Volvo Aero Corporation

Gknaerospace Sweden Ab

Jan Häggander

Jan Lundgren

Arne Boman

Mats Hallqvist

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 wall structure () and components incorporating such a wall structure that are intended to be exposed to high thermal loads. The wall structure () includes at least two layers; a first layer () and a second layer (), the second layer () being located closer to a source of the thermal load than the first layer (). The layers () are arranged so that heat is allowed to be conducted from the second layer () to the first layer (). Each of the first and second layers () are adapted to carry a significant portion of a structural load, and the second layer () exhibits a higher thermal conductivity and/or a lower thermal expansion than the first layer () which reduces thermal strain in the wall structure ().

Wall structure

Method and arrangement for providing a liquid fuel rocket engine member having a load bearing wall structure () including a plurality of cooling channels () for handling a coolant flow. Each cooling channel () is provided with a flow guiding surface () extending at an angle to the cooling channel axis, for providing the axial coolant flow with an added flow component in the radial direction.

Rocket engine member and a method for manufacturing a rocket engine member

Method and arrangement for providing a component () for being subjected to high thermal load during operation. The component includes a wall structure, which defines an inner space for gas flow. The component is formed by at least a first part () that includes an inner wall (), an outer wall () and at least one cooling channel () between the walls. An end portion of said inner wall of the first part of the component is joined to a second part (). The joint () is located at a distance from the interior of the component.

Component for being subjected to high thermal load during operation and a method for manufacturing such a component

Method and arrangement for providing an outlet nozzle () for use in a liquid fuel rocket engine. The nozzle forms a body of revolution having an axis () of revolution and a cross section that varies in diameter along said axis. The nozzle has a wall structure having a plurality of mutually adjacent cooling channels, helically extending substantially in parallel from the inlet end () of the nozzle to its outlet end (). The nozzle includes at least two longitudinally arranged sections (). A shift between a positive and a negative channel angle in the transition from one section to an adjacent section balances any roll momentum generated by friction of rocket exhausts against the nozzle wall.

Outlet nozzle and a method for manufacturing an outlet nozzle

A wall structure () configured to be exposed to a thermal load. The wall structure having at least two layers including a first layer () and a second layer (). The second layer () is located closer to a source of the thermal load than the first layer (), and the layers () are arranged so that heat is allowed to be conducted from the second layer () to the first layer (). Each of the first and second layers () are adapted to carry a significant portion of a structural load, and the second layer () exhibits a higher thermal conductivity and/or a lower thermal expansion than the first layer (). The invention reduces the thermal strain in the wall structure ().

Method and arrangement for providing liquid fuel rocket engine member (). The member forms a body of revolution having an axis of revolution and a cross section that varies in diameter along said axis. The wall structure includes a plurality of cooling channels (). The outside of the wall structure includes a continuous sheet metal wall (). The cooling channels () are longitudinally attached to the inside of the sheet metal wall. The method for manufacturing the rocket engine member () includes the steps of forming a sheet metal wall () having a wall section corresponding to the desired nozzle section, providing a plurality of channel members (), and attaching the channel members () to the inside of the sheet metal wall ().

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Trollhättan, Sweden

Jan Häggander