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Simulating Flow & Heat in Gas Turbine Engines
Whether gas turbine (GT) engines are used for aircraft propulsion or for ground-based power generation, they involve sophisticated subsystems that ‘turn’ (compressors and turbines) and ‘burn’ (combustors). The goal with GT engines is to provide the rated power with maximum fuel efficiency and uptime reliability, while not exceeding government-regulated levels of emissions. While separately each GT subsystem must be designed for maximum performance, together they must also be designed to work harmoniously to ensure the entire GT engine system functions as intended. Trying to find an optimal...
I was recently traveling to a User Conference that CD-adapco held in Asia and spent a great deal of time staring out the window of various aircraft. With several hours to contemplate wings, I started thinking about boundary layers and how I have been simulating them. After reading “Boundary Layer Theory” by H. Schlichting, I had to double-check to make sure my designs were modeling the fluid phenomena near the wall correctly. What we design is far from well-known and validated fluid dynamics test cases. In fact, we invent some of the most unconventional products. As I opened the simulations...
Time-Accurate Simulation of Crown-Implant Cementation
STAR-CCM+ was used to perform numerical simulations on the complete implant abutment, cement and crown system. The objective of the simulations was to better understand the cement flow patterns during the seating of the crown, and to explore the effects of modifying the abutments and altering cement application techniques.
For this optimization, Optimate+ was used to identify Pareto optimimum designs. The objective functions were to maximize mass flow through the medical inlet and to minimize pressure drop. Best solution was obtained in 80 design evaluations.
STAR-CCM+ solution showing shear stress at wall of naval cavity during inhaling. Shear stress is high in passages with narrow cross-sections where velocity is high.
Polyhedral mesh for flow simulation in a human respiratory system (nasal cavity up to hypopharynx).The geometry was obtained from CT-data using software Mimics from Materialise and imported into STAR-CCM+ in STL-format (surface triangulation).
A direct numerical simulation of the buoyancy driven turbulent flow inside a horizontal annular cavity at higher Rayleigh number, Ra = 1.18x109, and the cylinders ratio of 4.87 has been carried out using the commercial code STAR-CCM+. Kinetic energy budgets have been calculated to verify the accuracy of the unstructured finite volume code on polyhedral cells in Direct Numerical Simulation (DNS) mode. Comparison of DNS results with wall resolved Unsteady RANS (URANS) models shows that the later models are able to capture the general flow features but fail to predict the large unsteadiness and...
The current study investigates the noise characteristics of a Radial Fan with Forward Curved Blades by performing CFD simulations with the emphasis on employing different Turbulence Models and Unstructured Grids. The predicted noise spectra obtained from CFD results (Star-CCM+), and also hybrid CAA method (coupling of Star-CCM+ and ACTRAN) are in good agreement with the experimental results. Especially the overall trend of the experimental curves as well as the Blade Passing Frequency (BPF) is correctly predicted. Additionally, using transient surface & volume data helped to gain insight...
The present paper focuses on a low-speed computational investigation into the application of backward sweep for application on a typical low-pressure turbine rotor blade. A quasi-two-dimensional linear cascade using T106 profile, was investigated using flow solver Star-CCM+ ® . Three backward-swept tip modifications (axial sweep, tangential sweep, and a combination of both) have been applied to the baseline profile from 90%–100% span, the rest of the 90% of the blade remained straight and orthogonal to the cascade mainstream flow. The blade stacking axis near the tip was shifted away from the...
A numerical investigation on a low-speed linear cascade has been done to study the impact of sweep applied at the tip of a turbine rotor blade on tip leakage flow. Two forward and two backward swept blade tip modifications have been applied to the T106 profile to create new blade cascade configurations. The aim of applying sweep to the blade’s tip is an attempt to reduce tip losses. This can be achieved by reducing the leakage mass flow rate or by altering the leakage flow to reduce the leakage vortex strength, which is the main contributor to tip losses. A detailed comparison of the tip...

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