Patent application number | Description | Published |
20110033311 | Turbine Airfoil Cooling System with Pin Fin Cooling Chambers - A cooling system for a turbine airfoil having at least one pin fin with a dimpled outer surface is disclosed. The dimpled outer surface increases the cooling efficiency of the pin fin, which creates numerous efficiencies, including thermal efficiencies, manufacturing efficiencies and the like. The dimples may be formed from shapes including, but not limited to, circular, oval, racetrack, and hemispherical. The dimples may be aligned in a variety of configurations. | 02-10-2011 |
20110033312 | COMPOUND COOLING FLOW TURBULATOR FOR TURBINE COMPONENT - Multi-scale turbulation features, including first turbulators ( | 02-10-2011 |
20110038734 | Turbine Blade Having a Constant Thickness Airfoil Skin - A turbine blade is provided for a gas turbine comprising: a support structure comprising a base defining a root of the blade and a framework extending radially outwardly from the base, and an outer skin coupled to the support structure framework. The skin has a generally constant thickness along substantially the entire radial extent thereof. The framework and the skin define an airfoil of the blade. | 02-17-2011 |
20110058949 | Turbine Airfoil Fabricated From Tapered Extrusions - An airfoil ( | 03-10-2011 |
20110110762 | Damping Element for Reducing the Vibration of an Airfoil - An airfoil ( | 05-12-2011 |
20110142654 | Turbine Blade Damping Device With Controlled Loading - A damping structure for a turbomachine rotor. The damping structure including an elongated snubber element including a first snubber end rigidly attached to a first blade and extending toward an adjacent second blade, and an opposite second snubber end positioned adjacent to a cooperating surface associated with the second blade. The snubber element has a centerline extending radially inwardly in a direction from the first blade toward the second blade along at least a portion of the snubber element between the first and second snubber ends. Rotational movement of the rotor effects relative movement between the second snubber end and the cooperating surface to position the second snubber end in frictional engagement with the cooperating surface with a predetermined damping force determined by a centrifugal force on the snubber element. | 06-16-2011 |
20110171023 | AIRFOIL INCORPORATING TAPERED COOLING STRUCTURES DEFINING COOLING PASSAGEWAYS - A gas turbine engine ( | 07-14-2011 |
20110194939 | Snubber Assembly for Turbine Blades - A snubber associated with a rotatable turbine blade in a turbine engine, the turbine blade including a pressure sidewall and a suction sidewall opposed from the pressure wall. The snubber assembly includes a first snubber structure associated with the pressure sidewall of the turbine blade, a second snubber structure associated with the suction sidewall of the turbine blade, and a support structure. The support structure extends through the blade and is rigidly coupled at a first end portion thereof to the first snubber structure and at a second end portion thereof to the second snubber structure. Centrifugal loads exerted by the first and second snubber structures caused by rotation thereof during operation of the engine are at least partially transferred to the support structure, such that centrifugal loads exerted on the pressure and suctions sidewalls of the turbine blade by the first and second snubber structures are reduced. | 08-11-2011 |
20110194943 | COOLED SNUBBER STRUCTURE FOR TURBINE BLADES - A turbine blade assembly in a turbine engine. The turbine blade assembly includes a turbine blade and a first snubber structure. The turbine blade includes an internal cooling passage containing cooling air. The first snubber structure extends outwardly from a sidewall of the turbine blade and includes a hollow interior portion that receives cooling air from the internal cooling passage of the turbine blade. | 08-11-2011 |
20110217178 | TURBINE AIRFOIL HAVING OUTBOARD AND INBOARD SECTIONS - A turbine airfoil usable in a turbine engine and formed from at least an outboard section and an inboard section such that an inner end of the outboard section is attached to an outer end of the inboard section. The outboard section may be configured to provide a tip having adequate thickness and may extend radially inward from the tip with a generally constant cross-sectional area. The inboard section may be configured with a tapered cross-sectional area to support the outboard section. | 09-08-2011 |
20110243724 | TURBINE AIRFOIL TO SHROUND ATTACHMENT - A turbine airfoil ( | 10-06-2011 |
20110299990 | TURBINE AIRFOIL WITH OUTER WALL THICKNESS INDICATORS - A turbine airfoil usable in a turbine engine and including a depth indicator for determining outer wall blade thickness. The airfoil may include an outer wall having a plurality of grooves in the outer surface of the outer wall. The grooves may have a depth that represents a desired outer surface and wall thickness of the outer wall. The material forming an outer surface of the outer wall may be removed to be flush with an innermost point in each groove, thereby reducing the wall thickness and increasing efficiency. The plurality of grooves may be positioned in a radially outer region of the airfoil proximate to the tip. | 12-08-2011 |
20120034097 | COMPONENT WITH INSPECTION-FACILITATING FEATURES - A turbine airfoil can be formed with features to facilitate measurement of its wall thickness. An outer wall of the airfoil can include an outer surface and an inner surface. The outer surface of the airfoil can have an outer inspection target surface, and the inner surface of the airfoil can have an inner inspection target surface. The inner and outer target surfaces can define substantially flat regions in surfaces that are otherwise highly contoured. The inner and outer inspection target surfaces can be substantially aligned with each other. The inner and outer target surfaces can be substantially parallel to each other. As a result of these arrangements, a highly accurate measurement of wall thickness can be obtained. In one embodiment, the outer inspection target surface can be defined by an innermost surface of a groove formed in the outer surface of the outer wall of the airfoil. | 02-09-2012 |
20120070306 | TURBINE COMPONENT COOLING CHANNEL MESH WITH INTERSECTION CHAMBERS | 03-22-2012 |
20120177503 | COMPONENT COOLING CHANNEL - A cooling channel ( | 07-12-2012 |
20120201674 | COOLING MODULE DESIGN AND METHOD FOR COOLING COMPONENTS OF A GAS TURBINE SYSTEM - A cooling arrangement in a gas turbine system ( | 08-09-2012 |
20120207614 | INTEGRATED AXIAL AND TANGENTIAL SERPENTINE COOLING CIRCUIT IN A TURBINE AIRFOIL - A continuous serpentine cooling circuit forming a progression of radial passages ( | 08-16-2012 |
20120263575 | LOW PRESSURE COOLING SEAL SYSTEM FOR A GAS TURBINE ENGINE - A low pressure cooling system for a turbine engine for directing cooling fluids at low pressure, such as at ambient pressure, through at least one cooling fluid supply channel and into a cooling fluid mixing chamber positioned immediately downstream from a row of turbine blades extending radially outward from a rotor assembly to prevent ingestion of hot gases into internal aspects of the rotor assembly. The low pressure cooling system may also include at least one bleed channel that may extend through the rotor assembly and exhaust cooling fluids into the cooling fluid mixing chamber to seal a gap between rotational turbine blades and a downstream, stationary turbine component. Use of ambient pressure cooling fluids by the low pressure cooling system results in tremendous efficiencies by eliminating the need for pressurized cooling fluids for sealing this gap. | 10-18-2012 |
20120269647 | COOLED AIRFOIL IN A TURBINE ENGINE - An airfoil in a gas turbine engine includes an outer wall and an inner wall. The outer wall includes a leading edge, a trailing edge opposed from the leading edge in a chordal direction, a pressure side, and a suction side. The inner wall is coupled to the outer wall at a single chordal location and includes portions spaced from the pressure and suction sides of the outer wall so as to form first and second gaps between the inner wall and the respective pressure and suction sides. The inner wall defines a chamber therein and includes openings that provide fluid communication between the respective gaps and the chamber. The gaps receive cooling fluid that provides cooling to the outer wall as it flows through the gaps. The cooling fluid, after traversing at least substantial portions of the gaps, passes into the chamber through the openings in the inner wall. | 10-25-2012 |
20130004294 | DUCTILE ALLOYS FOR SEALING MODULAR COMPONENT INTERFACES - A vane assembly ( | 01-03-2013 |
20130156579 | AMBIENT AIR COOLING ARRANGEMENT HAVING A PRE-SWIRLER FOR GAS TURBINE ENGINE BLADE COOLING - A gas turbine engine including: an ambient-air cooling circuit ( | 06-20-2013 |
20140219818 | Turbine Component Cooling Channel Mesh with Intersection Chambers | 08-07-2014 |
20140286791 | Component Cooling Channel - A cooling channel ( | 09-25-2014 |
20150071785 | TURBINE BLADE AND NON-INTEGRAL PLATFORM WITH PIN ATTACHMENT - Platforms ( | 03-12-2015 |
20150078898 | Compound Cooling Flow Turbulator for Turbine Component - Multi-scale turbulation features, including first turbulators ( | 03-19-2015 |