Patent application number | Description | Published |
20100122538 | METHODS, APPARATUS AND SYSTEMS CONCERNING THE CIRCUMFERENTIAL CLOCKING OF TURBINE AIRFOILS IN RELATION TO COMBUSTOR CANS AND THE FLOW OF COOLING AIR THROUGH THE TURBINE HOT GAS FLOWPATH - A method of operating a turbine engine, wherein the turbine engine includes a compressor, a combustor, a turbine, a plurality of successive axially stacked stages that include a row of circumferentially spaced stator blades and circumferentially spaced rotor blades, and a plurality of circumferentially spaced injection ports disposed upstream of a first row of stator blades in the turbine; the injection ports comprising a port through which cooling air is injected into the hot-gas path of the turbine, the method comprising: configuring the stator blades in the first row of stator blades such that the circumferential position of a leading edge of one of the stator blades is located within +/−15% pitch of the first row of stator blades of the circumferential location of the injection port midpoint of at least a plurality of the injection ports. | 05-20-2010 |
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 |
20100166561 | TURBINE BLADE ROOT CONFIGURATIONS - A rotor blade for use in a turbine engine, the rotor blade comprising a root and, extending in a radial direction from the root, an airfoil, wherein the root includes at least one root aligned surface that is tilted. Tilted may comprises a non-radial orientation. The root aligned surfaces may comprise the surfaces along the root that are configured to align with and be relatively closely spaced from or in contact with the root aligned surfaces of the root of a neighboring rotor blade. The rotor blade may comprise at least two root aligned surfaces, one of which resides on a pressure side of the rotor blade and the other of which resides on a suction side of the rotor blade. All of the root aligned surfaces may be tilted. | 07-01-2010 |
20100166562 | TURBINE BLADE ROOT CONFIGURATIONS - A rotor blade for a turbine engine comprising a root and, extending in a radial direction from the root, an airfoil, wherein: the root comprises a shank and a dovetail; the shank extends from the dovetail and comprises a platform at an radial outward surface; the dovetail includes one or more tangs; the platform comprises an axially and circumferentially oriented surface that defines, at least in part, the inner most radial boundary of the flow path through the turbine; the dovetail is linear; and the platform is curved. | 07-01-2010 |
20110052387 | NON-AXISYMMETRIC AIRFOIL PLATFORM SHAPING - Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and/or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and/or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and/or trailing edges of nozzle assemblies of a turbine. | 03-03-2011 |
Patent application number | Description | Published |
20090053068 | STRUCTURES FOR DAMPING OF TURBINE COMPONENTS - Disclosed is a coating for gas turbine components including at least one material having vibration-damping properties. Further disclosed is an airfoil of a gas turbine having damped vibrational characteristics including an airfoil substrate and a coating applied to the airfoil substrate including at least one material having vibration-damping properties. A method of damping vibration of a gas turbine component includes applying a coating including at least one material having damping properties to the turbine component. | 02-26-2009 |
20100104446 | FABRICATED HYBRID TURBINE BLADE - A blade for a turbine includes: a support structure of high strength material as a central portion of the blade, the support structure including a root and a body extending to a tip, the body providing a leading edge, a trailing edge and mounting section; and a honeycomb skin attached to the mounting section for providing a lightweight airfoil portion of the blade. A method and a turbine are included. | 04-29-2010 |
20100254805 | GAS TURBINE INNER FLOWPATH COVERPIECE - A gas turbine inner flow path cover piece for a gas turbine a first turbine wheel and a second turbine wheel is provided is provided. The gas turbine inner flow path cover piece can include a main body having an first surface and a second surface, side pieces disposed on the first surface of the main body and mating pairs disposed on the second surface of the main body. | 10-07-2010 |
20110027090 | LOCKING SPACER ASSEMBLY FOR A CIRCUMFERENTIAL DOVETAIL ROTOR BLADE ATTACHMENT SYSTEM - A dual-component locking spacer assembly for insertion in a circumferential dovetail slot includes a stationary member having a platform configured to fit into a space between the adjacent rotor blade platforms. A first leg extends transversely from an underside of the platform. A longitudinally extending groove is defined in the platform. A slide member is movably engaged with the stationary member along the groove, and includes an upper plate and a second leg connected to the upper plate. The slide member is movable along the groove between a first unlocked position wherein the first and second legs are spaced apart a first distance so as to be insertable into the dovetail slot, and a second locked position wherein the first and second legs are spaced apart an extended second distance so as to engage against opposite walls of the dovetail slot and lock the stationary member in position in the dovetail slot. | 02-03-2011 |
20120034102 | BUCKET ASSEMBLY COOLING APPARATUS AND METHOD FOR FORMING THE BUCKET ASSEMBLY - A bucket assembly and a method for forming the bucket assembly are disclosed. The bucket assembly includes a platform, an airfoil, and a lower body portion. The platform defines a platform cooling circuit configured to flow cooling medium therethrough. The airfoil extends radially outward from the platform. The lower body portion extends radially inward from the platform. The lower body portion defines a root and a cooling passage extending from the root. The cooling passage is configured to flow cooling medium therethrough. The platform and lower body portion further include a ligament between the cooling passage and the platform cooling circuit. The ligament defines a bore hole extending through the ligament between the cooling passage and the platform cooling circuit. | 02-09-2012 |
20120063916 | TURBINE BLADE PLATFORM COOLING SYSTEMS - The present application provides a turbine blade cooling system. The turbine blade cooling system may include a first turbine blade with a first turbine blade platform having a cooling cavity in communication with a pressure side passage and a second turbine blade with a second turbine blade platform having a platform cooling cavity with a suction side passage. The pressure side passage of the first turbine blade platform is in communication with the suction side passage of the second turbine blade platform. | 03-15-2012 |
20120171046 | APPARATUS AND METHODS FOR COOLING PLATFORM REGIONS OF TURBINE ROTOR BLADES - A configuration of cooling channels through the interior of a turbine rotor blade having a platform, wherein the rotor blade includes an airfoil cooling channel that includes a cooling channel formed within the airfoil and an outboard airfoil supply channel. The configuration of cooling channels may include: a platform cooling channel that comprises a cooling channel that traverses at least a portion of the platform, the platform cooling channel having an upstream end and a downstream end; an outboard platform supply channel, which comprises a cooling channel that stretches from a second coolant inlet formed in the root to the upstream end of the platform cooling channel; and an inboard platform return channel, which comprises a cooling channel that stretches from the downstream end of the platform cooling channel to a termination point formed in the root. | 07-05-2012 |
20130039758 | TURBINE AIRFOIL AND METHOD OF CONTROLLING A TEMPERATURE OF A TURBINE AIRFOIL - According to one aspect of the invention, a turbine airfoil includes a platform and a blade extending from the platform. The airfoil also includes a slot formed in a slashface of the platform, the slot being configured to receive a pressurized fluid via passages and configured to direct the pressurized fluid to a selected region of the turbine airfoil to improve airfoil life. | 02-14-2013 |
20130078110 | OFFSET COUNTERBORE FOR AIRFOIL COOLING HOLE - The present application thus provides an airfoil for use in a turbine. The airfoil may include a wall, an internal cooling plenum, and a cooling hole extending through the wall to the cooling plenum. The cooling hole may include an offset counterbore therein. | 03-28-2013 |
20130089430 | TURBOMACHINE COMPONENT HAVING A FLOW CONTOUR FEATURE - A turbomachine component includes a main body having a gas path surface configured to be exposed to gases passing along a turbomachine gas path, a non gas path surface configured to be arranged in a turbomachine wheelspace outside the turbomachine gas path, and a non-axisymetric flow contour feature extending from the gas path surface to the non gas path surface. | 04-11-2013 |
20130108424 | TURBINE OF A TURBOMACHINE | 05-02-2013 |
20130108444 | TURBOMACHINE BLADE INCLUDING A SQUEELER POCKET | 05-02-2013 |
20130136610 | TURBINE BUCKET AIRFOIL PROFILE - 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. | 05-30-2013 |
20130230394 | Turbine Bucket with Pressure Side Cooling - The present application provides a turbine bucket for use with a gas turbine engine. The turbine bucket may include a platform, an airfoil extending from the platform, and a number of cooling circuits extending through the platform and the airfoil. One of the cooling circuits may be a serpentine cooling channel positioned within the platform. | 09-05-2013 |
20130230407 | Turbine Bucket with a Core Cavity Having a Contoured Turn - The present application thus provides a turbine bucket. The turbine bucket may include a platform, an airfoil extending from the platform at an intersection thereof, and a core cavity extending within the platform and the airfoil. The core cavity may include a contoured turn about the intersection so as to reduce thermal stress therein. | 09-05-2013 |
20130230408 | Turbine Bucket with Contoured Internal Rib - The present application thus provides a turbine bucket. The turbine bucket may include a platform and an airfoil extending from the platform. The airfoil may include an internal rib with a number of through holes positioned along a number of hole spaces and a number of in-between spaces. The in-between spaces may include a first depth, the hole spaces may include a second depth, and wherein the first depth is less than the second depth. | 09-05-2013 |
20140069110 | TURBINE BUCKET INTERNAL CORE PROFILE - Turbine bucket nominal internal core profiles and core insert external profiles are provided. In one embodiment, a turbine bucket includes an airfoil, platform, shank and dovetail. The bucket has a nominal internal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by a height of the bucket in inches, and wherein X and Y are non-dimensional values which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the bucket, the profile sections at the Z distances being joined smoothly with one another to form said bucket internal core profile. | 03-13-2014 |
20140096538 | PLATFORM COOLING OF A TURBINE BLADE ASSEMBLY - A turbine blade generally includes a platform having a pressure side, a suction side, a leading edge, a trailing edge, a pressure side slash face and a suction side slash face. A platform cooling circuit extends within the platform. The platform cooling circuit may extend from the suction side of the platform to the pressure side of the platform. The platform cooling circuit generally defines a fluid flow path that directs a cooling medium from the platform suction side to the platform pressure side. | 04-10-2014 |
20140255207 | TURBINE ROTOR BLADES HAVING MID-SPAN SHROUDS - A rotor blade for use in a turbine of a combustion turbine engine is described. The rotor blade may include an airfoil that extends from a connection with a root. The rotor blade may further include a mid-span shroud configured to engage a corresponding mid-span shroud on at least one neighboring rotor blades during operation. Outboard of the mid-span shroud, the airfoil may include an outboard region that is substantially hollow, and inboard of the mid-span shroud, the airfoil may include an inboard region that is substantially solid. | 09-11-2014 |
20140271225 | INTERIOR COOLING CIRCUITS IN TURBINE BLADES - A rotor blade comprising an airfoil portion and a root portion, and an internal cooling circuit having flow passages in the root portion and the airfoil portion, wherein the internal cooling circuit includes: a first flow passage; and a non-integral plug. The plug may include a plug channel configured to correspond to a desired level of coolant flow through the first cooling passage. The plug may be connected to the rotor blade in a fixed blocking position relative to the first flow passage. | 09-18-2014 |
20150037165 | TURBINE BLADE WITH SECTIONED PINS - A turbine blade is provided and includes pressure and suction surfaces connected to define an interior through which coolant is passable and first and second pedestal arrays, each of the first and second pedestal arrays including pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from pedestals of the second pedestal array by gaps respectively defined therebetween. | 02-05-2015 |