Actions for Casing for a gas turbine engine [electronic resource].

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Casing for a gas turbine engine [electronic resource].

Published
Washington, D.C. : United States. Dept. of Energy, 2016.
Oak Ridge, Tenn. : Distributed by the Office of Scientific and Technical Information, U.S. Dept. of Energy
Additional Creators
United States. Department of Energy and United States. Department of Energy. Office of Scientific and Technical Information
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Summary
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).
Report Numbers
E 1.99:9,388,738
9,388,738
Subject(s)
Note
Published through SciTech Connect.
07/12/2016.
"9,388,738"
"13/252,325"
David J. Wiebe; David A. Little; Richard C. Charron.
SIEMENS ENERGY, INC., Orlando, FL (United States)
Funding Information
FC26-05NT42644
View MARC record | catkey: 23491841