GAS TURBINE ENGINE GAS COLLECTOR Russian patent published in 2014 - IPC F02C7/06 

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engineering, particularly, to gas turbine engine with free turbine. Proposed gas collector has housing with two outer ring flanges interconnected by lengthwise and radial ribs, cylindrical shell, conical membrane with support ribs and curved shell, all making hot gas discharge circuit. Turbine bearing housing is arranged inside gas collector housing inner part with the channel feeding oil to cooling nozzles and turbine bearing lubing nozzles. Said housing has oil removal main line and main line to feed cold air from compressor for cooling turbine bearing housing walls, oil in oil feed lines and oil removal lines to feed cold air to turbine bearing labyrinth seals and unions of said lines. Note here that gas collector housing is equipped with inner flange while turbine bearings housing is composed of steeped sleeve with thrust and cylindrical flanges. Said sleeve is inserted into gas collector along two cylindrical spaced apart belts to thrust against said flanges. Extra cylindrical shell to seal cold air feed chamber is arranged between sleeve steps. Oil feed line is composed of channels made in the sleeve body. One of gas collector support ribs can be arranged between unions of oil removal line while steeped sleeve can be made from single-piece steel bar.

EFFECT: simplified design, higher reliability, longer life, better quality of repair.

3 cl, 3 dwg