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

Abstract

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.

Inventors:
;
Issue Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1214126
Patent Number(s):
9,127,554
Application Number:
13/602,422
Assignee:
Siemens Energy, Inc. (Orlando, FL)
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2012 Sep 04
Country of Publication:
United States
Language:
English
Subject:
33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Charron, Richard C., and Montgomery, Matthew D. Gas turbine engine with radial diffuser and shortened mid section. United States: N. p., 2015. Web.
Charron, Richard C., & Montgomery, Matthew D. Gas turbine engine with radial diffuser and shortened mid section. United States.
Charron, Richard C., and Montgomery, Matthew D. Tue . "Gas turbine engine with radial diffuser and shortened mid section". United States. https://www.osti.gov/servlets/purl/1214126.
@article{osti_1214126,
title = {Gas turbine engine with radial diffuser and shortened mid section},
author = {Charron, Richard C. and Montgomery, Matthew D.},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2015},
month = {9}
}

Patent:

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