TURBINE SUPPORT Russian patent published in 2014 - IPC F02C7/06 F02C7/28 

FIELD: machine building.

SUBSTANCE: support for a turbine of a gas turbine engine comprises a bearing (4), a shaft (6) and a labyrinth (11) with a flange (10) between the bearing (4) and the turbine disk (8). An additional flange (12) is set on the outer side of the labyrinth (11) flange (10) forming a blowdown cavity (13). The cavity (13) at its inlet is connected to the air cavity (14) of the housing of the shaft (15) and at its outlet - to the inner cavity (20) of the shaft (6) through the grooves (17) and channels (18) in the labyrinth (11) and (19) in the shaft (6) which are inclined in respect to the support (1) axis (16). The grooves (17) from the inlet (21) to the outlet (22) are oriented in the direction (23) of the shaft (6) rotation. A baffle plate (25) with bayonet-type mount (26) of the inner tail (27) on the additional flange (12) forming a slot air cavity (28) is installed on the external side of the additional flange (12). The support labyrinth (31) which is the closest to the turbine disk (8) is made with sealing microridges (34) on the working surface (35) of the rim (33) with increased thickness. The relation of the microridge (34) height h to the value of the radial clearance δ in the labyrinth (31) being the closest to the disk (8) falls within the range 1.5-2.5. The relation of the maximal diameter D of the labyrinth (31) being the closest to the disk to the minimal thickness H of the labyrinth (31) rim (33) falls within the range 20-40.

EFFECT: due to reduction of heat flows coming to the oil cavity of the support the efficiency of the turbine support is increased, thermal stresses in the support labyrinth being the closest to the turbine disk are reduced.

4 dwg