GAS TURBINE ENGINE AND ITS INTERMEDIATE ASSEMBLY Russian patent published in 2010 - IPC F01D9/02 F02K3/06 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine comprises intermediate assembly 14 to be arranged axially between turbine 1^st and 2^nd assemblies. The latter can represent LP compressor and HP compressor or HP turbine and LP turbine. Said intermediate assembly comprises circular channel 5c running around central axial line 18 of intermediate assembly 14. Intermediate assembly serves to direct gas flow from gas channel in the 1^st assembly to that in the 2^nd assembly. Inlet 19 of said circular gas channel 5c of intermediate assembly is notably shifted radially relative to its outlet 20. Intermediate assembly circular gas channel 5c accommodates at least one guide element 28, 29 to direct gas flow. Said guide element features the shape of circular guide element and is located nearby curved section of the wall that forms circular gas channel.

EFFECT: reduced losses in intermediate gas channel and increased radial shift of its outlet relative to inlet.

12 cl, 4 dwg