Abstract: To provide a thermal connection that can withstand mechanical stress in a high temperature structure comprising a panel having one face carrying a circuit made up of tubes in which a fluid flows, the outside walls of the tubes are covered in respective high thermal conductivity textile layers. The structure further comprises holding means for holding the tubes pressed in non-rigid manner against the panel. The structure enables heat exchange to take place between the panel and the fluid in order to cool the panel, to heat the fluid, or indeed in order to do both.

Abstract: In a turbomachine comprising an annular shell of metal material containing in a gas flow direction F: a fuel injection assembly; an annular combustion chamber of composite material; and an annular nozzle of metal material forming the inlet stage with fixed blades of a high pressure turbine, provision is made for the combustion chamber to be held in position inside the annular metal shell by a plurality of flexible metal tongues each comprising three branches connected together in a star configuration, the ends of two of these three branches being fixed securely to a downstream end of the combustion chamber via respective first and second fixing means, and the end of the third branch being fixed securely to the annular shell via third fixing means.

Abstract: To provide a thermal connection that can withstand mechanical stress in a high temperature structure comprising a panel having one face carrying a circuit made up of tubes in which a fluid flows, the outside walls of the tubes are covered in respective high thermal conductivity textile layers. The structure further comprises holding means for holding the tubes pressed in non-rigid manner against the panel. The structure enables heat exchange to take place between the panel and the fluid in order to cool the panel, to heat the fluid, or indeed in order to do both.

Abstract: In a turbomachine comprising an annular shell of metal material containing in a gas flow direction F: a fuel injection assembly; an annular combustion chamber of composite material; and an annular nozzle of metal material forming the inlet stage with fixed blades of a high pressure turbine, provision is made for the combustion chamber to be held in position inside the annular metal shell by a plurality of flexible metal tongues each comprising three branches connected together in a star configuration, the ends of two of these three branches being fixed securely to a downstream end of the combustion chamber via respective first and second fixing means, and the end of the third branch being fixed securely to the annular shell via third fixing means.