Axial loading management in turbomachinery
AssigneeHoneywell International Inc.
InventorKurt Kuster
Life of this patent
Estimating the term…
Abstract
Exemplary vanes for a turbocharger having variable nozzle geometries are disclosed. In one aspect, each of the vanes includes two axial surfaces that are on opposite sides of the vane. The opposite axial surfaces include two corresponding chambers. These chambers are partially exposed to each other through an aperture. Such an aperture allows for some degree of equalization of the pressures in the chambers and, thereby, reduces the axial load exerted by a vane, for example, on the unison ring. In another aspect, each of the vanes includes two opposite airfoil surfaces. At least one of the airfoil surfaces includes a notch that allows a chamber in the nozzle to be pressurized by the exhaust gas. The pressure in the chamber creates a counteracting force that reduces the axial load exerted by a vane.
Claims23
A variable geometry turbocharger comprising:
- a turbine housing having an inlet, a volute connected to the inlet, a nozzle wall adjacent to the volute and an outlet, the turbine housing being arranged to accept exhaust gas from an engine through the inlet and to radially distribute the exhaust gas through the volute;
- a turbine within the turbine housing;
- a plurality of vanes arranged within the turbine housing between the volute and the turbine, the vanes being oriented to direct the exhaust gas from the volute to the turbine, each vane comprising:
- a first chamber adjacent to a first axial surface, the first axial surface oriented adjacent to the nozzle wall;
- a second chamber adjacent to a second axial surface, the second axial surface being opposite and parallel to the first axial surface;
- and
- a first passage between the first chamber and the second chamber;
- wherein the first passage enables gas flow between the first chamber and the second chamber, and wherein the gas flow at least partially equalizes pressures in the first and second chambers.
The variable geometry turbocharger as recited in claim 5, wherein each vane further comprises an aperture adjacent to the second axial surface and wherein the second passage is implemented as a recess on the second axial surface.
A variable geometry turbocharger comprising:
- a turbine housing having an inlet, a volute connected to the inlet, a nozzle wall adjacent to the volute and an outlet, the turbine housing being arranged to accept exhaust gas from an engine through the inlet and to radially distribute the exhaust gas through the volute;
- a turbine within the turbine housing;
- a plurality of nozzle vanes arranged within the turbine housing between the volute and the turbine, the nozzle vanes being oriented to direct the exhaust gas from the volute to the turbine, each of the nozzle vanes comprising:
- a first chamber adjacent to a first axial surface;
- and
- a first passage connecting the first chamber to an area outside the nozzle vane;
- wherein the first passage allows the exhaust gas to enter the first chamber and wherein pressure of the exhaust gas in the first chamber creates a counteracting force that reduces an axial load exerted by a respective one of the nozzle vanes.
A turbocharging apparatus comprising:
- means for receiving and expelling exhaust gas from an engine;
- means for supplying the exhaust gas to a turbine through variable nozzles vanes;
- means for uniformly changing the directions of the variable nozzle vanes by actuating a unison ring;
- and
- means for equalizing pressures within each nozzle vane to reduce an axial loading on the unison ring.
An adjustable nozzle vane of a turbocharger comprising:
- a first chamber oriented adjacent to a first axial surface on the nozzle vane, the first axial surface oriented adjacent to a unison ring configured to actuate the nozzle vane;
- a second chamber oriented adjacent to a second axial surface, the second axial surface oriented opposite the first axial surface;
- and
- a first passage between the first and second chambers;
- wherein the first passage enables gas flow between the first and second chambers and at least partially equalizes pressures between the first and second chambers.
Dependencies are inferred from the claim text.