Turbine exhaust diffuser with region of reduced flow area and outer boundary gas flow
Abstract
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.
- Inventors:
- Issue Date:
- Research Org.:
- Siemens Energy, Inc., Orlando, FL, USA
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1126870
- Patent Number(s):
- 8668449
- Application Number:
- 12/944,210
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- DOE Contract Number:
- FC26-05NT42644
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Orosa, John. Turbine exhaust diffuser with region of reduced flow area and outer boundary gas flow. United States: N. p., 2014.
Web.
Orosa, John. Turbine exhaust diffuser with region of reduced flow area and outer boundary gas flow. United States.
Orosa, John. Tue .
"Turbine exhaust diffuser with region of reduced flow area and outer boundary gas flow". United States. https://www.osti.gov/servlets/purl/1126870.
@article{osti_1126870,
title = {Turbine exhaust diffuser with region of reduced flow area and outer boundary gas flow},
author = {Orosa, John},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2014},
month = {3}
}
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