Patent application number | Description | Published |
20080232971 | Coated turbine blade - The invention refers to a coated turbine blade for a gas turbine, having blade walls divided into sections with locally adapted material temperatures. The cooler material temperatures of the blade walls are at the points where the support ribs merge into the blade walls. The regions with higher material temperatures of the blade walls are at the positions where cavities are arranged inside the blade walls. This is achieved via a ceramic thermal barrier coating having different layer thicknesses that allow different material temperatures. The region of the surface of the blade wall which faces the working medium and lies opposite an internal rib has a thicker thermal barrier coating than a region of the surface of the blade wall which is cooled via a cooling medium that flows in the cavities. This results in homogenization of the material temperature in the connecting regions, which results in prolonged blade life. | 09-25-2008 |
20090035128 | COOLED TURBINE BLADE FOR A GAS TURBINE AND USE OF SUCH A TURBINE BLADE - An aspect of the invention is a turbine blade for a gas turbine, comprising a blade root, adjoining which one after the other are a platform region having a transversely running platform and then a blade profile curved in the longitudinal direction, comprising at least one cavity which is open on the root side and through which a coolant can flow and which extends through the blade root and the platform region into the blade profile. The cavity is surrounded by an inner wall, on the surface of which structural elements influencing the coolant are provided. In order to prolong the service life of such a turbine blade, the invention proposes that a section, lying at least in the blade profile and adjoining the platform region, of the surface of the inner wall be free of structural elements. Such a turbine blade can preferably be used in a stationary gas turbine | 02-05-2009 |
20090074572 | COOLED GAS TURBINE GUIDE BLADE FOR A GAS TURBINE, USE OF A GAS TURBINE GUIDE BLADE AND METHOD FOR OPERATING A GAS TURBINE - Described is a cooled gas turbine guide blade for a gas turbine, with a hollow blade profile which comprises an onflow edge onto which a working medium is capable of flowing, and with, for guiding a cooling medium, an onflow edge duct running inside the blade profile along the onflow edge. Furthermore, to the use of such a gas turbine guide blade and to a method for operating a gas turbine with an abovementioned gas turbine guide blade. In order to provide a gas turbine guide blade with an increased lifetime by means of the invention, it is proposed that, in the onflow edge duct, an electrical heating element be provided, which extends approximately completely over the entire length of the onflow edge duct and through which a heating current flows, before the operation of the gas turbine, for the preheating of the gas turbine guide blade. | 03-19-2009 |
20090185913 | Method of Producing a Turbine or Compressor Component, and Turbine or Compressor Component - Disclosed is a turbine or compressor component with an integrated cooling channel, in particular a turbine blade, and a method for producing the same. The aim of the invention is to ensure an improved estimation of the service life of the component and furthermore, if possible, also increased safety during operation and increased service life, even in the presence of constantly variable thermal and mechanical stress. To achieve this, the cooling channel of the component is subjected to internal pressure during a pressure impingement phase, said internal pressure being at a level sufficiently high that it causes the at least semiplastic deformation of the wall regions delimiting the cooling channel. | 07-23-2009 |
20090252612 | Blade and gas turbine - The invention relates to a turbomachine, in particular to a gas turbine and to a method for accelerating a temperature modification of a rotor shaft rotationally mounted in said turbomachine. The aim of said invention is to develop a device and a method for the turbomachine making it possible to reduce the size of a radial split of the turbomachine in order to obtain greater degree of efficiency. The inventive turbomachine comprises a rotor rotationally mounted in the case of the turbomachine, a feeding channel embodied in the rotor for introducing a fluid and an outlet channel embodied in the rotor for removing said fluid. An inlet orifice of the feeding channel is disposed further inside than the outlet orifice of the outlet channel, and means influencing a liquid flow is formed of an actuating device dependent on centrifugal force. Methods for cooling the rotor only by decelerating the gas turbine and for heating the turbomachine rotor by heating fluid flowing therethrough are also disclosed. | 10-08-2009 |
20090280291 | ELONGATE COMPONENT HAVING LONGITUDINAL GRAINS WITH DIFFERENT WIDTHS - A component, designed so that the longitudinal grain which experiences the greatest stress has a larger grain width than the other grains, is provided. This longitudinal grain is usually on the edge of the component. The component includes longitudinal grains that are directionally solidified in a rod-crystalline form along the longitudinal axis of the component. | 11-12-2009 |
20090324421 | Turbine Blade - A turbine blade is provided. The turbine blade includes a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure by at least one spacing element. For example the spacing element can be a solder globule in order to form a space through which a cooling medium can flow between the support structure and the shell. A method for the production of a turbine blade having a support structure and a shell which surrounds the support structure and which is connected to and at a distance from the support structure is also provided. The shell is soldered to the support structure in at least at one place of the support structure in order to connect the shell to and at a distance from the support structure. | 12-31-2009 |
20100068069 | Turbine Blade - A turbine blade, having a plurality of auxiliary cooling channels which branch off from a main cooling channel, formed within a blade body, is provided. The plurality of auxiliary cooling channels open into outlet openings in the leading edge region of the blade body. A heat shield element is attached to the blade body in the leading edge region at a predefined spacing, wherein the heat shield element has a number of outlet channels which are arranged behind one another in the longitudinal direction and extend from the main cooling channel to the outer wall face of the heat shield element. | 03-18-2010 |
20100129554 | METHOD FOR THE PRODUCTION OF COATED TURBINE MOVING BLADES AND MOVING-BLADE RING FOR A ROTOR OF AN AXIAL-THROUGHFLOW TURBINE - A method for producing a coated turbine blade, with which the frequency property thereof can be particularly easily adjusted to the required boundary conditions is provided. Recesses are introduced into a blade tip of the blade leaf of the turbine blade after coating of turbine blade. In one aspect a plurality of bores are made which are distributed along the blade leaf center line. | 05-27-2010 |
20110033305 | Turbine vane for a stationary gas turbine - A turbine vane for a stationary gas turbine is provided. The turbine vane includes a hollow vane blade, wherein a rib is provided inside the vane blade to allow a pressure side wall and a suction side wall to support one another. The rib has an opening penetrating the rib near a wall at a height of an external fillet between a side wall, and a platform surface for extending a life of the turbine vane. By the opening, material accumulations in a transition region are avoided or the accumulation is reduced, whereby increases in stiffness and higher temperature gradients associated therewith are avoided. | 02-10-2011 |
20110176930 | Turbine vane for a gas turbine and casting core for the production of such - A turbine vane or blade including an interior structure is provided. In addition, turbulence elements connected directly upstream of openings disposed at the rear edge of the blade of the turbine vane or blade are also provided. These are disposed in a sequence, each having a flow side against which a coolant flows and which is at least partially arched in a concave manner. Preferably, the turbulence elements are configured in a crescent-shaped manner. This makes it possible to enlarge the openings without resulting in an increased consumption of coolant. A casting core is also provided. The openings required in the casting core for the production of the webs of a turbine vane or blade may now be placed at further distances than before. | 07-21-2011 |
20110255956 | Gas turbine having cooling insert - A gas turbine including a plurality of rotor blades assembled into rotor blade rows and arranged on a turbine shaft and including a plurality of guide vanes assembled into guide van rows and mounted on a turbine housing by means of a guide van carrier is provided. The guide vane carrier includes a plurality of cooling air holes, and has a particularly high efficiency, while maintaining maximum operating reliability. Therefore, a cooling insert is introduced into a cooling air hole. | 10-20-2011 |
20120031579 | Method for producing a negative mold for casting a turbine blade and mold for producing a wax model of a gas turbine - A method for producing a negative mold for casting a turbine blade with a blade platform and at least one fastening element for fastening the turbine blade to a blade fixture is provided. The surface of the fastening element of a platform surface is located at a distance opposite of the blade platform. A wax model of the turbine blade to be produced is produced, a negative model of the turbine blade is created based on the wax model after the wax model has hardened and the wax model is melted out after completion of the negative mold. During hardening and/or during storage and/or during transport of the wax model at least one spacer is arranged between the platform surface of the blade platform and the opposite surface of the fastening element of the wax model. | 02-09-2012 |
20120039716 | Guide vane system for a turbomachine having segmented guide vane carriers - A turbine guide vane system, in particular for a gas turbine is provided. The turbine guide vane system includes a number of guide vane rows and a guide vane carrier, to enable particularly simple replacement of guide vanes, while maintaining a particularly high degree of efficiency, and thus designed for particularly short repair durations. For this purpose, the guide vane carrier has a number of segments, wherein a segment extends over the entire radial extension of the guide vane carrier and the connection of the remaining segments may be detached, and wherein the turbine guide vane carrier includes at least two sections along the axial extension thereof that are connected to one another and have a different number of segments. | 02-16-2012 |
20120039718 | CASTING APPARATUS FOR PRODUCING A TURBINE ROTOR BLADE OF A GAS TURBINE AND TURBINE ROTOR BLADE - A casting apparatus for producing a turbine rotor blade of a gas turbine, and to a turbine rotor blade produced therewith is provided. The casting apparatus includes a hollow ceramic shell mold, of which the pouring gate and cores arranged therein are oriented with respect to each other such that a hot casting material flowing into a cavity of the ceramic shell mold does not come in direct contact with the cores. Thus, so-called hot spots on cores are avoided, which until now have had negative effects on the solidification of the casting material. Especially in the region of the blade root of the turbine rotor blade to be produced improved solidification of the casting material may thus be obtained, reducing any disturbance in the structure of the solidified casting material. | 02-16-2012 |
20120070310 | AXIAL TURBOMACHINE ROTOR HAVING BLADE COOLING - An axial turbomachine rotor is provided. The rotor includes a rotor disk and a rotor blade ring, which includes a plurality of rotor blades, each of which include a blade root, with which the rotor blade is fixed radially outward on the rotor disk, wherein the blade root is engaged with the rotor disk at the outer edge of the rotor disk in a form-closed manner in such a way that during operation of the rotor, a gap is formed between the rotor blade and the rotor disk at a predetermined surface area of the rotor disk, in which area, a plurality of impingement cooling openings is arranged, through which a cooling medium may flow from the interior of the rotor disk into the gap whereby the rotor blade is cooled using the cooling medium by means of impingement cooling. | 03-22-2012 |
20120093654 | Rotor blade for an axial flow turbomachine and mounting for such a rotor blade - A rotor blade for an axial flow turbomachine, preferably a turbine, and to a mounting for such a rotor blade is provided. In the rotor blade, the two opposing lateral walls of the blade base are continuously curved along their extension between platform and bottom side of the blade base in order to reduce the mechanical load in the blade base and that of the walls supporting the blade base of a rotor. | 04-19-2012 |
20120100008 | ANNULAR FLOW CHANNEL SECTION FOR A TURBOMACHINE - An annular flow channel section for a turbomachine is provided. The annular flow channel includes a guide vane ring having a number of guide vanes which are arranged next to each other in the circumferential direction, each guide vane including a vane base, a platform and an airfoil that projects into the flow channel in a radiating pattern. The flow channel is delimited on the platform side by shielding elements, each of which being disposed between two immediately adjacent airfoils, wherein the shielding elements are arranged on the platforms for creating a particularly space-saving flow channel section while creating a gap, and impingement-cooling openings are provided in the platform. | 04-26-2012 |
20120103554 | PROCESS FOR OPTIMIZING A CORE DIE - A process for optimizing a core die is provided. By iteratively modifying the ceramic core without changing the core die, it is possible to ascertain an optimum core without modifying the core die every time. In a last step, an optimum core die is produced using the optimum ceramic core. | 05-03-2012 |
20120118524 | CORE DIE WITH VARIABLE PINS AND PROCESS FOR PRODUCING A CORE - A core die is provided. The core die includes a first half and a second half where a cavity is formed between the two. Pins are arranged on the halves and the pins are replaceable. By virtue of the modular inner structure of a core die, the core die may be matched to the desired changes of the core, by small changes, more quickly and more easily than would be the case if the core die had only one part or if the pins were a fixed component of the core die halves. | 05-17-2012 |
20120207615 | Cooling of a Gas Turbine Component Designed as a Rotor Disk or Turbine Blade - A gas turbine component for example a turbine blade or a rotor disk is provided. In order to extend the service life of the corresponding component by reducing the thermally or mechanically induced stress concentration in the direct surroundings of a duct opening onto a surface, at least one groove-like recess is provided near the effective zone of the opening. | 08-16-2012 |
20120251741 | Method for adjusting the coolant consumption within actively cooled components, and component - A method for adjusting the coolant consumption within actively cooled components is produced. The components include an interior with at least one duct with different regions which have different cross sections of flow. A greater increase in the wall thickness is produced in the region having the smaller cross section of flow by a first diffusion process and a lesser increase in the wall thickness is produced in the region having the larger cross section of flow by a second diffusion process which is different from the first. By using different diffusion coatings in a component, it is possible to adjust the flow of coolant through a component in a controlled way. | 10-04-2012 |
20120273153 | Casting mold having a stabilized inner casting core, casting method and casting part - A casting mold for a metal melt is provided. By coating a core of a casting mold, the core may be mechanically stabilized and an inner coating of the component to be cast may be obtained, wherein the coating preferably serves as an anti-corrosion layer. A method for producing a cast part using the casting mold is also provided. | 11-01-2012 |
20120285652 | Liner for a Die Body - A liner for a die body is presented. The liner includes a flexible base material characterized in that reinforcements with lower stretchability compared to the base material are bonded along the extent of the liner. A tool which includes the liner is also provided. The reinforcements may include glass fibers or carbon fibers. | 11-15-2012 |
20120321825 | Method for assessing the coolant consumption within actively cooled components - A process for setting the average flow rate within a hollow component is provided. The process includes setting a relatively small wall thickness in a first region with a relatively large flow cross section using a first diffusion coating process and setting a relatively large wall thickness by a second different diffusion process in a second region with a relatively small flow cross section. The use of different diffusion coatings in a component allows the flow of coolant through a component to be set in a controlled manner. | 12-20-2012 |
20130156599 | TURBINE BLADE FOR A GAS TURBINE - A turbine blade for a gas turbine is provided. The quantity of coolant flowing off the rear edge thereof is set relatively simply and exactly directly upon casting the turbine blade, without reworking the cast turbine blade with respect to the setting of coolant consumption being necessary. Raised areas are situated on the inner surfaces of the intake side wall or pressure side wall, between which a throttle element is present, by means of which the quantity of coolant flowing out is set. This arrangement allows a core tool to be produced simply, by means of which the casting cores required for casting the turbine blade are produced having the desired precision in great quantities. | 06-20-2013 |
20130233451 | SHOT PEENING IN COMBINATION WITH AN HEAT TREATMENT AND A COMPONENT - A method to produce a metallic component is described. The method provides that an additional shot peening is performed on at least portion of component in order to obtain a fine grain structure during a following heat treatment in order to yield higher HCF because a finer grain structure is reached. | 09-12-2013 |
20130330203 | METHOD FOR PRODUCING A PROTECTIVE LAYER FOR A ROTOR BLADE - A method for producing a protective layer for a rotor blade of a turbomachine is proposed. The rotor blade has a wear cap wall that in relation to the axis of the turbomachine protrudes radially towards the exterior of the turbomachine beyond a body of the rotor blade. The method enables the entire rotor blade to have a comparatively long service life and at the same time allows the wear cap wall to be thermally insulated in an especially simple manner. For the purpose, a profile producing a positive fit effective in the radial direction is inserted in a radially located region of the wear cap wall, a slip containing metal powder and/or a ceramic slip is applied to the region and the slip in sintered. | 12-12-2013 |
20140099209 | GAS TURBINE COMPONENT, METHOD FOR ITS PRODUCTION AND CASTING MOLD FOR USE OF THIS METHOD - A method is provided for casting a gas turbine component having at least a first section and a second section. As per the method, a liquid metal is cast into a casting mold and solidification of the metal is induced by means of controlled cooling. The cooling of the liquid metal in the first section is controlled in such a way that the metal solidifies in a directionally solidified crystal structure or a single-crystal structure. In the second section the cooling is carried out in such a way that it solidifies in a multidirectional crystal structure. | 04-10-2014 |
20140248157 | BLADE OR VANE OF DIFFERING ROUGHNESS AND PRODUCTION PROCESS - A blade or vane of different roughness and a process for producing such a blade or vane are presented. The performance of the blade or vane of a compressor or of a turbine can be improved because of the different configuration of the roughness of the surfaces on the suction side and the pressure side of the blade or vane. | 09-04-2014 |
20140255652 | SURFACE HAVING SPECIALLY FORMED RECESSES AND COMPONENT - A surface having specially formed recesses and component is provided. The component has a layer with a surface, having elongate recesses, which have a longitudinal direction, wherein the recesses are arranged at an angle which differs considerably from 0°, in particular 90°+/−20°, with respect to a direction of overflow over the surface, and are at least partially widened transversely to the longitudinal direction thereof in the region of the surface with respect to the base of the recess, in which the recess is widened proceeding from the base only above a certain height within the recess, and in particular the recess has a constant width before it, in which the recess does not extend through the entire thickness of the layer. | 09-11-2014 |
20140295086 | PROCESS FOR PRODUCING A LAYER SYSTEM - A process for producing a layer system is provided wherein the layer system has at least a substrate, a ceramic layer, which is applied to a surface structured in a targeted manner, in which process the intermediate layer, in particular the metallic layer, is applied in such a way that the recesses form during the coating. By introducing recesses into a surface, the stresses in the ceramic layer on the metallic substrate are reduced in such a manner that a longer lifespan for the ceramic layer is achieved. | 10-02-2014 |
20140377058 | TURBINE GUIDE VANE WITH A THROTTLE ELEMENT - A turbine guide vane having an aerodynamically bent vane airfoil with a channel system equipped with a throttle element is provided herein. The channel system includes channel sections for the guidance of coolant. In order to provide an alternative turbine guide vane by means of which both a partial coolant flow flowing in the interior and a partial coolant flow guided out of the turbine guide vane are adjustable; therefore, in an embodiment, the throttle element is designed for the removal of coolant. | 12-25-2014 |
20150017014 | CORE FOR CASTING A HOLLOW COMPONENT | 01-15-2015 |
20150064018 | TURBINE BLADE AND ASSOCIATED METHOD FOR PRODUCING A TURBINE BLADE - A turbine blade is provided, having a fastening section, a platform, and a blade, which follow one another along a longitudinal axis of the turbine blade, wherein the platform, in radial relation to the longitudinal axis, has an inner platform part and an outer platform part, wherein the outer platform part is designed as a closed platform frame that encloses the outer edge of the inner platform part. An associated method for producing a turbine blade is also provided. | 03-05-2015 |
20150071783 | TURBINE BLADE - A turbine blade is provided having a blade and a modular platform which follow one another along a longitudinal axis of the turbine blade. In order to provide a modular turbine blade that has an especially plain and simple design and that ensures an especially reliable, long-lasting, durable connection of the individual components among each other, the blade has an extension and the platform has an outer platform part and an at least two-part inner platform part which is radial in relation to the longitudinal axis and which lie laterally against the extension of the blade, and the outer platform part is designed as an endless platform frame that surrounds the outer edge of the inner platform part. | 03-12-2015 |
20150086361 | AXIAL ROTOR PORTION AND TURBINE ROTOR BLADE FOR A GAS TURBINE - A turbine rotor blade is provided with a blade root, platform adjoining it, and turbine blade on that side of the platform which faces away from the blade root, with at least one opening for feeding coolant into the turbine rotor blade interior on an underside of the blade root, which opening merges into a coolant duct. An axial rotor section for a rotor is provided, having an outer circumferential surface adjoining two end-side first side surfaces with rotor blade holding grooves distributed over the circumference and extending along an axial direction, wherein a turbine rotor blade is arranged in every holding groove, wherein a multiplicity of sealing elements are at the side of a side surface of the rotor section, and lie opposite the end sides of blade roots to form a gap. Multiple outlet holes for impingement cooling of the sealing elements are provided in the end surface. | 03-26-2015 |