Patent application number | Description | Published |
20110293408 | SEALING APPARATUS AT THE BLADE SHAFT OF A ROTOR STAGE OF AN AXIAL TURBOMACHINE - A turbomachine is disclosed. The turbomachine includes a rotor, a plurality of blades arranged side by side on the rotor in a circumferential direction, and a plurality of sealing apparatuses each disposed on a respective blade shaft of the plurality of blades. Each of the plurality of sealing apparatuses includes first and second bottom plates protruding in a respective axial direction on the respective blade shaft and first and second bulkheads which extend in a radial direction along the respective blade shaft and form a double-walled seal in the axial direction. A respective rounded or parabolic transitional cross-section from the bottom plates to the bulkheads is provided and at least one of the bulkheads is offset with respect to a blade root edge of the respective blade shaft in a direction toward a radial longitudinal axis of the respective blade shaft. | 12-01-2011 |
20130189086 | SEAL ASSEMBLY, METHOD AND TURBOMACHINE - A sealing arrangement for a turbomachine for sealing a radial gap between a rotor and a stator, with a plurality of sealing segments each comprising a honeycomb element and a base body for holding the honeycomb element, and with at least one support for arranging the sealing segments on a rotor section or stator section, wherein the base bodies can be arranged on the at least one support by a radial movement and by a plastic deformation of at least one body section, a generative method for the integral production of the sealing segments, and a turbomachine are disclosed. | 07-25-2013 |
20140041360 | FLOW CONDUCTING ASSEMBLY FOR COOLING THE LOW-PRESSURE TURBINE HOUSING OF A GAS TURBINE JET ENGINE - A gas turbine jet engine having a main flow channel ( | 02-13-2014 |
20140044529 | SEALING OF THE FLOW CHANNEL OF A TURBOMACHINE - A turbomachine having a flow channel and a housing radially surrounding the flow channel, a plurality of stationary and moving blades being situated in the flow channel, stationary blades being situated adjacent to the moving blades in the axial direction, and the stationary blades having at least one stationary blade hook which engages with at least one housing hook for the purpose of connecting the stationary blades to the housing. A sealing and lining element is situated in the radial direction between the moving blades adjacent to the stationary blades and the housing, and has a sealing structure interacting with blade tips of the moving blades. A heat protection element is provided in the area between the sealing and lining element and the housing, and a sealing element being situated on the heat protection element for the purpose of sealing contact with the housing hook. | 02-13-2014 |
20140044538 | CLAMPING RING FOR A TURBOMACHINE - A turbomachine having a flow channel ( | 02-13-2014 |
20140102107 | HOUSING STRUCTURE WITH IMPROVED SEAL AND COOLING - A housing structure for a turbo-engine, especially for a gas turbine or an aircraft engine, includes an outer housing wall and an inner housing wall, the inner and outer housing walls annularly enclosing a flow channel for the turbo-engine and being spaced apart radially from the flow channel. At least one heat shield is arranged between the inner and outer housing walls, and a bar or a fixture projects at least somewhat radially from the inner housing wall. The bar or the fixture has on at least one side a broadening element that includes a sealing face against which the heat shield is positioned in a sealing manner. | 04-17-2014 |
20140105731 | AXIAL SEAL IN A CASING STRUCTURE FOR A FLUID FLOW MACHINE - A casing structure for a fluid flow machine, in particular for a gas turbine or an aircraft engine, including an outer casing wall and an inner casing wall, which annularly surround a flow channel of the fluid flow machine and are spaced apart in a radial direction with respect to the flow channel. At least one cavity is formed between the inner and outer casing walls. The cavity is axially divided into at least two regions which are separated from each other by an axial seal in such a way that different pressure conditions are created according to the axial position of these regions, which different pressure conditions correspond to the pressure conditions in the flow channel. A corresponding fluid flow machine such as, for example, an aircraft engine. | 04-17-2014 |
20140112767 | COOLING-AIR GUIDANCE IN A HOUSING STRUCTURE OF A TURBOMACHINE - A housing structure for a turbomachine, the housing structure annularly surrounding, at least partially, a flow channel ( | 04-24-2014 |
20140112768 | FORM-FITTING HOUSING COMPONENT COMBINATION AND METHOD FOR THE MANUFACTURE THEREOF - A component combination for a shell of a flow channel ( | 04-24-2014 |
20140119902 | SEAL CARRIER ATTACHMENT FOR A TURBOMACHINE - A housing structure for a turbomachine having a stationary blade ring annularly surrounding a flow channel, and having a seal carrier ring which also annularly surrounds the flow channel, the stationary blade ring and the seal carrier ring being connected to each other, and either the stationary blade ring or the seal carrier ring having a one-sidedly open receptacle in the radial direction in relation to the flow channel and a radially projecting engagement area which corresponds to the connected seal carrier ring or stationary blade ring and which is held in a form-fitting manner in the axial direction and in the radial direction in the direction of the closed side of the receptacle but is freely movable with respect to the connected receptacle and the seal carrier ring or stationary blade ring having this receptacle in the radially opposite direction in the direction of the receptacle opening. | 05-01-2014 |
20140178201 | TURBINE BLADE HAVING A SHROUD AND A CUTTING TOOTH - A turbine blade ( | 06-26-2014 |
20140321969 | SLIDE RING SEAL - A turbomachine in the form of a stationary gas turbine or an aircraft engine, respectively a housing structure therefor; the housing structure including an outer housing wall ( | 10-30-2014 |
20140348655 | BALANCING BODY FOR A CONTINUOUS BLADE ARRANGEMENT - The present invention relates to a balancing body ( | 11-27-2014 |
20140363270 | TURBINE CASING HAVING REINFORCEMENT ELEMENTS IN THE CONTAINMENT AREA - A turbine casing ( | 12-11-2014 |
20140363284 | STATOR VANE SEGMENT OF A FLUID FLOW MACHINE AND TURBINE - A stator vane segment ( | 12-11-2014 |
20150086331 | BAUTEILSYSTEM EINER TURBOMASCHINE - A component system of a turbine engine including a first component segment and a second component segment configurable in a ring segment shape, so that at least one abutment surface of the first component segment and an abutment surface of the second component segment abut against each other; together, the first component segment and the second component segment including at least three overlapping elements for sealing a gap between the abutment surfaces. In the case of mutually abutting abutment surfaces, each overlapping element overlapping radially with the respective other component segment. At least two of the overlapping elements are configured on the first component segment, while at least one of the overlapping elements is configured on the second component segment. In the case of mutually abutting abutment surfaces, the overlapping element of the second component segment is axially configured between the overlapping elements of the first component segment. | 03-26-2015 |