JP2016008561A5 - - Google Patents

Description

An exhaust gas turbine supercharger according to the second aspect of the present invention includes any one of the labyrinth seal devices for an axial flow turbine described above, and a compressor is coaxially provided on the turbine shaft, and the energy of the exhaust gas. Thus, the compressor is rotated to supercharge the intake gas of the internal combustion engine.

As shown in FIG. 2, the labyrinth member 22 constituting the gas labyrinth seal GL has an exhaust gas passage so that the outer peripheral surface 22a does not generate a step with respect to the inner peripheral surface 13a of the exhaust gas passage 13 (exhaust gas outlet casing 12). The exhaust gas passage 13 is formed together with the exhaust gas outlet casing 12. Further, the labyrinth member 22 is fixed to the bearing block 2 so as to be adjacent through between gap-shaped seal gas discharge passage 26 between the exhaust gas outlet casing 12.

The seal gas after passing through the gas labyrinth seal GL flows into the air collecting chamber 30 (see FIG. 2), further flows through the deaeration passage 31 to the seal gas discharge passage 26, and is discharged into the exhaust gas passage 13. Thus, the position where the seal gas is discharged into the exhaust gas passage 13 is a position downstream of the adjacent portion (gap G1) between the turbine disk 6 and the labyrinth member 22 in the axial direction of the turbine shaft 4.

Claims (6)

A turbine shaft supported by a bearing stand;
A turbine disk provided on the turbine shaft;
An exhaust gas turbine blade provided on the outer periphery of the turbine disk;
A casing that forms exhaust gas passages for supplying exhaust gas to the exhaust gas turbine blades and exhausting the exhaust gas that has passed through the exhaust gas turbine blades out of the system;
An annular labyrinth member fixed on the bearing stand side and constituting a gas labyrinth seal adjacent to the exhaust gas downstream side of the turbine disk;
A labyrinth seal device for an axial flow turbine, comprising: a seal gas discharge passage for discharging a seal gas flowing through the gas labyrinth seal into the exhaust gas passage on the exhaust gas downstream side of the exhaust gas turbine blade;
The labyrinth seal device for an axial-flow turbine, wherein the seal gas discharge passage is formed between the exhaust gas passage formation portion of the casing and the labyrinth member.   The labyrinth seal device for an axial flow turbine according to claim 1, wherein an outer peripheral surface of the labyrinth member forms the exhaust gas passage together with the casing.   The joining portion of the seal gas discharge passage with the exhaust gas passage is formed so that a flow direction of the seal gas has an axial component facing a downstream side of the exhaust gas passage. Labyrinth seal device of the axial flow turbine.   The labyrinth seal device for an axial flow turbine according to any one of claims 1 to 3, wherein the seal gas discharge passage includes a bent portion that changes a flow direction of the seal gas.   At the position of the seal gas discharge passage, the exhaust gas downstream side end portion of the labyrinth member overlaps with the outer peripheral side of the exhaust gas upstream side end portion of the exhaust gas passage forming portion of the casing, and the protruding member is disposed in the circumferential direction on the overlapped portion. The labyrinth seal device for an axial flow turbine according to claim 4, wherein the labyrinth seal device is interspersed with the axial flow turbine. An internal combustion engine comprising the labyrinth seal device for an axial turbine according to any one of claims 1 to 5, wherein a compressor is coaxially provided on the turbine shaft, and the compressor is rotationally driven by the energy of the exhaust gas. An exhaust gas turbocharger characterized by supercharging the intake gas .