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Title: Ducting arrangement for cooling a gas turbine structure

Abstract

A ducting arrangement (10) for a can annular gas turbine engine, including: a duct (12, 14) disposed between a combustor (16) and a first row of turbine blades and defining a hot gas path (30) therein, the duct (12, 14) having raised geometric features (54) incorporated into an outer surface (80); and a flow sleeve (72) defining a cooling flow path (84) between an inner surface (78) of the flow sleeve (72) and the duct outer surface (80). After a cooling fluid (86) traverses a relatively upstream raised geometric feature (90), the inner surface (78) of the flow sleeve (72) is effective to direct the cooling fluid (86) toward a landing (94) separating the relatively upstream raised geometric feature (90) from a relatively downstream raised geometric feature (94).

Inventors:
;
Issue Date:
Research Org.:
Siemens Energy, Inc., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1195939
Patent Number(s):
9,085,981
Application Number:
13/655,675
Assignee:
Siemens Energy, Inc. (Orlando, FL)
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2012 Oct 19
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Lee, Ching-Pang, and Morrison, Jay A. Ducting arrangement for cooling a gas turbine structure. United States: N. p., 2015. Web.
Lee, Ching-Pang, & Morrison, Jay A. Ducting arrangement for cooling a gas turbine structure. United States.
Lee, Ching-Pang, and Morrison, Jay A. Tue . "Ducting arrangement for cooling a gas turbine structure". United States. https://www.osti.gov/servlets/purl/1195939.
@article{osti_1195939,
title = {Ducting arrangement for cooling a gas turbine structure},
author = {Lee, Ching-Pang and Morrison, Jay A.},
abstractNote = {A ducting arrangement (10) for a can annular gas turbine engine, including: a duct (12, 14) disposed between a combustor (16) and a first row of turbine blades and defining a hot gas path (30) therein, the duct (12, 14) having raised geometric features (54) incorporated into an outer surface (80); and a flow sleeve (72) defining a cooling flow path (84) between an inner surface (78) of the flow sleeve (72) and the duct outer surface (80). After a cooling fluid (86) traverses a relatively upstream raised geometric feature (90), the inner surface (78) of the flow sleeve (72) is effective to direct the cooling fluid (86) toward a landing (94) separating the relatively upstream raised geometric feature (90) from a relatively downstream raised geometric feature (94).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2015},
month = {7}
}

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