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Title: Casing for a gas turbine engine

Abstract

A casing for a can annular gas turbine engine, including: a compressed air section (40) spanning between a last row of compressor blades (26) and a first row of turbine blades (28), the compressed air section (40) having a plurality of openings (50) there through, wherein a single combustor/advanced duct assembly (64) extends through each opening (50); and one top hat (68) associated with each opening (50) configured to enclose the associated combustor/advanced duct assembly (64) and seal the opening (50). A volume enclosed by the compressed air section (40) is not greater than a volume of a frustum (54) defined at an upstream end (56) by an inner diameter of the casing at the last row of compressor blades (26) and at a downstream end (60) by an inner diameter of the casing at the first row of turbine blades (28).

Inventors:
; ;
Issue Date:
Research Org.:
SIEMENS ENERGY, INC., Orlando, FL (United States)
Sponsoring Org.:
USDOE
OSTI Identifier:
1261615
Patent Number(s):
9,388,738
Application Number:
13/252,325
Assignee:
SIEMENS ENERGY, INC. (Orlando, FL)
DOE Contract Number:  
FC26-05NT42644
Resource Type:
Patent
Resource Relation:
Patent File Date: 2011 Feb 04
Country of Publication:
United States
Language:
English
Subject:
42 ENGINEERING; 33 ADVANCED PROPULSION SYSTEMS

Citation Formats

Wiebe, David J., Little, David A., and Charron, Richard C. Casing for a gas turbine engine. United States: N. p., 2016. Web.
Wiebe, David J., Little, David A., & Charron, Richard C. Casing for a gas turbine engine. United States.
Wiebe, David J., Little, David A., and Charron, Richard C. Tue . "Casing for a gas turbine engine". United States. https://www.osti.gov/servlets/purl/1261615.
@article{osti_1261615,
title = {Casing for a gas turbine engine},
author = {Wiebe, David J. and Little, David A. and Charron, Richard C.},
abstractNote = {A casing for a can annular gas turbine engine, including: a compressed air section (40) spanning between a last row of compressor blades (26) and a first row of turbine blades (28), the compressed air section (40) having a plurality of openings (50) there through, wherein a single combustor/advanced duct assembly (64) extends through each opening (50); and one top hat (68) associated with each opening (50) configured to enclose the associated combustor/advanced duct assembly (64) and seal the opening (50). A volume enclosed by the compressed air section (40) is not greater than a volume of a frustum (54) defined at an upstream end (56) by an inner diameter of the casing at the last row of compressor blades (26) and at a downstream end (60) by an inner diameter of the casing at the first row of turbine blades (28).},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2016},
month = {7}
}

Patent:

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