- ADT to Sponsor 25th IAHR Symposium - Sept. 20-24 Timisoara
- ADT to Present TURBOdesign Suite 5.0 at ASME 2010 Turbo Expo
- ADT to Exhibit at the Turbocharging Conference,May, London
- ADT - Impact-Tek Streamline Turbomachinery Structural Design
- Ebm-papst couples TURBOdesign-1 with Automatic Optimization
- ADT announces VINAS as distributor for Japan
- TURBOdesign Suite Pumps & Hydraulic Turbines Workshop
- ADT to exhibit at the Ansys EASC in Munich, July 09
- ADT to exhibit at the ASME Turbo Expo 2009 in Orlando
- JAXA achieves superior design of Rocket Pumps with TD-1
- ADT to exhibit at RINA Waterjet Propulsion 5
- ADT to exhibit at the IMechE International Fan Symposium
- Release of TURBOdesignSuite V3
- TURBOdesign Suite V3.0 showcased at Engineous Symposium
- TURBOdesign Suite to be showcased at FanNoise 2007
- TURBOdesign-1 v 3.0 Featured in World Pumps June Issue
- ADT Pump & Fan Workshop in conjunction with TURBOlab
- Ebm-papst utilizes TURBOdesign-1 in Optimal Fan Design
- ADT and Engineous Japan Inc Plan a Joint Consortium
- IMechE 8th International Conference on Turbocharging.
- 51st ASME TURBO EXPO.
- Pump and Fan Design Workshop, London, 3-4 April 2006.
- Commercial Release of TURBOcfd Announced
- Application of TURBOdesign-1 in Ebara Corporation
- Commercial Release Of TURBOdesign-2 Announced
- Avio utilizes TURBOdesign-1 for Aeroengine LP Turbines
- Kubota uses TURBOdesign-1 in design of Hydraulic Turbines
- 50th ASME TURBO EXPO.
- The 6th European Turbomachinery Conference
- Development News on TURBOdesign-2
- Issue of Version 2.2 of TURBOdesign-1
- 2003 World Pump Article
Commercial Release Of TURBOdesign-2 Announced
Advanced Design Technology the global leader in advanced turbomachinery design codes are pleased to announce the commercial release of TURBOdesign-2 Version 1.0.0
TURBOdesign-2 is an Aerodynamic design code for application to turbomachinery blades; the software is based on a 3D viscous transonic inverse design method. TURBOdesign-2 has been developed mainly for the design of turbomachinery components such as transonic fans where shock and boundary layer interaction effects are significant.
International Consortium
TURBOdesign-2 was developed as part of an international consortium in which involved 6 major Aero-Engine and Gas Turbine manufacturers, which included The Avio Group of Italy, The Ebara Corporation of Japan, Kawasaki Heavy Industry, Rolls-Royce Aeroengines, Toshiba and Toyota Motor Corporation of Japan.
TURBOdesign-2 Overview
This efficient new method computes the blade geometry for a specified distribution of blade loading, which itself directly relates to the pressure distribution plus the blade thickness, which is normally specified as normal thickness. This method is not only robust in 3D applications but also it can ensure structural integrity of the design as normal thickness distribution is specified. TURBOdesign-2 allows designers to use their knowledge of flow physics to arrive directly at optimum blade loading, and consequently 3D geometry. As a result of the inverse nature of this code, design know-how obtained in any specific case will automatically become more universal since it is based on flow physics. Simple and effective design guidelines can be generated and followed by all designers. This mechanism renders the design process systematic, which in turn substantially increases the likelihood of breakthrough designs. These features of TURBOdesign-2 enable rapid design of complex blade geometries such as those found in civil and military aeroengine fans.
Advantages & Benefits TURBOdesign-2
? Full shock capturing capability and viscous model.
? Blade geometry and 3D viscous flow fields are the direct outputs.
? Easy to export the resulting geometry to major CAD, FEA and CFD.
? Rapid design cycle.
? Easy to generate database of design know-how.
TURBOdesign-2 Unique Design Process
? Mainly applicable to transonic axial fans and compressors.
? Rotating and stationary components.
? Two types of design specification:
Method 1 - The loading distribution or derivative of circumferentially averaged swirl velocity, as in TURBOdesign-1, is specified together with blade normal thickness.
Method 2 - The surface static pressure Loading, ?P (=P+ ñ P-) is specified together with the normal thickness.
? Possible to use both Analysis and Design Modes.
? Existing blade geometry can be read in and only certain parts of the blade are modified by changes to the loading distribution.
? Interactive modification of thickness, streamwise and spanwise loading distribution.
Please contact ADT for further information or request an online demonstration of this unique design code.
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