GAS TURBINE ENGINE BEARING Russian patent published in 2009 - IPC F02C7/06 

FIELD: engines and pumps.

SUBSTANCE: invention relates gas turbine bearings. Increase in reliability of gas turbine bearing support is provided for by ruling out wear of bearing support sealing elements and increase in consumption of oil for bearing cooling and lubrication purposes. Jet flange with jet channel feeding oil into bearing oil chamber features radial wall smoothly changing over into tapered hood that forms intermediate oil discharge chamber to feed oil from jet channel along aforesaid radial wall. Tapered hood is arranged between care and inner race with minimum clearance Δ with respect to inner bearing race. Note here that oil chamber is separated from air chamber by stepwise labyrinth seal, while intermediate chamber communicates, via channels, with the bearing oil chamber. Note also that D/d=1 to 1.2, where D is outer diametre of labyrinth knife edge nearby bearing support, d is diametre of outer race. Oil is fed from the jet over radial and tapered surfaces to get onto bearing outer race to lubricate and oil it, thus, reducing race temperature on the disk side. This reduced temperature gradient over the race length and increases reliability of gas turbine bearing support.

EFFECT: ruling out ingress of oil in bearing support air chambers.

2 dwg