Liner for a turbine section, a turbine section, a gas turbine engine and an aeroplane provided therewith
AssigneeVolvo Aero Corporation
InventorArne Boman
Life of this patent
Estimating the term…
Abstract
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.
Claims29
A liner for a turbine section, the liner comprising a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of A liner for a turbine section, the liner comprising a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels for air cooling of the liner, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein the material of the webs has a higher thermal conductivity than the material of the first wall, an exterior surface of the liner for facing the turbine section to be lined being continuous and uninterrupted, 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, wherein at least one of the cooling channels has a width/height ratio of below 5, wherein the material of the webs has a higher thermal conductivity than the material of the first wall, and an exterior surface of the liner for facing the turbine section to be lined is continuous and uninterrupted.
A liner for a turbine section, the liner comprising a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels for air cooling of the liner, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein the material of the webs has a higher thermal conductivity than the material of the first wall, an exterior surface of the liner for facing the turbine section to be lined being continuous and uninterrupted.
A turbine section, comprising a liner, the liner comprising a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels for air cooling of the liner, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein the material of the webs has a higher thermal conductivity than the material of the first wall, an exterior surface of the liner for facing the turbine section to be lined being continuous and uninterrupted.
A gas turbine engine, comprising a turbine section, the turbine section comprising a liner, the liner comprising a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels for air cooling of the liner, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein the material of the webs has a higher thermal conductivity than the material of the first wall, an exterior surface of the liner for facing the turbine section to be lined being continuous and uninterrupted.
An aeroplane, comprising a gas turbine engine, the gas turbine engine comprising a turbine section, the turbine section comprising a liner, the liner comprising a first wall, a plurality of webs interconnected with and projecting from the first wall, and a plurality of cooling channels for air cooling of the liner, each of the cooling channels being delimited by two adjacent webs and the first wall, wherein the material of the webs has a higher thermal conductivity than the material of the first wall, an exterior surface of the liner for facing the turbine section to be lined being continuous and uninterrupted.
Dependencies are inferred from the claim text.