EPSRC Reference: |
GR/N09107/01 |
Title: |
DNS/LES OF COMPRESSIBLE SUBSONIC FLOW THROUGH TURBINE BLADE ROWS AND AROUND AEROFOILS |
Principal Investigator: |
Voke, Professor P |
Other Investigators: |
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Researcher Co-Investigators: |
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Project Partners: |
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Department: |
Engineering and Physical Sciences |
Organisation: |
University of Surrey |
Scheme: |
Standard Research (Pre-FEC) |
Starts: |
27 March 2000 |
Ends: |
26 April 2001 |
Value (£): |
55,825
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EPSRC Research Topic Classifications: |
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EPSRC Industrial Sector Classifications: |
No relevance to Underpinning Sectors |
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Related Grants: |
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Panel History: |
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Summary on Grant Application Form |
The Advected Grid Explicit simulation method for compressible flow will be developed for use in aerospace engineering geometries. The resulting developed code will be used to:- Simulate slightly compressible flat-plate boundary layers, initially with zero pressure gradient, then with favourable and adverse pressure gradients. These simulations are essential before simulations of lifting aerofoils or blades can be made.- Simulate truly compressible subsonic flow through non-parallel channels.Severla options for implementing the advected grid will be investigated, including a purely Cartesian advecting grid, a continuously distorting advecting grid, and a stationary grid.- Simulate boundary layers and channels with curved surfaces. The methods to be used depend on results from the previous stages but will be based on existing achievements for using generalised co-ordinates for curved domains.Comparisons will be made with available date for turbomachinery blades and aerofoils.
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Key Findings |
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Potential use in non-academic contexts |
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Impacts |
Description |
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Summary |
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Date Materialised |
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Sectors submitted by the Researcher |
This information can now be found on Gateway to Research (GtR) http://gtr.rcuk.ac.uk
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Project URL: |
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Further Information: |
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Organisation Website: |
http://www.surrey.ac.uk |