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Title: 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):
8,668,449
Application Number:
12/944,210
Assignee:
Siemens Energy, Inc. (Orlando, FL)
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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Works referenced in this record:

A Three-Dimensional CFD Design Study of a Circulation Control Inlet Guide Vane for a Transonic Compressor
conference, January 2009

  • Gunter, Sandra L.; Guillot, Stephen A.; Ng, Wing F.
  • ASME Turbo Expo 2009: Power for Land, Sea, and Air, Volume 7: Turbomachinery, Parts A and B
  • DOI: 10.1115/GT2009-59360