1. An apparatus, comprising:
a compressor casing for a turbocharger, the compressor casing defining an air inlet and having a blower casing component, the air inlet configured to admit air to a compressor wheel mechanically coupled to a turbine disc via a shaft, the turbine disc rotatable about a rotational axis of the turbocharger; and
a turbine casing for the turbocharger, the turbine casing housing the turbine disc, the turbine casing comprising a shroud component surrounding at least a portion of the turbine disc.
2. The apparatus of claim 1, wherein a wall of the blower casing component and a wall of the air inlet are adjacent to and continuous with each other along at least a section, and each of the wall of the blower casing component and the wall of the air inlet have a selected thickness and each comprise a selected material such that the combination of the wall of the blower casing component and the wall of the air inlet will exhibit a burst-strength sufficient to retain one or more fragments of the compressor wheel under a burst condition.
3. The apparatus of claim 2, wherein at least one of the wall of the air inlet or the wall of the blower casing comprise a ductile metal.
4. The apparatus of claim 2, wherein the thickness of the wall of the air inlet differs from a thickness of the wall of the blower casing.
5. The apparatus of claim 1, wherein the compressor casing and the turbine casing are formed together as one undivided, monolithic turbocharger casing.
6. The apparatus of claim 1, wherein the shroud component is integrated with a remainder of the turbine casing, and the shroud component has a cross-section having a thickness, the thickness being defined as perpendicular to a longitudinal axis of the shroud component and the thickness being determined to have a burst-strength for retaining one or more fragments of the turbine disc under a burst condition, the longitudinal axis parallel to the rotational axis of the turbocharger.
7. The apparatus of claim 6, wherein the shroud component is integrated with the remainder of the turbine casing at a first end of the shroud component, the first end being further away from the turbine disc than a second end of the shroud component.
8. The apparatus of claim 6, wherein the shroud component has an inner surface that defines a water circulation passage extending through the shroud component, and is configured so that thermal fluid circulating through the water circulation passage will carry heat from the shroud component to a location away from the shroud component.
9. The apparatus of claim 8, wherein the water circulation passage is an annular-shaped passage that extends along a circumferential edge of the shroud.
10. The apparatus of claim 6, wherein the shroud component comprises a heat transfer structure configured to transport heat energy from inside the shroud component to a stream of air impinging on the heat transfer structure.
11. The apparatus of claim 1, wherein the shroud component is coupled to a flange of the turbine casing, the flange integrated with the turbine casing and extending along a length of the shroud component, the flange positioned at an outer face of the shroud with respect to the rotational axis of the turbocharger, the flange having a first thickness.
12. The apparatus of claim 11, wherein the flange and the shroud component are coupled to one another at a distal end of the flange and a distal end of the shroud component and wherein the distal end of the shroud component has a second thickness and a proximal end of the shroud component has a third thickness, the third thickness larger than the second thickness and the first thickness of the flange.
13. The apparatus of claim 11, wherein the shroud component is an annular shroud surrounding the turbine disc, and a distal end of the shroud component is coupled at an outer surface to a flange of the turbine casing, the flange extending along a length of the shroud component from the distal end to a proximal end of the shroud component, the proximal end proximal to a blade of the turbine disc.
14. The apparatus of claim 1, further comprising a first bearing bush positioned within the turbine casing and a second bearing bush positioned within the compressor casing, the first bearing bush and second bearing bush surrounding bearings of the shaft, an inner diameter of the first bearing bush and the second bearing bush based on a diameter of the bearings.
15. The apparatus of claim 14, wherein the first bearing bush is positioned within the turbine casing and has an outer diameter corresponding to an inner diameter of the turbine casing, and further comprising a first mounting flange defined by the first bearing bush, wherein the first mounting flange defines a plurality of apertures configured to facilitate mounting of the first bearing bush to the turbine casing.
16. The apparatus of claim 14, wherein the second bearing bush is positioned within the compressor casing and has an outer diameter corresponding to an inner diameter of the compressor casing and further comprising a second mounting flange defined by the second bearing bush, wherein the second mounting flange defines a plurality of apertures for mounting the second bearing bush to the compressor casing.
17. The apparatus of claim 1, wherein the compressor casing and the turbine casing are not monolithic, but are coupled to one another through an intermediate spacer centered along the rotational axis, the intermediate spacer having a width and surrounding the shaft, the width of the intermediate spacer selected based on a length of the shaft.
18. The apparatus of claim 17, wherein the intermediate spacer has a surface that defines two depressions that are about the same size as each other but disposed on opposing sides of the intermediate spacer.
19. A turbocharger, comprising:
a compressor casing comprising an air inlet and a blower casing formed as a single, unitary piece with an air inlet wall continuous with a blower casing wall, the air inlet configured to admit air to a compressor wheel of the turbocharger; and
a turbine casing housing a turbine disc mechanically coupled to the compressor wheel, the turbine casing comprising an annular shroud surrounding the turbine disc and an exhaust casing, the shroud integrated and formed as one piece with the exhaust casing, a thickness of the shroud being uniform along a length of the shroud.
20. An apparatus, comprising:
a compressor casing for a turbocharger, the compressor casing defining an air inlet and having a blower casing component, the air inlet configured to admit air to a compressor wheel mechanically coupled to a turbine disc via a shaft, where a ratio of a thickness of an air inlet wall to a thickness of a blower casing wall is a function of a radius of curvature between the air inlet wall and the blower casing wall and a material burst-strength of the air inlet wall and the blower casing wall; and
a turbine casing for the turbocharger, the turbine casing housing the turbine disc, the turbine casing comprising a shroud component surrounding at least a portion of the turbine disc.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. An auxiliary-gas supplying apparatus for combustion engine disposed externally of an intake member communicated with a combustion chamber, comprising:
an ozone generator for generating ozone by using air;
an auxiliary gas generator for generating an auxiliary gas containing ionized oxygen by forcibly decomposing at least a part of the ozone generated by the ozone generator; and
an intake auxiliary-gas supply path for supplying the auxiliary gas which is generated by the auxiliary gas generator and which contains the ionized oxygen, to the intake member,
the auxiliary gas generator is constructed by spirally winding a tubular body including a plurality of bulges protruded inwardly from an inside wall thereof.
2. The auxiliary-gas supplying apparatus for combustion engine according to claim 1, wherein the intake member is an intake manifold, and
wherein the intake auxiliary-gas supply path is in discrete communication with individual branch pipes of the intake manifold.
3. The auxiliary-gas supplying apparatus for combustion engine according to claim 1, wherein the intake member is an intake manifold, and
wherein the intake auxiliary-gas supply path includes a branch path for supplying the auxiliary gas through plural circumferential places of a collecting pipe of the intake manifold or of an intake pipe communicated with the collecting pipe.
4. The auxiliary-gas supplying apparatus for combustion engine according to claim 1, wherein the intake member is made from a synthetic resin.
5. The auxiliary-gas supplying apparatus for combustion engine according to claim 1, further comprising an exhaust auxiliary-gas supply path for supplying the auxiliary gas which is generated by the auxiliary gas generator and which contains the ionized oxygen, to an exhaust path.