The aerodynamic design of uncooled turbomachinery rows is based, among other things, on the repeated simulation of three-dimensional blade rows with a fast turnaround time. Traditionally blade rows have been simulated using clean aerodynamic surfaces and simplified computational domains consisting of just the aerodynamic surface and an approximated main annulus. A more accurate and realistic re...

In this opening lecture I will summarize some of the fundamentals of cavitation in the hope that this will allow attendees greater insight into the more advanced lectures which follow. Whether your primary interest is in the turbomachinery field or in the biological and bioengineering contexts in which cavitation is important these fundamentals are important in understanding the observed phenom...

We analyze the stability of a cylindrical Couette flow under the imposition of a weak axial flow in case of a very short cylinder with a narrow annulus gap. We consider an incompressible viscous fluid which is contained in the narrow gap between two concentric short cylinders, where the inner cylinder rotates with constant angular velocity. The caps of the cylinders have narrow tubes conically ...

A new computational capability under development for accurate and efficient high-fidelity direct numerical simulation (DNS) and large eddy simulation (LES) of turbomachinery is described. This capability is based on an entropy-stable Discontinuous-Galerkin spectral-element approach that extends to arbitrarily high orders of spatial and temporal accuracy and is implemented in a computationally e...

The first lecture in this two-lecture sequence provides background and general concepts. The second lecture provides practical examples. The objective of these two lectures is to provide a modular design optimization tool description that will take into account interaction of the hot gas flow-field, heat transfer in the blade material, internal coolant flow-field, stresses and deformations of t...

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The LOX-Hydrogen J-2X Rocket Engine, which is proposed for use as an upper-stage engine for numerous earth-to-orbit and heavy lift launch vehicle architectures, is presently in the design phase and will move shortly to the initial development test phase. Analysis of the design has revealed numerous potential resonance issues with hardware in the turbomachinery turbine-side flow-path. The analys...

For advanced aerospace propulsion systems, development of ceramic matrix composite integrally-bladed turbine disk technology is attractive for a number of reasons. The high strength-to-weight ratio of ceramic composites helps to reduce engine weight and the onepiece construction of a blisk will result in fewer parts count, which should translate into reduced operational costs. One shortcoming w...