Volvo Aero Corporation

Gknaerospace Sweden Ab

Arne Boman

Jan Lundgren

Jan Häggander

Jan H&auml;ggander

Mats Olofsson

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.

Liner for a turbine section, a turbine section, a gas turbine engine and an aeroplane provided therewith

A component configured for being subjected to a high thermal load during operation includes a wall structure with cooling channels adapted for handling a coolant flow. At least one first cooling channel is adapted to convey the coolant from a first portion of the component to a second portion of the component. At least one second cooling channel in the second portion is closed so that the coolant is at least substantially-prevented from entering the closed second cooling channel from a cooling channel in the first portion.

Component configured for being subjected to high thermal load during operation

A method is provided for producing an engine wall structure that includes an inner wall, to which hot gas is admitted during engine operation, an outer wall, which is colder than the inner wall during engine operation, and at least two webs that connect the inner wall with the outer wall and delimit a cooling duct between the walls. The engine wall structure is produced by wire-electro discharge machining the duct out of a solid sheet forming the entire engine wall structure including the inner wall, the outer wall and the webs.

Method of producing an engine wall structure

An engine wall structure includes an inner wall to which hot gas is admitted during engine operation, an outer wall, which is colder than the inner wall during engine operation, and at least two webs that connect the inner wall with the outer wall and delimit a cooling duct between the walls. The webs are mainly formed by a first material and the inner wall is mainly formed by a second material of other composition and other heat conductivity than the first material.

Engine wall structure and a method of producing an engine wall structure

Method and arrangement for providing a liquid fuel rocket engine member ( ). The member has a load bearing wall structure ( ) having a plurality of cooling channels ( ). For improving the heat transfer, a material with a higher thermal conductivity than the load bearing wall structure ( ) is applied to the wall structure.

Rocket engine member and method for manufacturing a rocket engine member

The invention relates to an apparatus for increasing the heat transfer to the coolant at the inside of a nozzle wall provided with coolant channels of expander cycle rocket engines. To achieve this the invention proposes that, to disturb the boundary layer at the nozzle wall and thereby increasing the heat transfer, the inside of the nozzle wall facing the flame has a particularly chosen increased surface roughness of such a magnitude that it penetrates the viscous sub-layer of the boundary layer at the nozzle wall.

Apparatus for controlling the heat transfer to the nozzle wall of expander cycle rocket engines

The invention refers to an apparatus for controlling the flow separation line of rocket nozzles for reducing side loads. For obtaining this control it is suggested according to the invention that the inside of the nozzle ( ) has circumferentially regular spaced areas ( ) with increased surface roughness compared with the rest of the inside of the nozzle.

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Trollhättan, Sweden

Arne Boman