FIELD: motors and pumps.
SUBSTANCE: invention relates to the constructions of aviation gas turbine engines, in particular to the structures of units for the removal of hot gases. Exhaust device of the gas pumping unit contains elements consisting, in turn, of four walls. All walls consist of a supporting hot part and a non-curtaining cold part connected to each other. Supporting hot part and the non-carrying cold part are connected together by a rigid connection at one point of connection and compensators in several places.
EFFECT: elimination of temperature deformations is achieved.
4 cl, 14 dwg, 2 tbl
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