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Title: Gas turbine engine with radial diffuser and shortened mid section

An industrial gas turbine engine (10), including: a can annular combustion assembly (80), having a plurality of discrete flow ducts configured to receive combustion gas from respective combustors (82) and deliver the combustion gas along a straight flow path at a speed and orientation appropriate for delivery directly onto the first row (56) of turbine blades (62); and a compressor diffuser (32) having a redirecting surface (130, 140) configured to receive an axial flow of compressed air and redirect the axial flow of compressed air radially outward.
Authors:
;
Publication Date:
OSTI Identifier:
1214126
Report Number(s):
9,127,554
13/602,422
DOE Contract Number:
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2012 Sep 04
Research Org:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org:
USDOE
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS