Noise attenuation device for compressor inlet duct

Patent metadata

Field	Value
Publication number	US-2016258447-A1
Application number	US-201415032172-A
Country	US
Kind code	A1
Filing date	Oct 30, 2014
Priority date	Oct 31, 2013
Publication date	Sep 8, 2016
Grant date	—

Abstract

A turbocharger compressor noise attenuation device ( 60, 160 ) is formed separately from the air inlet ( 16 ) of the compressor housing ( 12 ). The device ( 60 ) includes a tapered inner surface ( 66 ) having a minimum diameter portion ( 62 ) that is axially spaced apart from a first end face ( 50 ), a maximum diameter portion ( 64 ) that is between the minimum diameter portion ( 62 ) an opposed second end ( 48 ), and an annular groove ( 72 ) formed in a working face ( 74 ) of the minimum diameter portion that is parallel to the first end face ( 50 ).

First claim

We claim:

1 . An air intake pipe ( 40 ) configured to connect a turbocharger compressor air inlet ( 16 ) to an air intake system of an engine, the air intake pipe ( 40 ) comprising;
an outer surface ( 42 ), an inner surface ( 44 ); a first end ( 46 ) configured to connect to the air intake system, and a second end ( 48 ) opposed to the first end ( 46 ), the second end ( 48 ) including
an annular terminal end face ( 50 ) corresponding to the surface extending between the outer surface ( 42 ) and the inner surface ( 44 ), and
a tapered portion ( 60 ) protruding radially inward from the inner surface ( 44 ) and disposed adjacent to the terminal end face ( 50 ), the tapered portion including
a minimum diameter portion ( 62 ) that is axially spaced apart from the end face ( 50 ),
a maximum diameter portion ( 64 ) that is between the minimum diameter portion and the first end ( 46 ), and
an annular groove ( 72 ) formed in a working face ( 74 ) of the minimum diameter portion ( 62 ) that is parallel to the terminal end face ( 50 ), the groove ( 72 ) extending about a circumference of the inner surface ( 44 ).

2 . The air intake pipe ( 40 ) of claim 1 , wherein the maximum diameter portion ( 64 ) has a diameter that is less than that of the inner surface ( 44 ), whereby a first shoulder ( 68 ) is defined at one end of the tapered portion ( 60 ).

3 . The air intake pipe ( 40 ) of claim 1 , wherein
the maximum diameter portion ( 64 ) has a diameter that is less than that of the inner surface ( 44 ), whereby a first shoulder ( 68 ) is defined at one end of the tapered portion ( 60 ), the first shoulder facing the pipe first end ( 46 ), and the minimum diameter portion ( 62 ) has a diameter (d 3 ) that is less than that of the maximum diameter portion ( 64 ) whereby a second shoulder ( 70 ) corresponding to the working face ( 74 ) is defined at another end of the tapered portion, the second shoulder ( 70 ) facing the pipe second end ( 48 ) and having a larger radial dimension than the first shoulder ( 68 ).

4 . The air intake pipe ( 40 ) of claim 1 , wherein the annular groove ( 72 ) is shaped and dimensioned to receive an end ( 17 ) of the air inlet ( 16 ) in a press fit relationship.

5 . The air intake pipe ( 40 ) of claim 1 , wherein the minimum diameter of the tapered portion ( 60 ) is made to correspond to the minimum diameter of the turbocharger compressor air inlet ( 16 ).

6 . A noise attenuation device ( 160 ) configured to be inserted between an air intake pipe ( 140 ) and an air inlet ( 16 ) of a turbocharger compressor ( 3 ), the noise attenuation device ( 160 ) comprising
a hollow cylindrical body including
a tapered inner surface ( 166 ),
one end corresponding to a minimum diameter portion ( 162 ) of the tapered inner surface ( 166 ),
another end opposed to the one end and corresponding to a maximum diameter portion ( 164 ) of the tapered inner surface ( 166 ), and
an outer surface ( 165 ) that includes
an outwardly-protruding, circumferentially-extending first flange ( 180 ),

wherein the noise attenuation device ( 160 ) is configured to be disposed coaxially within the air inlet ( 16 ) in a manner such that the minimum diameter portion ( 162 ) is downstream with respect to direction of air flow through the air inlet ( 16 ) relative to the maximum diameter portion ( 164 ), and the first flange ( 180 ) engages a corresponding groove ( 154 ) formed on an inner surface of the air inlet ( 16 ) at a location spaced apart from an inlet end ( 17 ) of the air inlet ( 16 ), whereby the body is secured within the air inlet ( 16 ).

7 . The noise attenuation device ( 160 ) of claim 6 , wherein the outer surface ( 158 ) further comprises a second flange ( 178 ) disposed at the another end corresponding to the maximum diameter portion ( 164 ), the second flange ( 178 ) protruding radially outward so as to define a shoulder ( 170 ) that is spaced apart from the another end, and having a radial dimension corresponding to the thickness of a terminal end ( 17 ) of the air inlet ( 16 ), such that when the insert is disposed the air inlet ( 16 ), the shoulder ( 170 ) abuts the terminal end ( 17 ) of the air inlet ( 16 ) and the first flange ( 180 ) resides within the groove ( 154 ).

8 . The noise attenuation device ( 160 ) of claim 6 wherein the noise attenuation device ( 160 ) is formed of an elastic material.

9 . The noise attenuation device ( 160 ) of claim 6 wherein the minimum diameter portion ( 162 ) has a diameter (d 3 ′) that is less than the noise attenuation device outer diameter (d 6 ), whereby a shoulder ( 182 ) is defined at the end corresponding to the minimum diameter portion ( 162 ) which serves as a noise reflecting surface.

10 . The noise attenuation device ( 160 ) of claim 9 , wherein the shoulder ( 182 ) is configured so that when the noise attenuation device is inserted between an air intake pipe ( 140 ) and an air inlet ( 16 ) of a turbocharger compressor ( 3 ), the shoulder ( 182 ) defines a working face ( 174 ) that confronts an air vent passageway ( 20 ) formed in the air inlet ( 16 ).

11 . An exhaust gas turbocharger ( 1 ) comprising:
a turbine ( 2 ) including a turbine housing ( 11 ) and a turbine wheel ( 4 ) disposed in the turbine housing ( 11 ); a compressor ( 3 ) including
a compressor housing ( 12 ) defining a cylindrical air inlet ( 16 );
a compressor wheel ( 5 ) disposed within the compressor housing ( 12 ) adjacent to the air inlet ( 16 ), the compressor wheel ( 3 ) connected to the turbine wheel ( 4 ) via a shaft ( 6 );
an air intake pipe ( 140 ) connected to the air inlet ( 16 ), the air intake pipe ( 140 ) comprising:
a first end ( 146 );
a second end ( 148 ) opposed to the first end ( 146 ), the second end ( 148 ) connected to the air inlet ( 16 );
a longitudinal axis ( 152 ) extending between the first end ( 146 ) and the second end ( 148 ); and
a noise attenuation device ( 160 ) protruding inward from, and extending circumferentially about, an inner surface ( 144 ) of the air intake pipe ( 140 ) adjacent the second end ( 148 ), wherein the noise attenuation device ( 160 ) is tapered along an axial direction of the air intake pipe ( 140 ) such that a minimum diameter portion ( 162 ) of the noise attenuation device ( 160 ) is disposed at the second end ( 148 ).

12 . The exhaust gas turbocharger of claim 11 , wherein the noise attenuation device ( 160 ) includes a circumferential groove ( 72 ) that receives a terminal end of the air inlet ( 16 ).

13 . The exhaust gas turbocharger of claim 12 wherein the groove ( 72 ) opens facing the compressor wheel ( 5 ), and is shaped and dimensioned to receive an end of the air inlet ( 16 ) in a press fit relationship.

14 . The exhaust gas turbocharger of claim 11 wherein the noise attenuation device ( 160 ) is formed as an insert that is configured to be separable from, and received within, the air inlet ( 16 ), the insert comprising:
an outer surface ( 142 ) that includes an outwardly-protruding, circumferentially-extending first flange ( 180 ) that is configured to be received in a corresponding groove ( 154 ) formed on an inner surface of the air inlet ( 16 ), such that when the first flange ( 180 ) is engaged with the groove ( 154 ), the insert is secured within the air inlet ( 16 ).

15 . The exhaust gas turbocharger of claim 14 , wherein the outer surface ( 142 ) of the insert further comprises a second flange ( 178 ) disposed at one end, the flange ( 178 ) protruding radially outward so as to define a shoulder that is spaced apart from the one end and has a radial dimension corresp

Assignees

• Borgwarner Inc

Inventors

• Day Andrew
• Mawer James
• Richardson Andrew
• Chaggar Sanjit
• Birnie Steve

Classifications

• F04D29/284

  for compressors · CPC title

• F04D17/10

  for compressing or evacuating · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F04D25/045

  the pump wheel carrying the fluid driving means, e.g. turbine blades · CPC title