Abstract: A system for injecting a fluid into a wall boundary layer of a flow in a turbomachine is disclosed. The system has a plurality of nozzles which are disposed in a side wall limiting the flow and are oriented diagonally in the direction of flow. The nozzles each have a rectangular, flat nozzle cross-section. A compressor having such a system, as well as a turbomachine having such a compressor, are also disclosed.
Abstract: The invention relates to a method for cleaning a turbo-machine stage (100) consisting of at least one of the following steps: a cleaning nozzle (1) is introduced into an opening of a turbo-machine, in particular into an inspection opening (220); and the blade (100) of the stage is acted upon by solid particles, said particles subliming at the blade temperature, in particular into dry ice particles.
Type:
Application
Filed:
August 3, 2011
Publication date:
July 11, 2013
Applicant:
MTU AERO ENGINES GMBH
Inventors:
Jürgen Rösing, Frank Seidel, Lutz Winkler, Bernd Kriegl, Thomas Uihlein, Martin Dürr, Fabian Moritz
Abstract: The invention relates to a method for optically detecting surfaces wherein strip patterns are projected onto the surface, images are captured, and the three-dimensional contour thereof is determined from the reproduction of the strip pattern on the surface of the object. The aim of the invention is to prevent reflections that interfere with the images and as a result, the surface of the object is covered with a layer of a fluorescent material, is then radiated with ultraviolet radiation, and the radiation emitted by the fluorescent material in the visible light is detected.
Type:
Grant
Filed:
June 6, 2008
Date of Patent:
July 9, 2013
Assignee:
MTU Aero Engines AG
Inventors:
Joachim Bamberg, Roland Höfling, Wilhelm Satzger
Abstract: A method is disclosed for the repair of a component of a turbomachine, in particular a rotor of an aircraft gas turbine, with blades taken up in at least one groove and with at least one support region for limiting a blade tilt angle, whereby at least one segment, which has been subjected to wear, of the support region of the component is removed, and a coating that can be introduced in the unit on at least one supporting surface of at least one blade is formed on the component for limiting the blade tilt angle. In addition, a component of a turbomachine, in particular a rotor of an aircraft gas turbine, with at least one such repair site is disclosed.
Abstract: A machining or processing apparatus (14) for machining or processing a sealing element (16) located within a housing (12) of a gas turbine (10), the machining or processing apparatus (14), at least in the partially assembled state of the gas turbine (10), being at least partly introducible through a port (22) of the housing (12) into an interior space (24) of the gas turbine (10) and including a machining or processing device (15) which allows work to be performed on the sealing element (16) upon introduction of the machining or processing apparatus (14) under relative movement of the machining or processing device (15) and the sealing element (16). In addition, a method for machining or processing a sealing element (16) located within a housing (12) of a gas turbine (10).
Abstract: A method for repairing turbine blades by replacing at least a part of the blade profile, the method having: a) manufacture of a replacement blade part; b) separation of the damaged area with a standardized cutting plane, leaving behind a remaining blade; c) matching of the replacement blade part to the actual geometry of the remaining blade; d) connecting or joining of the replacement blade part to the remaining blade by soldering of at least one web and welding of an outer contour.
Abstract: A mounting device and method for mounting a component is disclosed. The mounting device includes a component carrier and an adapter. The adapter is insertable into a guide of the component carrier. The method uses the mounting device to mount a component on the mounting device.
Abstract: A turbomachine stage including guide vanes, radially inner and/or radially outer airfoil platforms, which together form a guide vane cascade, and further including rotor blades, radially inner and/or radially outer airfoil platforms, which together form a rotor blade cascade adjacent to the guide vane cascade. Radially outer airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies, in particular periodically, in the radial and/or axial direction around the circumference.
Abstract: A turbomachine stage includes guide vanes and an airfoil platform forming a guide vane cascade, and rotor blades and an airfoil platform forming a rotor blade cascade. Airfoil platforms have cascade regions extending between circumferentially adjacent airfoils, and gap regions which radially and/or axially bound an axial gap extending axially between the guide vane cascade and the rotor blade cascade. A contour of at least one of these gap regions varies in the radial and/or axial direction around the circumference.
Abstract: The present invention relates to a rotating blade (5), in particular for a compressor or turbine stage of a gas turbine, having a radially outer rib arrangement with at least one rib (2), onto which a coating (3) is disposed, whereby, in a meridian section (FIGS. 2, 3, 4), the coating (3) has an outer contour (3.1), which extends axially outwardly in the radial direction.
Abstract: A method for depositing material layers on a workpiece made of a material which contains a titanium aluminide includes the steps of preparing the workpiece; heating the workpiece in a localized region by induction to a predefined preheating temperature; and depositing an additive, preferably in powder form, on the heated surface of the workpiece by build-up welding, in particular laser build-up welding, plasma build-up welding, micro-plasma build-up welding, TIG build-up welding or micro-TIG build-up welding; said additive including a titanium aluminide.
Type:
Application
Filed:
June 16, 2011
Publication date:
June 6, 2013
Applicant:
MTU AERO ENGINES GmbH
Inventors:
Karl-Hermann Richter, Herbert Hanrieder, Sonja Dudziak, Albert Grueninger
Abstract: A method for removing a layer made of a first material from a surface of a body made of a second material is disclosed. The body is subjected to a pressurized jet containing a blasting medium composed of particles, where the pressurized jet at least intermittently has an Almen intensity of at most 0.35 Almen A, preferably at most 0.3 Almen A and particularly preferably at most 0.25 Almen A.
Type:
Application
Filed:
August 6, 2011
Publication date:
June 6, 2013
Applicant:
MTU Aero Engines GmbH
Inventors:
Horst Pillhoefer, Johann Oettl, Markus Niedermeier, Thomas Cosack, Dirk Ruhlig
Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades.
Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions formed and disposed on a lateral wall having a plurality of blades such that at least one depression is disposed on a blade pressure side and at least one thickened area is disposed on a blade suction side for each blade of the plurality of blades.
Abstract: A vibration dampened power generation aggregate including an internal combustion engine, generator and outlet box mounted upon a frame having vibration dampening mounts for the power generation aggregates. The outlet box as an interior space divided into compartments for the placement of accessories, switches and generator governors. The frame has a first side and a second side and the power generation aggregate is mounted on the frame such that the mass of the power generation aggregate is evenly distributed on the first and second sides to reduce harmonic vibration and sound transmission of the power generation aggregate on the frame during aggregate operation.
Type:
Grant
Filed:
March 4, 2010
Date of Patent:
May 28, 2013
Assignee:
MTU Friedrichshafen GmbH
Inventors:
Wolfgang Farr, Todd Riemann, Kurt Snaza
Abstract: A device and method for axially displacing at least one turbine rotor relative to at least one corresponding turbine stator in a multistage axial turbine is disclosed. The turbine shaft is provided with a split design and has a first axially displaceable shaft half, which is connected via a turbine disc to the turbine rotor and via a torque coupling to the second shaft half. By axially displacing the turbine rotor relative to the turbine stator and by controlling this axial displacement, the operation of the turbine is held in its possible optimum of efficiency.
Abstract: A method for coating a plastic surface and a plastic component is disclosed. The method includes applying a base layer to a plastic surface. A layer of a coating is applied by kinetic cold gas spraying on the base layer. The base layer is applied by a method that is different from the kinetic cold gas spraying. The base layer adheres to the plastic surface and the layer of the coating applied by kinetic cold gas spraying is deposited on the base layer by the kinetic cold gas spraying.
Type:
Application
Filed:
November 11, 2010
Publication date:
May 23, 2013
Applicant:
MTU AERO ENGINES GMBH
Inventors:
Manuel Hertter, Andreas Jakimov, Mihaela-Sorina Seitz, Marcin Olbrich, Juergen Kraus, Bertram Kopperger, Klaus Broichhausen, Hans Banhirl, Erwin Bayer, Wolfgang Werner, Eberhard Knodel
Abstract: A method for automatically controlling an internal combustion engine, where, during normal operation in a first controller mode, a charge air temperature controller is set as dominant for a map-controlled thermostatic valve for automatically controlling the charge air temperature (TLL), or, during normal operation in a second controller mode, a coolant temperature limit controller is set as dominant for the map-controlled thermostatic valve for automatically controlling the coolant temperature (TKM). If a charge air temperature sensor fails, the second controller mode is set with the coolant temperature limit controller dominant, and if a coolant temperature sensor fails, the first controller mode is set with the charge air temperature controller dominant.
Abstract: A process for manufacturing a honeycomb seal is disclosed. The process includes the following steps: a) the honeycomb structure is brought to the desired three-dimensional form and is fixed in this form; b) then the honeycomb structure is filled with a filler material; c) then the honeycomb structure filled with the filler material is machined on a side on which a carrier element is arranged, such that this side has the desired contour and that the end edges of the honeycomb structure are sealed flushly with the filler compound; d) then the side contoured in this way is coated with a coating; e) next the carrier element is applied to the coating, preferably by laser powder build-up welding.
Abstract: A pre-chamber sparkplug is suggested with a central electrode, with at least one ground electrode, which is distanced from the central electrode forming a spark gap, and with at least one transfer bore in a pre-chamber cap. The ground electrode comprises an internal circumferential area, which faces the central electrode, and an external circumferential area, which faces away from the central electrode. The internal circumferential area of the ground electrode shows a concave progression in the longitudinal direction of the pre-chamber sparkplug, subjected to a tensile force, and the external circumferential area shows a convex progression in the longitudinal direction of the pre-chamber sparkplug, subjected to a pressure.