Gas turbine engine with radial diffuser and shortened mid section
Patent
·
OSTI ID:1214126
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.
- Research Organization:
- Siemens Energy, Inc., Orlando, FL (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FC26-05NT42644
- Assignee:
- Siemens Energy, Inc. (Orlando, FL)
- Patent Number(s):
- 9,127,554
- Application Number:
- 13/602,422
- OSTI ID:
- 1214126
- Resource Relation:
- Patent File Date: 2012 Sep 04
- Country of Publication:
- United States
- Language:
- English
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