| Patent Number |
Title Of Patent |
Date Issued |
| 7574864 |
Diffuser for a gas turbine, and gas turbine for power generation |
August 18, 2009 |
| The invention relates to a gas turbine, for energy generation, with a compressor, arranged coaxially to a rotor, mounted such as to rotate, for the compression of an inlet gaseous fluid, at least partly serving for combustion of a fuel in a subsequent annular combustion chamber, with |
| 7430802 |
Labyrinth seal in a stationary gas turbine |
October 7, 2008 |
| The invention relates to a segmented inner ring for holding guide blades. According to the invention, a lateral wall opposing the front side of the inner ring and pertaining to a shaft shoulder formed on the rotor shaft extends radially, and respectively one half of a labyrinth seal is f |
| 7338244 |
Attachment device for turbine combustor liner |
March 4, 2008 |
| An attachment device for coupling one or more restrained members to a frame. In at least one embodiment, the attachment device may be configured to attach one or more turbine combustor liners to a carrier. The attachment device may include a body rotatable about an axis of rotation a |
| 7334412 |
Cooling air and injected liquid system for gas turbine blades |
February 26, 2008 |
| The invention relates to a turbine 1, in particular a gas turbine, which along a swivel-mounted rotationally symmetrical rotor 2 has a compressor 3, a combustion chamber 5 and a turbine section 7 formed of a plurality of turbine stages 15, in which each turbine stage 15 contains mutually |
| 7322196 |
Combustion chamber for combusting a combustible fluid mixture |
January 29, 2008 |
| A combustion chamber (1) for combusting a combustible fluid mixture having a burner (2) disposed on the combustion chamber (1) and a method for cooling a combustion chamber (1). A fixing device is provided for liner elements (5) of a combustion chamber (1) by which simplified assembly |
| 7290983 |
Turbine, fixing device for blades and working method for dismantling the blades of a turbine |
November 6, 2007 |
| A turbine and a method for dismantling a blade of a turbine. A turbine includes a rotor that extends in an axial direction and an accessible combustion chamber, which communicates with an annular hot-gas conduit, in which a plurality of blades that form a blade row is arranged. Each |
| 7201564 |
Turbine vane system |
April 10, 2007 |
| A turbine vane, especially a turbine vane of the last stages, respectively includes a lower area which is radially and externally arranged, an upper area which is radially and internally arranged, and a radial cooling air channel extending between the upper area and the lower area. Cooli |
| 7131813 |
Turbine engine and a method for cooling a turbine engine |
November 7, 2006 |
| A turbine engine with a turbine shaft which has a number of disks arranged adjacent to one another, to each of which a number of blades are fastened in a star arrangement, wherein these blades can be cooled with at least one coolant which flows through coolant channels inside the blades |
| 7089748 |
Combustion chamber, in particular of a gas turbine |
August 15, 2006 |
| The invention relates to a combustion chamber, in particular of a gas turbine, comprising an external wall structure that surrounds an internal area and an internal wall, which is formed by the surface of a housing that is located in the internal area. Said combustion chamber can be |
| 7059835 |
Turbine, in particular a gas turbine, and a blade |
June 13, 2006 |
| A turbine (1) with a rotationally symmetrical rotor (4) on rotary bearings which has on its outer perimeter moving blade retaining grooves running transverse to the outer perimeter and set at the same angular distance from one another, having a moving blade (13) that has a vane (24) and |
| 7021061 |
Heat shield arrangement for a hot-gas conducting component, in particular for structural pieces |
April 4, 2006 |
| The invention relates to a heat shield arrangement for a hot gas conducting structure, in particular a metal component of a gas turbine unit or combustion chamber, with the heat shield elements anchored adjacently on a support structure to cover a surface. Said heat shield elements e |
| 6979173 |
Turbine blade or vane |
December 27, 2005 |
| A turbine blade or vane includes an inner contour profile which is matched to the contour profile of the outer transition region, so that a substantially uniform blade or vane wall thickness is achieved. |
| 6971847 |
Fastening system |
December 6, 2005 |
| Components must often be released again from their holder for maintenance. Since the fastenings are often very complicated, it takes a considerable amount of time to release them. A fastening system is one where components can be fastened in a rotationally locked manner to a holder, and |
| 6968672 |
Collar for a combustion chamber of a gas turbine engine |
November 29, 2005 |
| This invention relates to a combustion chamber arrangement for a gas turbine, with a number of individual combustion chambers which open into an annular gap, leading to a turbine chamber, whereby burners are arranged before the individual combustion chambers, connected to the individual |
| 6957538 |
Combustion chamber for a gas turbine |
October 25, 2005 |
| The invention relates to a combustion chamber for a gas turbine having at least one closed-circuit-cooled burner insert which can be disposed in an inlet opening of the combustion chamber for the purpose of feeding and/or igniting a combustible gas/air mixture, and having an outlet openi |
| 6941758 |
Internally coolable screw |
September 13, 2005 |
| A screw includes a head and a shank, and includes a coolant passage which has an inflow opening and an outflow opening. The cooling pasage does not pass axially through the entire head and shank. By avoiding a coolant flow which passes axially through the entire screw, especially effecti |
| 6938424 |
Annular combustion chambers for a gas turbine and gas turbine |
September 6, 2005 |
| The invention relates to an annular combustion chamber for a gas turbine wherein the annular combustion chamber extends in an axial direction, encloses a combustor and has on its inside facing the combustor a bearing structure on which a lining element secured to this lines the annular |
| 6925808 |
Combustion chamber with a closed cooling system for a turbine |
August 9, 2005 |
| In order to develop a combustion chamber with a closed cooling system for a turbine with an inner wall and an outer wall (1) bounding the combustion area, wherein there is an intermediate space between the inner wall and the outer wall (1) through which cooling fluid can flow, and which |
| 6923620 |
Turbine blade/vane and casting system for manufacturing a turbine blade/vane |
August 2, 2005 |
| A turbine blade/vane includes a profiled blade/vane aerofoil, which extends along a blade/vane center line. A platform is formed on an end region of the blade/vane aerofoil, extending transverse to the blade/vane center line. This is to be designed for a particularly high capability for |
| 6905301 |
Turbine blade/vane |
June 14, 2005 |
| A turbine blade/vane, having a blade/vane aerofoil which extends along a blade/vane axis and through which cooling medium flows, mainly in the longitudinal direction of the turbine blade/vane, is configured comparatively simply for reliable and effective closed cooling. In particular |
| 6874988 |
Gas turbine blade |
April 5, 2005 |
| A gas turbine blade includes a combined convective cooling effected by a meandering cooling channel and an impact cooling channel and an impact cooling effected via an impact cooling insert. The impact cooling insert is arranged inside a first partial section of the meandering cooling |
| 6837053 |
Gas turbine combustion chamber and air guidance method therefore |
January 4, 2005 |
| In order to provide a method of air guidance and a design for a gas turbine combustion chamber which permits improved cooling and reduced pressure losses and which avoids the overcooling phenomena by specific reaction to hot spots, a gas turbine combustion chamber includes a casing and a |
| 6835046 |
Configuration of a coolable turbine blade |
December 28, 2004 |
| A turbine blade through which cooling liquid flows, comprises several flow channels that are adjacently arranged in the flowing-off direction of the working fluid. The flow channels extend between inflow openings, which are located on a radially inner blade foot, and out-flow openings, w |
| 6805535 |
Device and method for producing a blade for a turbine and blade produced according to this metho |
October 19, 2004 |
| A device and a method are for producing a blade including two outer walls and at least one cavity between the outer walls, for a turbine. An outer mould and several cores are used in forming the outer walls and the at least one cavity of the blade. At least one of the cavities is divided |
| 6786694 |
Gas turbine and method of operating a gas turbine |
September 7, 2004 |
| In a gas turbine, having a number of turbine blades/vanes respectively combined to form blade/vane rows, each of the turbine blades/vanes including an integrated cooling air duct, the cooling air requirement is to be kept particularly low in conjunction with reliable cooling of the t |
| 6786048 |
Thermal shield for a component carrying hot gases, especially for structural components of gas t |
September 7, 2004 |
| A hot gas chamber, for example a combustion chamber of a gas turbine installation, is lined with thermal shield elements. A closed-circuit cooling system is provided by configuring the thermal shield element as a hollow body into which cool air flows via a cool air supply channel. Once |
| 6769875 |
Cooling system for a turbine blade |
August 3, 2004 |
| The invention relates to a blade (13; 14) for a turbine (10), comprising at least one channel (22) which is delimited by walls (19, 20, 21). An insert (25) which can be subjected to the action of a liquid coolant is inserted into at least one channel (22). According to the invention, at |
| 6755986 |
Moving turbine blade |
June 29, 2004 |
| A moving turbine blade includes a blade profile with inner cooling which extends out from a blade platform adjoined by a blade foot, the blade foot engaging with a turbine disk and having a radial cross-section with an area whose width increases towards the blade platform. A moving turbi |
| 6739381 |
Method of producing a turbine blade |
May 25, 2004 |
| In a method of producing a turbine blade in hollow section, an especially low defect or scrap rate is to be ensured. To this end, a first core element is connected via a number of approximately cylindrical spacers to a further core element and/or to a casting mold, the cavities left in t |
| 6726452 |
Turbine blade arrangement |
April 27, 2004 |
| A turbine blade arrangement includes rotating blades respectively provided with a leg which can be respectively inserted into a groove on the outer circumference of a turbine disk in a radial, positive fit and which are respectively provided with a profiled section which has a lateral pl |
| 6725666 |
Combustion-chamber arrangement |
April 27, 2004 |
| The invention relates to a combustion-chamber arrangement for gas turbines, having an annular combustion chamber connected to at least one burner and leading into a turbine space, an annular-combustion-chamber wall which defines the annular combustion chamber being of double-shell constr |
| 6719529 |
Gas turbine blade and method for producing a gas turbine blade |
April 13, 2004 |
| A gas turbine blade includes an inlet edge region of a platform. Eroded into it is a slot which runs parallel to the flow-on edge and into which cooling air is introduced in an impact-cooled manner from the platform under side and is discharged in a film-cooling manner from the platform |
| 6712120 |
Device and method for casting a workpiece and workpiece |
March 30, 2004 |
| A device for casting a workpiece, especially a turbine blade with inner cooling, includes a casting cavity in which casting cores which produce channels that pass through the workpiece are provided. There are no poorly cooled areas present in the workpiece. To this end, the casting cores |
| 6709237 |
Turbine blade or vane and process for producing a turbine blade or vane |
March 23, 2004 |
| The present invention relates to a turbine blade or vane (13; 14), in particular for a gas turbine (10), which has at least one chamber (18; 29; 20; 21) which can be acted on by a cooling medium and, at a rear edge (26), has a gap (25), which is delimited by two walls (28, 29), for the |
| 6705832 |
Turbine |
March 16, 2004 |
| A turbine includes a sealing element with a receiving area for sealing the guide blade vanes which are adjacent to each other in the peripheral direction of the turbine. The foot plates of the guide blade vanes extend into the receiving area. The edge area of the foot plates does not hav |
| 6702547 |
Gas turbine |
March 9, 2004 |
| In a gas turbine (1) having a number of rotor blades (12) in each case combined into rows of rotor blades and arranged on a turbine shaft (8), and having a number of stator blades (14) in each case combined into rows of stator blades and connected to a turbine casing, a particularly high |
| 6691503 |
Gas turbine having first and second combustion chambers and cooling system |
February 17, 2004 |
| A gas turbine (5) according to the invention, which comprises a main combustion chamber (10), a cooling system for air cooling of at least the guide vanes (26, 29) and guide rings (28, 38) of various stages (25, 27) of the gas turbine (5), and a main gas passage, also includes a further |
| 6684620 |
Combustion chamber arrangement for gas turbines |
February 3, 2004 |
| A combustion chamber arrangement for gas turbines includes a multiplicity of individual combustion chambers which open out in a common annular combustion chamber and are arranged in the shape of a circle. The arrangement is such that it can be cooled highly efficiently using convecti |
| 6682307 |
Sealing system for a rotor of a turbo engine |
January 27, 2004 |
| A turbomachine, in particular a gas turbine, includes a rotor which extends along an axis of rotation. The rotor includes a circumferential face, which is defined by the outer radial boundary surface of the rotor, and a receiving structure. Additionally, it includes a first rotor blade a |
| 6676372 |
Gas turbine with axially mutually displaceable guide parts |
January 13, 2004 |
| A gas turbine with axially mutually displaceable guide parts that compensates for differing amounts of thermal expansion, comprising guide parts which can be displaced with respect to one another in the axial direction and enclose a funnel-like gas duct from outside. In order to opti |
| 6676370 |
Shaped part for forming a guide ring |
January 13, 2004 |
| A shaped part (30) for forming a guide ring (21) for a gas turbine (1) is, on the one hand, to be produced with particularly little outlay and, on the other hand, is to be designed so that it can be cooled particularly effectively with steam as the coolant. For this purpose, according to |
| 6672074 |
Gas turbine |
January 6, 2004 |
| In a turbine (1) having a moving-blade row which has a moving blade (12) on a turbine shaft (8), and having a guide blade (14) which has a guide-blade row, an especially high efficiency is to be achieved with simple means with the turbine blades (12, 14) being cooled in a reliable manner |
| 6672070 |
Gas turbine with a compressor for air |
January 6, 2004 |
| In gas turbines, compressed air is supplied via an air duct to combustion chambers and is heated there. Pressure losses in the air duct should be minimized in order to ensure good overall efficiency. This is achieved by the compressed air flowing with approximately constant velocity in t |
| 6659714 |
Baffle cooling device |
December 9, 2003 |
| A device for a component to be cooled includes a baffle cooling plate with at least one leadthrough for the cooling agent, arranged in front of the component. The baffle cooling plate can be impinged upon with a cooling agent. A deviation channel for the cooling agent is provided next to |
| 6652228 |
Gas turbine blade and gas turbine |
November 25, 2003 |
| Disclosed is a gas turbine blade, in which a ceramic covering, which is mechanically fastened to a metal platform, is arranged in a manner that the metal platform is protected against a hot gas in a hot gas duct of a gas turbine. |
| 6641362 |
Component that can be subjected to hot gas, especially in a turbine blade |
November 4, 2003 |
| A component can be subjected to hot gas. At least one duct is provided which can be subjected to a cooling fluid. The duct is bounded by two first walls opposite to one another. The walls include turbulators with the same direction of inclination. In order to avoid constrictions, the |
| 6632070 |
Guide blade and guide blade ring for a turbomachine, and also component for bounding a flow duct |
October 14, 2003 |
| The invention relates to a guide vane (17) for a turbomachine (1), in particular a gas turbine guide vane, in which the platform (48) has a separating region (50), which is embodied as a separate component. This has, in particular, advantages with respect to the simplification of cast |
| 6631561 |
Turbine blade and method for producing a turbine blade |
October 14, 2003 |
| A method is for producing a turbine blade, in particular, a gas turbine blade, comprising a head, a foot, and a blade section, in addition to an internal canalization system, including individual channels through which coolant gas can pass along a flow path within the turbine blade. The |
| 6619912 |
Turbine blade or vane |
September 16, 2003 |
| The present invention relates to a process for producing a turbine blade or vane (13; 14), which has at least one chamber (22; 23, 24, 25) and an inlet (30; 31) for applying a cooling medium to the chamber (22; 23, 24, 25), at least one inlet (30) running at an angle with respect to a |
| 6612806 |
Turbo-engine with an array of wall elements that can be cooled and method for cooling an array o |
September 2, 2003 |
| A turbomachine includes a coolable arrangement, having a first wail element and having a second wall element. Coolant is used to cool the arrangement in a turbomachine. After the impingement cooling of the first wall element, the coolant is further used for cooling the second wall elemen |
