Thermal lining for jet engine combustion chamber

Details Thermal lining for jet engine combustion chamber Thermal lining for jet engine combustion chamber

F - Mech Eng,Light,Heat,Weapons

02

K

139/58, 60/69

F02K 9/34 (2006.01)

Patent

CA 1341559

The invention involves a thermal lining for the combustion chamber of an engine, especially a jet engine. The thermal lining (1) consists of a three-dimensional, multidirectional heat-resistant fiber structure (2). This structure is self-supporting and permeable to gases. The thermal lining (1) also includes an elastic layer (3) of elastomer material which impregnates the structure (2) and can be in turn filled with fibers. At least one such elastic layer (3) is inserted between the structure (2) and the combustion chamber case (9). The lining resists high temperatures and severe engine operating conditions, especially when high-frequency acoustic vibrations are generated. The invention can especially be used in the power plants of missiles, rockets or similar vehicles.

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