Nozzle Ring Groove Design for Turbocharger Pressure Pulse Dissipation
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Solution Overview
Problem
Conventional nozzle rings in exhaust gas turbochargers cause pressure disturbances that lead to turbine blade excitations, resulting in increased stress and material fatigue, which are complex and costly to address.
Innovation Solution
A nozzle ring design featuring a disc-shaped main body with guide vanes and a groove that connects bores, allowing pressure pulses to dissipate along the main body, reducing rotor blade excitations and stress.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If a nozzle ring is fixed to the bearing housing using bolt-type or screw connection, then the nozzle ring is securely positioned, but pressure disturbances occur which generate turbine blade excitations and increased stress levels
Solution Approach 1:
The harmful fastening means (bolts or screws) are extracted from the system by replacing them with an adhesive bonding connection. This removes the source of pressure disturbances and turbine blade excitations while maintaining the functional connection between the nozzle ring and bearing housing.
Solution Approach 2:
An adhesive bonding agent is introduced as an intermediary substance between the nozzle ring and bearing housing. This adhesive mediator provides secure positioning without creating the pressure disturbances associated with mechanical fastening, thereby eliminating turbine blade excitations.
2Reliability
If conventional fastening means are used to secure the nozzle ring, then reliable positioning is achieved, but complex and costly measures are required to address turbine blade excitations
Solution Approach 1:
The complex and costly measures (inducer/exducer clips, speed limitations, turbine stage redesign) are avoided by extracting the problematic fastening means and replacing them with simple adhesive bonding, thereby reducing device complexity while maintaining reliability.
Solution Approach 2:
The connection method is changed from mechanical (bolts/screws) to chemical bonding (adhesive), fundamentally changing the parameter of connection type. This parameter change eliminates the need for complex corrective measures while maintaining secure positioning.
3Ease of manufacture
If the nozzle ring is designed with through holes for fastening means, then secure mounting is possible, but pressure disturbances are generated that cause material fatigue
Solution Approach 1:
The through holes for fastening means are extracted from the nozzle ring design. By eliminating these holes and using adhesive bonding instead, the source of pressure disturbances is removed, thereby preventing material fatigue in turbine blades while maintaining ease of manufacture through simplified bonding procedures.
Data Source
Figure 1~2d
Figure 3a~3b
Figure 4~5a
AI summary
A nozzle ring (10) for a radial turbine is described. The nozzle ring includes a disc-shaped main body (11) having a central opening (12) for passing a shaft there through. Additionally, the nozzle ring includes guide vanes (14) disposed circumferentially in a radially outer portion on a first surface (11A) of the main body (11). Two or more bores (17) are provided in a radially inner portion of the main body (11). Further, a groove (171) is provided in the first surface (11A) of the main body (11), the groove (171) connecting at least two of the two of more bores (17).