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Bielek
Craig A. Bielek, Simpsonville, SC US
| Patent application number | Description | Published |
|---|---|---|
| 20100158678 | AIRFOIL SHAPE FOR A TURBINE NOZZLE - An article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape. | 06-24-2010 |
| 20100166558 | METHODS AND APPARATUS RELATING TO IMPROVED TURBINE BLADE PLATFORM CONTOURS - A flow directing assembly for use in a turbine engine comprising: a plurality of circumferentially spaced blades, each of the blades including a radial projecting airfoil with a concave pressure side and a convex suction side that extend from a platform; and a plurality of flow passages, each flow passage defined by the airfoils of neighboring blades and an inner wall formed by abutting platforms of neighboring blades, the inner wall forming the inner radial boundary of the flow passage; wherein the inner wall of one or more of the flow passages comprises means for reducing frictional losses between the flow through the turbine engine and the inner wall. The means for reducing frictional losses may comprise a non-axisymmetrical trough positioned between neighboring airfoils that is configured to reduce frictional losses. | 07-01-2010 |
Craig Allen Bielek, Simpsonville, SC US
| Patent application number | Description | Published |
|---|---|---|
| 20090035145 | Airfoil shape for a turbine bucket and turbine incorporating same - Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z′ set forth Table I wherein X and Y values are in inches and the Z′ values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z′ values by the height of the airfoil in inches and adding the radius of the airfoil base. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.0.060 inches in directions normal to the surface of the airfoil. | 02-05-2009 |
| 20090162193 | TURBINE INLET GUIDE VANE WITH SCALLOPED PLATFORM AND RELATED METHOD - A nozzle segment is disclosed that includes a first platform configured to be connected with a casing of a gas turbine engine, a second platform configured to be connected with the casing, the second platform being disposed apart from the first platform in a radial direction of the gas turbine engine, and a plurality of blades disposed between the first and second platforms and connected thereto, a portion of an inside surface of the first platform or the second platform being scalloped so as to increase a throat area of the nozzle segment in order to increase the nozzle segment's mass flow rate handling capability. | 06-25-2009 |
Craig Allen Bielek, Greenville, SC US
| Patent application number | Description | Published |
|---|---|---|
| 20120042654 | TIP FLOWPATH CONTOUR - An apparatus is provided and includes a turbine including a casing and a turbine bucket having a tip proximate to the casing and a trailing edge defined relative to a direction of fluid flow through the turbine and a diffuser, defined between a central surface and a downstream section of the casing, which is fluidly coupled to the turbine and disposed downstream from the trailing edge, a slope of the downstream section of the casing being angled by at least 6 degrees relative to a slope of the tip within about 0.5 turbine bucket chord lengths as measured at the tip from the trailing edge, and the central surface and the downstream section of the casing being at least substantially parallel or divergent from the trailing edge. | 02-23-2012 |
| 20120045324 | HUB FLOWPATH CONTOUR - An apparatus is provided and includes a turbine including a platform, a casing and a turbine bucket having a hub coupled to the platform and a trailing edge defined relative to a direction of fluid flow through the turbine and a diffuser, defined between a central surface and a downstream section of the casing, which is fluidly coupled to the turbine and disposed downstream from the trailing edge, a slope of the hub being angled by at least 6 degrees relative to a slope of the central surface within about 0.5 turbine bucket chord lengths as measured at the hub from the trailing edge, and the central surface and the downstream section of the casing being at least substantially parallel or divergent from the trailing edge. | 02-23-2012 |
Yan Bielek, Cumberland, RI US
| Patent application number | Description | Published |
|---|---|---|
| 20110104376 | LIQUID FORMULATIONS FOR COATING AND PRINTING SUBSTRATES - A method is disclosed of preparing a liquid formulation for application as a deposit on a substrate. The method includes the steps of providing a liquid having a first viscosity in a non-evaporative state; and adding an amine-acid adduct to the liquid to form a mixture having a second viscosity greater than the first viscosity. The amine-acid adduct is evaporative such that the amine-acid adduct is substantially completely removed from the deposit in a functionally dry state. | 05-05-2011 |