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Title: 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.
Authors:
Publication Date:
OSTI Identifier:
1126870
Report Number(s):
8,668,449
12/944,210
DOE Contract Number:
FC26-05NT42644
Resource Type:
Patent
Research Org:
Siemens Energy, Inc., Orlando, FL, USA
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING