Patent application number | Description | Published |
20090092497 | Securing element for fastening moving blades - A securing element for securing the position of moving blades in slots, running at least mainly in the axial direction, of a rotor parent body of a turbomachine rotor is described, comprising a plate-shaped parent body, wherein the parent body has an approximately central recess which is formed between two end sections of the parent body and defines a center section, running between the two end sections, of the parent body, wherein the two end sections have bearing surfaces running parallel to one another. | 04-09-2009 |
20100000796 | Earth Drilling Device - The invention relates to an earth drilling device having a rotary drive and a drilling head connected to the rotary drive via a shaft. The invention is distinguished in that the shaft runs at least partially axially along a pipe with two pipe ends, the first pipe end of which is connectable to a vacuum source and the second pipe end of which is provided with a pipe opening over which the drilling head at least partially projects, that the drilling head is provided with at least two fillet sections connected to the shaft, which are attached to the shaft in radial extension and in projection to the axis of the pipe only partly cover the pipe opening, that the fillet sections are each connected to an axially oriented surface section whose surface, which is radially oriented outward, contacts the inner wall of the pipe in a gliding manner or contacts an inner wall of a sleeve coaxially connected to the second pipe end when the drilling head rotates, and that the axially oriented surface sections each are connected to a limb which axially projects over the pipe or the sleeve. | 01-07-2010 |
20120141259 | BLADE SEGMENT AND FLUID FLOW MACHINE - A blade segment ( | 06-07-2012 |
20130149165 | ROTATING BLADE HAVING A RIB ARRANGEMENT WITH A COATING - The present invention relates to a rotating blade ( | 06-13-2013 |
20130266426 | SEALING SYSTEM FOR A TURBOMACHINE - Disclosed is a sealing system for a turbomachine, in particular for a gas turbine, the sealing system being formed in an annular space between a flow-limiting wall of the turbomachine and at least one rotor blade tip of a rotor blade or an outer shroud arranged on the rotor blade tip, and comprising at least one sealing point. The sealing point comprises at least one run-in coating arranged on the rotor blade tip or on the outer shroud in the direction of the flow-limiting wall of the turbomachine. The invention furthermore encompasses a gas turbine comprising the sealing system. | 10-10-2013 |
20130266427 | SEALING SYSTEM FOR A TURBOMACHINE - A sealing system for a turbomachine, in particular, for a gas turbine, having an annular space between a flow-restricting wall and at least one series of rotor blades including a plurality of rotor blades. The sealing system comprises at least one first sealing fin disposed on an end of the rotor blade facing the wall, at least one second abradable lining disposed following the first sealing fin in the flow direction on the end of the rotor blade facing the wall, at least one first abradable lining disposed on the inside of the wall and opposite the first sealing fin, and at least one second sealing fin disposed in the flow direction following the first abradable lining on the inside of the wall and opposite the second abradable lining. The invention furthermore relates to a gas turbine comprising at least one sealing system. | 10-10-2013 |
20130272880 | MOVING BLADE AND TURBOMACHINE - A moving blade for a turbomachine, in particular an aircraft engine, is disclosed, having an inner shroud which has a front elongation for forming an axial overlap with an upstream guide blade, and on which at least one flow guide element for deflecting a leakage flow of a cooling air flow in the peripheral direction is situated. The at least one flow guide element is guided beyond a leading edge of the elongation. A turbomachine having a plurality of these types of moving blades is also disclosed. | 10-17-2013 |
20140178201 | TURBINE BLADE HAVING A SHROUD AND A CUTTING TOOTH - A turbine blade ( | 06-26-2014 |
20140348633 | TURBINE STAGE WITH A BLOW-OUT ARRANGEMENT AND METHOD FOR BLOWING OUT A SEALING GAS FLOW - A turbine stage having a gas channel in which at least one rotor assembly is disposed, is disclosed. A cavity communicates with the gas channel and is delimited by a front side of a rotor element and by a rotor element-mounted seal. A blow-out arrangement with at least one gas passage for blowing out a sealing gas flow into the cavity is provided, where the gas passage for blowing out the sealing gas flow is configured with a swirl in the circumferential direction and has an outlet opening that is offset radially outwardly from the rotor element-mounted seal. | 11-27-2014 |
20150017011 | BLADE FOR A GAS TURBOMACHINE - A blade, in particular a rotor blade or a stator vane, for a gas turbomachine, in particular a turbojet engine, the blade having an airfoil ( | 01-15-2015 |
20150037161 | METHOD FOR MOUNTING A GAS TURBINE BLADE IN AN ASSOCIATED RECEIVING RECESS OF A ROTOR BASE BODY - A gas turbine blade in an associated receiving recess of a rotor base body includes a slot in the blade root and has the shape of a straight cylinder. A blade retaining plate has a first securing region and a second securing region interconnected by a shaft region; the shaft region having the shape of a straight cylinder configured to conform to the slot of the blade root. The shaft region comes to rest on a bottom of the receiving recess of the rotor base body; the first securing region being reshaped to form a first limit stop for a first end wall of the blade root; and the second securing region being reshaped to allow the blade root to be inserted along the insertion direction into the receiving recess. The second securing region of the blade retaining plate is subsequently reshaped to allow the second securing region to form a second limit stop for a second end wall of the blade root facing opposite the first end wall, and the blade root to be secured in position in the receiving recess. | 02-05-2015 |
20150063983 | TURBOMACHINE - A turbomachine having a cooling device for supplying cooling air onto a compressor region from an air distribution chamber is disclosed, the air distribution chamber being arranged between an outlet diffuser of a compressor and a combustion chamber, where the cooling device has cooling air pipes for supplying cooling air from the air distribution chamber into a cavity between the outlet diffuser and a rotor segment of the compressor. | 03-05-2015 |