A LINER FOR A TURBINE SECTION, A TURBINE SECTION, A GAS TURBINE ENGINE AND AN AEROPLANE PROVIDED THEREWITH
A liner for a turbine section includes a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein each cooling channel presents a height c...
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Main Author | |
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Format | Patent |
Language | English French German |
Published |
13.06.2012
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Subjects | |
Online Access | Get full text |
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Summary: | A liner for a turbine section includes a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein each cooling channel presents a height corresponding to the height of its delimiting webs, and a width corresponding to the distance between its delimiting webs. At least one of the cooling channels has a width/height ratio of below 5 or/and the material of the webs has a higher thermal conductivity than the material of the first wall. A turbine section, a gas turbine engine and an aeroplane provided with such a liner are also disclosed. |
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Bibliography: | Application Number: EP20060835822 |