Adjustable-trim centrifugal compressor, and turbocharger having same

Patent metadata

Field	Value
Publication number	US-9777640-B2
Application number	US-201414532278-A
Country	US
Kind code	B2
Filing date	Nov 4, 2014
Priority date	Nov 4, 2014
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. The inlet-adjustment mechanism includes an axially elongated ring. In the open position, the radially outer surface of the ring is spaced from a tapering inner surface of the air inlet so that air can flow in an annular passage between the tapering surface and the ring. In the closed position, the ring abuts the tapering surface to close off the annular passage, whereby the effective inlet diameter is then defined by the inner diameter of the ring at its trailing edge. Movement of the inlet-adjustment mechanism from the open position to the closed position is effective to shift the compressor's surge line to lower flow rates.

First claim

What is claimed is:

1. A turbocharger, 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 receiving exhaust gas and supplying the exhaust gas to the turbine wheel;
a centrifugal compressor assembly comprising a compressor housing and a compressor wheel mounted in the compressor housing and connected to the rotatable shaft for rotation therewith, the compressor wheel having blades and defining an inducer portion, the compressor housing defining an air inlet for leading air axially into the compressor wheel, the compressor housing further defining a volute for receiving compressed air discharged radially outwardly from the compressor wheel, the air inlet having an inner surface a portion of which comprises a cylindrical sliding surface that extends for an axial length along a downstream direction, followed by a shroud surface that is adjacent to outer tips of the blades of the compressor wheel, the air inlet further defining a tapering inner surface that is axially disposed between the sliding surface and the shroud surface and extends for an axial length along the downstream direction, the tapering inner surface being smaller in diameter at a downstream end of the tapering inner surface than at an upstream end thereof;
a compressor inlet-adjustment mechanism disposed in the air inlet of the compressor housing and movable between an open position and a closed position, the inlet-adjustment mechanism comprising an axially elongated ring comprising a tubular wall whose inner surface becomes smaller in diameter in the downstream direction toward the compressor wheel such that the diameter of the inner surface is smaller at a downstream end of the ring than at an upstream end of the ring, the downstream end of the ring defining a trailing edge, the inner diameter of the ring at the trailing edge being smaller than an inner diameter of the shroud surface of the compressor housing at the inducer portion of the compressor wheel,
wherein the inlet-adjustment mechanism further comprises a support portion that is joined by a plurality of circumferentially spaced struts to the ring, the support portion having a radially outer surface that engages the cylindrical sliding surface of the air inlet and is movable along the cylindrical sliding surface,
wherein the ring is arranged so that when the inlet-adjustment mechanism is in the open position the trailing edge of the ring is spaced from the tapering inner surface of the air inlet such that there is an annular passage between the tapering inner surface and the ring for a flow of air therethrough and the trailing edge is axially spaced relatively farther upstream from the inducer portion such that an effective diameter of the air inlet at the inducer portion is determined by the shroud surface, and wherein the trailing edge of the ring in the closed position abuts the tapering inner surface to eliminate said annular passage and is axially spaced relatively closer to the inducer portion of the compressor wheel such that the effective diameter of the air inlet at the inducer portion is determined by the inner diameter of the ring at the trailing edge.

2. The turbocharger of claim 1 , wherein the struts have an airfoil cross-sectional shape in a θ-z plane.

3. The turbocharger of claim 1 , wherein there are four said struts circumferentially spaced apart.

4. The turbocharger of claim 1 , wherein the tubular wall has an airfoil cross-sectional shape in an r-z plane.

5. The turbocharger of claim 1 , wherein the diameter of the inner surface of the ring at the trailing edge is between 0.45 and 0.98 times d 1S , where d 1S is a diameter of the inducer portion of the compressor wheel.

6. The turbocharger of claim 5 , wherein the tubular wall has an axial length L and the trailing edge of the tubular wall in the closed position is spaced an axial distance S from a leading edge of the inducer portion of the compressor wheel, and wherein L is larger than S.

7. The turbocharger of claim 6 , wherein S<8.5(d 1S −d r ), where d r is the diameter of the inner surface of the ring at the trailing edge thereof.

8. A turbocharger, 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 receiving exhaust gas and supplying the exhaust gas to the turbine wheel;
a centrifugal compressor assembly comprising a compressor housing and a compressor wheel mounted in the compressor housing and connected to the rotatable shaft for rotation therewith, the compressor wheel having blades and defining an inducer portion, the compressor housing defining an air inlet for leading air axially into the compressor wheel, the compressor housing further defining a volute for receiving compressed air discharged radially outwardly from the compressor wheel, the air inlet having an inner surface a portion of which comprises a cylindrical sliding surface that extends for an axial length along a downstream direction, followed by a shroud surface that is adjacent to outer tips of the blades of the compressor wheel;
a compressor inlet-adjustment mechanism disposed in the air inlet of the compressor housing and movable between an open position and a closed position, the inlet-adjustment mechanism comprising an axially elongated ring whose inner surface becomes smaller in diameter in the downstream direction toward the compressor wheel such that the diameter of the inner surface is smaller at a downstream end of the ring than at an upstream end of the ring, wherein the ring is formed by a wall configured substantially as a body having a funnel shape, wherein the wall of the ring includes openings through the wall to allow air to pass through the openings, the downstream end of the ring defining a trailing edge, the inner diameter of the ring at the trailing edge being smaller than an inner diameter of the shroud surface of the compressor housing at the inducer portion of the compressor wheel,
wherein the ring is arranged so that when the inlet-adjustment mechanism is in the open position the trailing edge of the ring is axially spaced relatively farther upstream from the inducer portion such that an effective diameter of the air inlet at the inducer portion is determined by the shroud surface, and wherein the trailing edge of the ring in the closed position is axially spaced relatively closer to the inducer portion of the compressor wheel such that the effective diameter of the air inlet at the inducer portion is determined by the inner diameter of the ring at the trailing edge, and wherein the openings in the ring are unblocked when the ring is in the open position so that air passes through the openings from an interior to an exterior of the ring before encountering the inducer portion of the compressor wheel, and the compressor housing is configured to block the openings when the ring is in the closed position so that air is substantially prevented from passing through the openings.

Assignees

• Honeywell Int Inc

Inventors

• Mohtar Hani
• Smith William Joseph
• Pees Stephane
• Petitjean Dominique
• Roberts Quentin

Classifications

• Y02T10/144

  Cross-Sectional Technologies · mapped topic

• F02B2037/125

  Control for avoiding pump stall or surge · CPC title

• F02B37/225

  air passages · CPC title

• F04D27/0253

  by throttling (F04D27/0246 takes precedence) · CPC title

• F02C9/16 Primary

  Control of working fluid flow (F02C9/48 takes precedence; control of air-intake flow F02C7/057) · CPC title