GAS TURBINE ENGINE COMPRESSOR STATOR Russian patent published in 2012 - IPC F04D29/58 F02C7/20 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine compressor stator consists of outer, inner and ventilated casings 2, 3 and 4, respectively, interconnected by flexible elements. Front and rear surfaces 5 and 6 of ventilation chambers are located between outer and inner casings 2 and 3, 4, respectively. Bleed chamber 7 is arranged between ventilation chambers. Outer casing 2 is jointed with inner casing 3 and 4 in front and rear ventilation chambers 5 and 6 by means of dual centering with thrust against of casing but joints. Inner casing 4 is made integral with flexible elements at outlet of rear ventilation chamber 6. Bleed chamber flexible elements are, preferably, closed by heat-insulation jackets. Surface of inner case 3 is provided with ring ribs in front ventilation chamber 5.

EFFECT: reduced weight and production costs.

3 cl, 3 dwg