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US 2018/0128125 A1Published application
Turbine shroud contour exducer relief
AssigneeHoneywell International Inc.
InventorBrian D. Alexander
Life of this patent
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Abstract
A turbocharger turbine having a blade-gap zone between the blades and the shroud wall. The blade-gap zone is larger at and near the exducer than at an upstream location where the shroud wall is at its minimum radius. Also disclosed is a method of customizing and manufacturing a turbine by establishing an optimized blade-gap zone at the exducer, and machining it into a turbine housing.
Claims6
A method of designing and manufacturing a turbine to meet design requirements including one or more metrics from the group of metrics including flow, efficiency, and outlet temperature, comprising:
- providing a base turbine design;
- establishing the one or more metrics for the base turbine design;
- providing a database of modification effects for a plurality of sets of turbine housing machining parameters, each set of turbine housing machining parameters including one or more turbine housing parameters from the group of turbine housing parameters including an extension distance, a radial increase, and a corner geometric configuration;
- selecting an initial set of turbine housing machining parameters for the base turbine design to create a modified turbine design;
- establishing the one or more metrics for the modified turbine design;
- iteratively reselecting the set of turbine housing machining parameters and reestablishing the one or more metrics for the modified turbine design until the one or more metrics are optimized to establish an optimum set of turbine housing machining parameters for the design requirements;
- and
- manufacturing a turbine of the base turbine design and manufacturing the turbine housing to meet the optimum set of turbine housing machining parameters.
5 more elements
Dependencies are inferred from the claim text.