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Aerospace & Defense

Gas Turbine Engines


Anti-Icing Systems

CFD simulation showing velocity contours near the inlet from the Piccolo tube Simulation of Piccolo Tube Anti-Icing System
Flow modeling simulation showing the contours of collection efficiency on a Boeing 737 nacelle Collection Efficiency for Icing Analysis

Combustors

Temperature contours on a flame surface and contours of vorticity magnitude on the mid-plane of a gas turbine combustor GE Aircraft Engines LM6000 Combustor Instability Analyzed with Large Eddy Simulation (LES)
CFD siumlation of a FETC gas turbine combustor Studying Instability in Lean Premixed Combustion
FLUENT/UNS closely matched the measured film effectiveness in this benchmark study of film cooling CFD for Turbine Film Cooling
The FLUENT CFD studies showed that configuration changes could produce a more uniform exit temperature profile in the gas turbine Gas Turbine Combustor Optimization

Compressors and Fans

Flow modeling siumlation showing rotor axial flow Compressors

Fire Suppression

Time-dependent prediction of simulated halon distribution for fire suppression in the core compartment of a jet engine Fire Suppression and Detection

Fuel Systems

A CFD simulation from FLUENT's primary atomization models Gas Turbine Spray Nozzles
120-degree cut-out of a simplex atomizer showing the liquid fuel (red) and the air (blue) High Performance Fuel Injector Design

Inlets and Diffusers

Hybrid inlet total pressure contours at exit, created using an unstructured mesh CFD package Sandia Uses CFD Software with Adaptive Meshing Capability to Optimize Complex Inlet Design
CFD simulation showing static pressure contours on a drone surface Propulsion System Testing With CFD
Contours of Mach number illustrate the shock for mid-descent case for generic nacelle Preliminary Design and Evaluation of High Bypass Nacelle Inlets Using 3-D Navier-Stokes CFD Simulation
Contours of Mach number at four locations: the inlet to the duct, the muff inlet, the screen, and the bell mouth inlet Using CFD to Optimize Auxiliary Power Unit Design

Installations

Illustration of a response surface for the scarf angle optimization of a nacelle Southampton Partnership Optimizes Collaboration
Contours of Mach number at four locations: the inlet to the duct, the muff inlet, the screen, and the bell mouth inlet Using CFD to Optimize Auxiliary Power Unit Design
Contours of Mach number illustrate the shock for mid-descent case for generic nacelle Preliminary Design and Evaluation of High Bypass Nacelle Inlets Using 3-D Navier-Stokes CFD Simulation
Efflux pattern on an airplane for a Mach 0.15 case Enhancing Thrust Reverser Performance
An iso-surface of the 10% LEL detection (corresponding to 1.61% of net enclosure volume) ATEX for Explosive Atmospheres
CFD pathlines illustrate the flow in the original configuration of the gas turbine Reducing Gas Turbine Emissions

Nozzles

CFD simulations were performed to match the rig hardware dimensions Honeywell Validates Turbofan Mixer Nozzle Design
Temperature in the mixing zone and on the nozzle components on a turbofan lobed mixer nozzle Turbofan Lobed Mixer Nozzle

Secondary Air Systems

Contours of total temperature at a pressure ratio of 1.5 of a labyrinth seal Predicting Windage Heating of Air Through Labyrinth Seals
Pathlines on the suction side of the blade (left) show a passage vortex at the blade root and tip. On the pressure side (right) a leakage vortex is observed. Thermal Analysis of Gas Turbines by CRIEPI
FLUENT/UNS closely matched the measured film effectiveness in this benchmark study of film cooling CFD for Turbine Film Cooling
Analysis of turbine disk cooling is one example of BMW Rolls-Royce's successful integration of Fluent codes with PATRAN for CAD compatibility Turbomachinery Design

Thrust Reversers

Stream lines from the thrust reverser efflux by computational fluid dynamics (CFD) Computer Simulation of Thrust Reversers Reduces Testing, Enhances Performance and Reliability

Turbines

Pathlines on the suction side of the blade (left) show a passage vortex at the blade root and tip. On the pressure side (right) a leakage vortex is observed. Thermal Analysis of Gas Turbines by CRIEPI
FLUENT/UNS closely matched the measured film effectiveness in this benchmark study of film cooling CFD for Turbine Film Cooling
Analysis of turbine disk cooling is one example of BMW Rolls-Royce's successful integration of Fluent codes with PATRAN for CAD compatibility Turbomachinery Design
Contours of static pressure through a multi-stage turbine Multi-Stage Turbine Simulation Uses Mixing Plane Model with Unstructured Meshes
Mach number contour plots on the Aachen turbine hub and blades ERCOFTAC F1 and U1 Test Cases Modeled