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Laflen
James D. Laflen, Bellevue, WA US
| Patent application number | Description | Published |
|---|---|---|
| 20090327324 | METHOD OF REFACTORING A RUNNING DATABASE SYSTEM - A database development system is provided. The system includes a current-state source representation of a database that can be captured in a model of the database and a metadata component that preserves user intentions describing when a user interacts with the system to perform a refactoring operation (or other code enhancement) for use in subsequent operations by the system. A deployment component is provided that utilizes the preserved user intentions to optimize behavioral upgrades to the system, where simulations can be run against the model to facilitate efficient and automated deployments. | 12-31-2009 |
James Harvey Laflen, Cincinnati, OH US
| Patent application number | Description | Published |
|---|---|---|
| 20100074745 | DUAL STAGE TURBINE SHROUD - A turbine shroud includes a shroud hanger having an arcuate panel from which three inner hooks extend inwardly, and from which two outer hooks extend outwardly therefrom. The two outer hooks effect a statically determinate configuration of the shroud. | 03-25-2010 |
| 20100111682 | CRENELATED TURBINE NOZZLE - A turbine nozzle includes a row of vanes extending radially between annular outer and inner bands. The outer band includes a pair of radial flanges defining an annular seal groove therebetween. One of the flanges is crenelated to improve nozzle life. | 05-06-2010 |
James Harvey Laflen, Loveland, OH US
| Patent application number | Description | Published |
|---|---|---|
| 20080206042 | METHODS AND SYSTEM FOR RECUPERATED CIRCUMFERENTIAL COOLING OF INTEGRAL TURBINE NOZZLE AND SHROUD ASSEMBLIES - A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, circumferentially mixing the cooling air in a plenum defined within the leading edge to substantially uniformly distribute the cooling air throughout the gap, and directing the cooling air in the gap through at least one cooling hole formed between the plenum and the inner surface. | 08-28-2008 |