatigue, and material oxidation. High-pressure turbine airfoils in particular are subject to large variations in external gas temperatures and heat transfer coefficients, and high aero-mechanical loads. The efficient distribution of internal and film cooling flows, the management of internal coolant temperatures, and the optimal arrangement of cooling features to control thermal gradients are major factors in controlling thermal stress. The objective of this paper is to describe a process for conceptual and preliminary turbine airfoil cooling design based on the assembly of primitive cooling elements to define an overall “realizable” 3D airfoil cooling structure. This approach allows the evaluation of multiple cooling configurations, and potentially an improved prediction of cooling flows, early in the design process. This conceptual design method can be used to quickly generate models for fabrication and testing in a rapid prototyping laboratory. The design process is outlined for the simplified case of impingement cooling in a prototypical airfoil shape to illustrate some of the key design parameters and procedures. A future paper will address improvements in automation and more complex geometries. The paper also presents predictions based on a parametric impingement cooling model for the local surface heat transfer coefficient distribution. The model is easily incorporated into the conceptual design method. It is particularly useful for determining axial and radial thermal gradients the airfoil wall induced by sparse impingement arrays, for which the use of average heat transfer coefficients give unsatisfactory results. The model was calibrated using data from past published literature and more recently obtained experimental data from the GE Global Research Center.
Sponsorship	International Gas Turbine Institute
Starting Page	675
Ending Page	689
Page Count	15
File Format	PDF
ISBN	9780791843147
DOI	10.1115/GT2008-50704
e-ISBN	0791838242
Volume Number	Volume 4: Heat Transfer, Parts A and B
Conference Proceedings	ASME Turbo Expo 2008: Power for Land, Sea, and Air
Language	English
Publisher Date	2008-06-09
Publisher Place	Berlin, Germany
Access Restriction	Subscribed
Subject Keyword	Cycles Temperature Creep Impingement cooling Optimization Design High pressure (physics) Coolants Oxidation Manufacturing Film cooling Shapes Turbines Thermal stresses Testing Cooling Rupture Airfoils Fatigue Flow (dynamics) Stress Temperature gradient Rapid prototyping Conceptual design Heat transfer coefficients
Content Type	Text
Resource Type	Article

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