Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.

Abstract: A device such as a drum for positioning at least one guide blade row from a plurality of guide blade groups in a turbomachine, the device on the outer circumferential side including at least one flange for attachment to a housing section of the turbomachine and on the inner circumferential side including a plurality of uniformly distributed receptacles for accommodating holding elements of the guide blade groups and a plurality of recesses, the device having a depth-reduced inner circumferential section, relative to the accommodating grooves, between at least two adjoining receptacles, which extends in each case from the one receptacle to the other receptacle; a blade-device combination; a method for assembling such a blade-device combination; and a turbomachine.

Abstract: A turbomachine including at least one blade-row group that is arranged in the main flow path and at least two rows of blades that are adjacent to each other in the main flow direction, each row having a plurality of blades (38, 40), whereby a narrow cross section and a degree of overlap between the blades of the upstream row of blades and the blades of the downstream row of blades vary starting at the center of the main flow path in the direction of at least one main flow limiter.

Abstract: A method for producing a component of a turbomachine is disclosed. The method includes a) layer-by-layer deposition of a powder component material onto a component platform in a region of a buildup and joining zone, where the deposition takes place in accordance with layer information of the component to be produced; b) local layer-by-layer fusion or sintering of the powder component material by energy supplied in the region of the buildup and joining zone, where the buildup and joining zone is heated to a temperature just below a melting point of the powder component material; c) layer-by-layer lowering of the component platform by a predefined layer thickness; and d) repetition of steps a) to c) until the component is finished. A device for producing a component of a turbomachine is also disclosed.

Abstract: A method for coating a turbine blade of a gas turbine is disclosed. The method includes applying a lacquer coat to a region of the turbine blade, where the lacquer coat includes chromium particles and/or chromium alloy particles, halides, and a binding agent. The method further includes drying the applied lacquer coat at a temperature between 50° C. and 600° C. with disintegration of the binding agent and subsequent reactive connection at a temperature between 900° C. and 1160° C.

Abstract: An inner ring for forming a guide blade ring for a turbomachine is disclosed, composed of at least two one-part ring segments having a plurality of openings, closed on the peripheral side, for accommodating journal bearings on the blade side, the outer diameter of the inner ring being at least 12 times larger than its height. Also disclosed are a guide blade ring having this type of inner ring and a turbomachine having this type of guide blade ring.

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 method for producing a rotor, particularly a turbine disk or a turbine ring for a turbine stage of a turbomachine, wherein at least the following steps are carried out: producing a blade ring (14) including a plurality of rotor blades (12), welding adapters (22) together which are disposed in the region of blade footings of the rotor blades (12), wherein at least substantially radial weld seams (30a) having predetermined welding depths are generated, disposing a rotor disk (32) or a rotor ring on the blade ring (14), and welding the rotor disk (32) or the rotor ring to the adapters (22) of the rotor blades (12), wherein at least one further weld seam (30b) is generated. A rotor, particularly a turbine disk or a turbine ring for a turbine stage of a turbomachine is also disclosed.

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: A method for electrochemically processing a workpiece surface using an electrode, which has at least one effective surface for processing the workpiece surface, and using an electrolyte, wherein the electrolyte is suctioned away from the effective surface. The invention further relates to an electrode, which has at least one electrolyte feed for supplying the electrolyte to the effective area and an electrolyte suctioning system for suctioning the electrolyte away from the effective area.

Abstract: A sealing system and method is disclosed. The sealing system includes a brush sealing element and an accommodating element with an accommodating chamber. The brush sealing element is disposed in the accommodating chamber and a bendable strap is disposed on the accommodating element. The method includes fastening the brush sealing element in the accommodating chamber of the accommodating element. The accommodating element is arranged in a groove of a housing segment and a position of the accommodating element is secured on the housing element by bending the strap of the accommodating element to engage with a side wall of the housing segment.

Abstract: A turbine or compressor stage of a gas turbine, the rotor blade having a radially outer shroud (1) which has a sealing fin array having a first sealing fin (3.1) and a second sealing fin (3.2) which is adjacent to the first sealing fin and connected thereto by a first groove base (10) having a circumferential region (13) of maximum radial height, which is located at a first circumferential position is provided. The sealing fin array has a third sealing fin (3.3) adjacent to the second sealing fin and opposite to the first sealing fin, the third sealing fin being connected to the second sealing fin by a second groove base (20) having a circumferential region (23) of maximum radial height, which is located at a second circumferential position different from the first circumferential position.

Abstract: A blade for a turbomachine is disclosed. At least one cooling channel is configured in the blade neck, whose inlet is disposed near a platform projection on the high-pressure side and whose outlet is disposed in the region of a platform projection on the low-pressure side. An integrally bladed rotor base body having a plurality of these types of blades as well as turbomachine with such a rotor base body is also disclosed.

Abstract: A blading for a turbine, in particular a gas turbine, is disclosed. The blades of the blading in a section near the tip have a distribution ratio (t/l) of at least 0.70, in particular at least 0.9, and/or at most 0.97, in particular at most 0.95. A downstream flow angle (?) is at most 167°, in particular at most 165°, and at least 155°, in particular at least 160°. In addition, or alternatively, an acceleration ratio (w2/w1) is at least 1.4, in particular at least 1.5.

Abstract: A blade of a turbomachine is disclosed. A contour variation is provided on the suction side of the blade, where the contour variation has a negative step as viewed in a direction of flow. The step has a stepped surface extending perpendicularly to a contour of the suction side and the contour variation has a tangential surface which leads upstream tangentially on the contour of the suction side starting from a step edge.

Abstract: A rotor for a turbomachine, in particular for a jet engine, having a blade ring which includes multiple differently designed rotor blades (10a, 10b) having blade platforms (14a, 14b) engaged flush with one another, the blade ring including at least two groups of differently designed rotor blades (10a, 10b), each group of rotor blades (10a, 10b) being assigned blade platforms (14a, 14b), each of which is engageable flush with a matching blade platform (14a, 14b) of at least one other group of rotor blades (10a, 10b) and not with a blade platform (14a, 14b) of the same group of rotor blades (10a, 10b). A method for manufacturing a blade ring of a rotor for a turbomachine is also provided.

Abstract: A compressor having a stator vane assembly having an inner ring and a seal carrier secured thereto, the seal carrier having two opposite seal carrier end faces and the inner ring having two inner ring end faces which face said seal carrier end faces and are received between said seal carrier end faces with an axial gap therebetween, at least one clamping element bearing axially with a first clamping element end face against the inner ring and with a second clamping element end face against the seal carrier and being axially resiliently clamped between the inner ring and the seal carrier. A compressor with a clamping element for radial clamping is also provided.

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; the additive including a titanium aluminide.

Abstract: A safety device (10) for a bearing arrangement of a rotor of a turbomachine, whereby the safety device (10) includes at least two support structures (12) between which at least one buckling structure (14) is arranged that is configured to collapse when a predetermined buckling load that acts on at least one of the support structures (12) is exceeded, thereby reducing the volume of the safety device (10). A method for the production of a safety device (10) for a bearing arrangement of a rotor of a turbomachine, as well as to a bearing arrangement of a rotor of a turbomachine having such a safety device (10).

Abstract: A housing-side structure of a turbomachine, in particular of a gas turbine, including an in particular segmented jacket ring (16), which carries an abradable lining for radially outer ends of rotor-side moving blades of a moving blade ring, wherein the jacket ring (16) carrying the abradable lining is connected by means of at least one constriction (18) to a stator-side housing part (19), which is radially adjacent to the jacket ring (16) on the outside and the jacket ring is thermally decoupled from said stator-side housing.