Turbocharger variable-vane cartridge with nozzle ring and pipe secured by two-piece self-centering spacers

Patent metadata

Field	Value
Publication number	US-10087774-B2
Application number	US-201414499730-A
Country	US
Kind code	B2
Filing date	Sep 29, 2014
Priority date	Sep 29, 2014
Publication date	Oct 2, 2018
Grant date	Oct 2, 2018

Abstract

A variable-nozzle turbocharger includes a variable vane mechanism that has an annular nozzle ring supporting an array of rotatable vanes, an insert having a tubular portion sealingly received into a bore of the turbine housing and having a nozzle portion extending radially out from one end of the tubular portion and being axially spaced from the nozzle ring with the vanes therebetween, and a plurality of two-piece self-centering spacer assemblies connected between the nozzle portion of the insert and the nozzle ring. Each spacer assembly comprises a tubular sleeve and a separate pin that passes through the through-passage of the sleeve, end portions of the pin being secured respectively to the nozzle ring and the nozzle portion. One end of each sleeve has a conical surface and engages in a corresponding conical countersink in the adjacent face of the nozzle ring or nozzle portion.

First claim

What is claimed is:

1. A turbocharger having a variable-nozzle turbine, comprising:
a turbine assembly comprising a turbine housing and a turbine wheel mounted in the turbine housing and connected to a rotatable shaft for rotation therewith, the turbine housing defining a chamber surrounding the turbine wheel for receiving exhaust gas and for supplying the exhaust gas to the turbine wheel, the turbine assembly defining a nozzle leading from the chamber generally radially inwardly to the turbine wheel, the turbine housing further defining an axially extending bore through which exhaust gas is discharged after passing through the turbine wheel;
a compressor assembly comprising a compressor housing and a compressor wheel mounted in the compressor housing and connected to the rotatable shaft for rotation therewith;
a center housing connected between the compressor housing and the turbine housing; and
a generally annular nozzle ring and an array of vanes circumferentially spaced about the nozzle ring and disposed in the nozzle such that exhaust gas flows between the vanes to the turbine wheel, each vane being rotatably mounted to the nozzle ring and connected to a rotatable actuator ring such that rotation of the actuator ring rotates the vanes for regulating exhaust gas flow to the turbine wheel;
an insert having a tubular portion sealingly received into the bore of the turbine housing and having a nozzle portion extending generally radially out from one end of the tubular portion, the nozzle portion being axially spaced from the nozzle ring such that the vanes extend between the nozzle ring and the nozzle portion; and
a plurality of spacers connected between the nozzle portion of the insert and the nozzle ring for securing the nozzle ring to the insert and maintaining an axial spacing between the nozzle portion of the insert and the nozzle ring;
wherein each of the spacers comprises a two-piece self-centering assembly comprising a tubular sleeve and a pin, each sleeve defining a through-passage and each corresponding pin passing through the through-passage, each pin having a first end portion that projects from a first end of the sleeve and passes through an aperture defined by the nozzle ring and having a second end portion that projects from an opposite second end of the sleeve and passes through an aperture defined in the nozzle portion of the insert, the first end of each pin being secured to the nozzle ring and the second end of each pin being secured to the nozzle portion of the insert;
wherein the pins are secured to the nozzle ring and the nozzle portion so as to draw the nozzle ring and the nozzle portion axially toward each other so that the first ends of the sleeves bear against a face of the nozzle ring and the second ends of the sleeves bear against a face of the nozzle portion, the sleeves keeping the nozzle ring and the nozzle portion spaced apart, and
wherein one of the first and second ends of each sleeve forms a conical surface that is coaxial with the through-passage of the sleeve, and the face against which the one end of each sleeve bears defines a corresponding conical countersink that is coaxial with the aperture through which the end portion of the pin passes, such that engagement between the conical surfaces of the sleeves and the conical countersinks maintains the through-passages of the sleeves coaxial with the apertures for the pins, whereby the self-centering assemblies maintain the sleeves substantially coaxial with the corresponding pins.

2. The turbocharger of claim 1 , wherein the conical countersinks are defined in the face of the nozzle ring and the first ends of the sleeves define the conical surfaces that engage in the countersinks.

3. A variable-nozzle turbine cartridge for a variable-nozzle turbine, the cartridge comprising an assembly of:
a generally annular nozzle ring and an array of vanes circumferentially spaced about the nozzle ring, each vane being rotatably mounted to the nozzle ring and connected to a rotatable actuator ring such that rotation of the actuator ring rotates the vanes for regulating exhaust gas flow therethrough;
an insert having a tubular portion configured for being sealingly received into a bore of a turbine housing and having a nozzle portion extending generally radially out from one end of the tubular portion, the nozzle portion being axially spaced from the nozzle ring such that the vanes extend between the nozzle ring and the nozzle portion; and
a plurality of spacers connected between the nozzle portion of the insert and the nozzle ring for securing the nozzle ring to the insert and maintaining an axial spacing between the nozzle portion of the insert and the nozzle ring;
wherein each of the spacers comprises a two-piece self-centering assembly comprising a tubular sleeve and a pin, each sleeve defining a through-passage and each corresponding pin passing through the through-passage, each pin having a first end portion that projects from a first end of the sleeve and passes through an aperture defined by the nozzle ring and having a second end portion that projects from an opposite second end of the sleeve and passes through an aperture defined in the nozzle portion of the insert, the first end of each pin being secured to the nozzle ring and the second end of each pin being secured to the nozzle portion of the insert;
wherein the pins are secured to the nozzle ring and the nozzle portion so as to draw the nozzle ring and the nozzle portion axially toward each other so that the first ends of the sleeves bear against a face of the nozzle ring and the second ends of the sleeves bear against a face of the nozzle portion, the sleeves keeping the nozzle ring and the nozzle portion spaced apart, and
wherein one of the first and second ends of each sleeve forms a conical surface that is coaxial with the through-passage of the sleeve, and the face against which the one end of each sleeve bears defines a corresponding conical countersink that is coaxial with the aperture through which the end portion of the pin passes, such that engagement between the conical surfaces of the sleeves and the conical countersinks maintains the through-passages of the sleeves coaxial with the apertures for the pins, whereby the self-centering assemblies maintain the sleeves substantially coaxial with the corresponding pins.

4. The variable-nozzle turbine cartridge of claim 3 , wherein the conical countersinks are defined in the face of the nozzle ring and the first ends of the sleeves define the conical surfaces that engage in the countersinks.

Assignees

• Honeywell Int Inc

Inventors

• Barthelet Pierre
• Morand Nicolas
• Severin Emmanuel
• Beltrami Calogero
• Eumont Vincent
• Abel Francis
• Gerard Arnaud
• Tingaud Aurelien
• Krishnamoorthy Jayavenkateshwaran

Classifications

• F02C6/12 Primary

  Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure · CPC title

• F05D2230/642

  using maintaining alignment while permitting differential dilatation · CPC title

• F01D9/048

  for radial admission · CPC title

• F05D2250/51

  Inlet · CPC title

• F02B37/24

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