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 |
20120107134 | APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES - A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that extends from a connection at the root to the approximate radial height of the platform, wherein, the interior cooling passage comprises a high-pressure coolant region and a low-pressure coolant region, and wherein a pressure side of the platform comprises a topside extending circumferentially from the airfoil to a pressure side slashface. The platform cooling arrangement may include: a platform cavity formed within the pressure side of the platform, a high-pressure connector that connects the platform cavity to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the platform cavity to the low-pressure coolant region of the interior cooling passage; and a pin bank formed within the platform cavity that includes radial pins. | 05-03-2012 |
20120156055 | APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES - A configuration of cooling channels through the interior of a turbine rotor blade, the turbine rotor blade including a platform at an interface between an airfoil and a root. In one embodiment, the configuration of cooling channels includes: an interior cooling passage that is configured to extend from a connection with a coolant source in the root to the interior of the airfoil; a platform cooling channel that traverses at least a portion of the platform; a turndown extension that includes a first section, which comprises a connection with the platform cooling channel, and a second section, which comprises a radially oriented cooling channel; and a connector that extends from a connector opening formed through an outer face of the root to a connection with the interior cooling passage and, therebetween, bisects the second section of the turndown extension. | 06-21-2012 |
20130064671 | AIRFOIL SHAPE FOR TURBINE BUCKET AND TURBINE INCORPORATING SAME - A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape. | 03-14-2013 |
20130101387 | SYSTEM AND METHOD FOR INTEGRATING SECTIONS OF A TURBINE - A system and method for integrating sections of a turbine are provided. In one system, a turbine includes a last stage bucket section with a first annular outer wall that is angled with respect to a centerline of the turbine at a first angle average. The turbine also includes a diffuser section having a second annular outer wall that is angled with respect to the centerline of the turbine at a second angle average for improving radial swirl. The first angle average is greater than the second angle average. | 04-25-2013 |
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 |
20130039771 | TURBOMACHINE COMPONENT HAVING AN AIRFOIL CORE SHAPE - A turbomachine component includes a turbine stator nozzle member having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and 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 core shape. | 02-14-2013 |
20130104550 | TURBINE OF A TURBOMACHINE | 05-02-2013 |
20130136607 | TURBINE NOZZLE AIRFOIL PROFILE - The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape. | 05-30-2013 |
20130136608 | TURBINE BUCKET AIRFOIL PROFILE - The present application provides a turbine bucket including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape. | 05-30-2013 |
20130170977 | Gas Turbine Nozzle with a Flow Groove - The present application provides a turbine nozzle. The turbine nozzle may include an airfoil with a leading edge and a trailing edge and a flow groove extending from the leading edge to the trailing edge. | 07-04-2013 |
20130170997 | Gas Turbine Nozzle with a Flow Fence - The present application provides a turbine nozzle. The turbine nozzle may include an airfoil with a leading edge and a trailing edge and a flow fence extending from the leading edge to the trailing edge. | 07-04-2013 |