FIELD: engines and pumps.
SUBSTANCE: invention relates to aircraft gas turbine engine joint between compressor and combustion chamber. Gas turbine engine compressor stator comprises inner and outer housings (3) and (2), respectively, interconnected by resilient elements (6, 7). Compressor stator inner housing is coupled with combustion chamber diffuser (10) in axial direction with clearance d at butt (13) equal to 0<d<0.6 mm. Flange of combustion chamber diffuser (10) at butt (13) with compressor stator inner housing has slots (14).
EFFECT: higher reliability and efficiency, longer life.
4 dwg
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