Turbocharger with variable-vane turbine nozzle having a bypass mechanism integrated with the vanes

Patent metadata

Field	Value
Publication number	US-9938894-B2
Application number	US-201514705083-A
Country	US
Kind code	B2
Filing date	May 6, 2015
Priority date	May 6, 2015
Publication date	Apr 10, 2018
Grant date	Apr 10, 2018

Abstract

A turbocharger includes a variable turbine nozzle defined between a nozzle ring and a pipe flange, and having a plurality of circumferentially spaced vanes rotatably mounted on the nozzle ring such that the vanes are pivotable. Each vane includes an airfoil section and a disk section rigidly affixed to an end of the airfoil section, the disk section being disposed against a face of the pipe flange, each disk section having a plurality of perforations extending axially therethrough. The pipe flange has a corresponding number of holes for each disk section of the vanes, the holes being positioned such that as each vane is rotated the perforations in the disk sections and the holes in the pipe flange of the insert become aligned in some positions of the vanes, allowing exhaust gas to pass between the nozzle and a space on an opposite side of the pipe flange from the nozzle.

First claim

What is claimed is:

1. A turbocharger comprising:
a compressor comprising a compressor housing and a compressor wheel disposed in the compressor housing;
a turbine housing defining a bore extending axially through the turbine housing and defining an exhaust gas inlet and an annular volute that receives exhaust gas via the exhaust gas inlet, the volute extending circumferentially about the bore, and a turbine wheel disposed within the turbine housing and arranged for receiving exhaust gas from the volute and expanding the exhaust gas and discharging the exhaust gas into the bore, the compressor wheel and the turbine wheel being affixed to opposite ends of a shaft;
a turbine nozzle extending from the volute radially inwardly to the turbine wheel, the turbine nozzle being defined between a first wall and a second wall axially spaced from the first wall;
a variable-vane assembly comprising a fixed nozzle ring and a plurality of circumferentially spaced vanes rotatably mounted on the nozzle ring such that the vanes are each rotatable about respective vane pivot axes, the nozzle ring defining the first wall of the turbine nozzle, each vane including an airfoil section disposed in the nozzle and an axle rigidly attached to and protruding from a first end of the airfoil section adjacent the nozzle ring, the axles being received respectively into holes in the nozzle ring such that the axles are rotatable in the holes for pivoting of the vanes about the vane pivot axes;
an insert having a pipe section sealingly received into the bore of the turbine housing and a pipe flange extending radially out from one end of the pipe section, the pipe flange forming the second wall of the turbine nozzle and being axially spaced from the nozzle ring such that the vanes extend between the nozzle ring and the pipe flange;
wherein each vane includes a disk section rigidly affixed to a second end of the airfoil section, the disk section being disposed against a face of the pipe flange of the insert, each disk section having a plurality of perforations extending axially therethrough, the pipe flange of the insert having a corresponding number of holes for each disk section of the vanes, the holes being positioned such that as the vanes are rotated the perforations in the disk sections and the holes in the pipe flange of the insert become aligned in some positions of the vanes, allowing exhaust gas to pass between the nozzle and a space on an opposite side of the pipe flange from the nozzle.

2. The turbocharger of claim 1 , wherein the perforations and the holes are positioned such that the perforations become aligned with the holes only from a mid-open position to a fully-open position of the vanes.

3. The turbocharger of claim 1 , wherein when the perforations and holes are aligned, exhaust gas flows from the turbine housing volute through the aligned perforations and holes, from a side of the pipe flange opposite from the nozzle, and proceeds into the nozzle in a direction orthogonal to the exhaust gas flowing through the vanes so as to disrupt the flow through the vanes and thereby cause turbine stage efficiency to be reduced.

4. The turbocharger of claim 1 , further comprising an additional sealed shroud component attached between the pipe flange and the pipe section of the insert so as to form a sealed chamber in communication with the holes in the pipe flange, the pipe section of the insert including communication holes providing communication between the sealed chamber and the turbine housing bore downstream of the turbine wheel, such that when the disk section perforations and pipe flange holes are aligned, a portion of the exhaust gas flowing through the nozzle can proceed through the aligned perforations and holes into the sealed chamber, and then from the sealed chamber through the communication holes into the bore.

Assignees

• Honeywell Int Inc

Inventors

• Groves Chris
• Marsal Damien
• Sibille Stephane
• Tingaud Aurelien
• Lombard Alain

Classifications

• F02B37/24 Primary

  by using pumps or turbines with adjustable guide vanes · CPC title

• F05D2260/606

  Bypassing the fluid · CPC title

• F05D2220/40

  in turbochargers · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F01D17/165

  for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line (F01D17/167 takes precedence) · CPC title