Turbine exhaust diffuser with region of reduced flow area and outer boundary gas flow
An exhaust diffuser system and method for a turbine engine. The outer boundary may include a region in which the outer boundary extends radially inwardly toward the hub structure and may direct at least a portion of an exhaust flow in the diffuser toward the hub structure. At least one gas jet is provided including a jet exit located on the outer boundary. The jet exit may discharge a flow of gas downstream substantially parallel to an inner surface of the outer boundary to direct a portion of the exhaust flow in the diffuser toward the outer boundary to effect a radially outward flow of at least a portion of the exhaust gas flow toward the outer boundary to balance an aerodynamic load between the outer and inner boundaries.
- Research Organization:
- Siemens Energy, Inc., Orlando, FL, USA
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FC26-05NT42644
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- Patent Number(s):
- 8,668,449
- Application Number:
- 12/944,210
- OSTI ID:
- 1126870
- Country of Publication:
- United States
- Language:
- English
A Three-Dimensional CFD Design Study of a Circulation Control Inlet Guide Vane for a Transonic Compressor
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conference | January 2009 |
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