FIELD: engine building.
SUBSTANCE: invention relates to an exhaust housing of an aircraft gas turbine engine comprising shell (4), hub (5), hollow posts (63) connecting said shell (4) to said hub (5), and branch pipe (3) located on shell (4) and made with possibility of connection with output tube (30) of gas turbine engine transition mode valve, wherein said branch pipe (3) is fixed on shell (4) during hollow post (63) so that air flow (7) coming from output tube (30) of the transient mode valve penetrates into hollow post (63) and flows inside hub (5).
EFFECT: allows to limit temperature difference between hub and shell during takeoff or during acceleration phases of aircraft due to heating of said hub and, thus, increases service life of outlet housing.
7 cl, 7 dwg
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