Abstract: A radial press is provided including a base, a hollow ring die mounted on the base rotatably relative to a press axis with an inner contour tapering in the direction of the axis and rotationally symmetrical, and a rolling element unit rotatable relative to the axis and having a pressure ring, which surrounds the axis, and a plurality of rolling elements arranged around the axis which are rotationally symmetrical. The rolling elements are supported on the pressure ring at a variable distance from the axis and can roll on the inner contour of the ring die. A rotary drive acts on the ring die or the rolling element unit and effects rotation about the axis. A feed drive also acts on the rolling element unit or the ring die and effects axial displacement of the rolling element unit and the ring die relative to each other.

Abstract: A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper.

Abstract: A turbine blade for a turbine rotor, is provided having a single-crystal basic body which has a blade tip and extends in the radial direction. The turbine blade includes at least one oxidation-resistant intermediate coating, which is applied by laser metal forming and is epitaxially bonded to the basic body, is arranged on the radially outer blade tip, and in that an at least single-layer, wear-resistant and oxidation-resistant coating, which is applied by laser metal forming and consists of oxidation-resistant binder material and abrasive particles embedded therein, is arranged on at least certain regions of said epitaxial intermediate coating.

Abstract: A dual brazing alloy element for a materially integral connection of a ceramic surface to a metallic surface includes a first layer having a Ni-based brazing alloy with a Ni content of at least 50% by weight and having at least one component configured to lower a melting point of the Ni-based brazing alloy selected from the group consisting of Si, B, Mn, Sn and Ge. A second layer includes an active brazing alloy material having a total content of 1-15% by weight of at least one active element selected from the group consisting of Ti, Hf, Zr and V.

Abstract: A leaf seal for sealing a shaft rotating about an axis, in particular in a gas turbine, includes a plurality of spaced-apart leaves arranged in a concentric circle around the axis and fixed in position by brazing, the leaves having surfaces oriented essentially parallel to the axis. The leaves are brazed to one another via intermediate spacers made of a brazing foil, so that a brazed joint is produced by brazing alloy from the brazing foils. The brazing temperature may be set to an optimum value just above the solidus temperature of the brazing foil, at which partial melting of the brazing foil occurs and penetration of liquid brazing alloy into the gap between the leaves is avoided.

Abstract: A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair.

Abstract: A dual brazing alloy element for a materially integral connection of a ceramic surface to a metallic surface includes a first layer having a Ni-based brazing alloy with a Ni content of at least 50% by weight and having at least one component configured to lower a melting point of the Ni-based brazing alloy selected from the group consisting of Si, B, Mn, Sn and Ge. A second layer includes an active brazing alloy material having a total content of 1-15% by weight of at least one active element selected from the group consisting of Ti, Hf, Zr and V.

Abstract: A blade arrangement of a gas turbine, with at least one blade which in the radial direction projects into a hot gas passage arranged concentrically to an axis, and terminates in a blade tip which with a clearance lies opposite a heat shield which delimits the hot gas passage. The blade and the heat shield are movable in relation to each other in the circumferential direction, and the blade tip and the heat shield are covered with coatings, which enable a directed cutting of the blade tip into the heat shield. By such a blade arrangement, a reduction of the clearance as a result of cutting in is simply achieved by the heat shield having a porous thermal barrier coating as an outer, abradable coating, and by the blade tip being provided with a homogenous, metallic cover coating.

Abstract: A turbine blade for a turbine rotor, is provided having a single-crystal basic body which has a blade tip and extends in the radial direction. The turbine blade includes at least one oxidation-resistant intermediate coating, which is applied by laser metal forming and is epitaxially bonded to the basic body, is arranged on the radially outer blade tip, and in that an at least single-layer, wear-resistant and oxidation-resistant coating, which is applied by laser metal forming and consists of oxidation-resistant binder material and abrasive particles embedded therein, is arranged on at least certain regions of said epitaxial intermediate coating.

Abstract: A combustion device for a gas turbine that includes a portion having first and second walls that defines an inside of the combustion device, a zone between the first and second walls and an outside of the combustion device. A plurality of first passages connect the inside of the combustion device to the zone between the first and second walls and a plurality of second passages connect the zone between the first and second walls to the outside of the combustion device. A plurality of chambers are defined within the zone between the first and second walls, each chamber being connected with one first passage and at least one second passage. Each chamber defining a Helmholtz damper.

Abstract: It is disclosed a method of applying a coating (12) with a controlled laser metal forming process. A light source with a specific power and a signal capturing apparatus is moved over an article (1) to form locally a melt pool (7) on the surface (5) of the article (1) to which a coating powder (8) is injected. An optical signal (13) is captured from the melt pool (7), and the monitored optical signal (13) is used for the determination of the temperature and temperature fluctuations of the melt pool (7). Furthermore, a control system (16) is used to adjust at least one process parameter such as the power of the light source to obtain desired melt pool properties. Subsequently the melt pool (7) solidifies. The high degree of control over the microstructure provides an efficient tool for generating laser metal formed hard coatings (12) with optimised wear properties.

Abstract: A gas turbine engine hot gas component repair method for defects that do not extend through the thickness of the component is provided. First defects are removed by machining a cavity in the surface of a component. Coupons, fittable within the cavities are manufactured, are for example coated with brazing medium on an inner surface and then joined to the component by joining means such as laser metal forming. The joint holds the coupon during later heat treatment, thereby eliminating a need for holding aids. Before heat treatment, a further brazing medium can be applied to the surface of the coupon overlapping onto the component. A single heat treatment, brazing the coupon to the component and, brazing the brazing medium to the outer surface of the coupon can, then be used to complete the repair.

Abstract: The invention relates to an oxidation and corrosion resistant braze alloy consisting of (wt.-%) 10-15% Cr, 4.5-6% Al, 0.17-0.3% Y, 8-12% Co, 0-4% W, 2.5-5% Ta, 2.0-3.5% B with Cr+Al>15%, Cr/Al?3 and Al+Ta>7.5%, remainder Nickel and unavoidable impurities and to the use of this alloy for brazing onto a Nickel based or a Cobalt based superalloy article. The braze alloy can either be used in pure form as a paste or a foil or as a blend in a blend braze paste, in a braze tape or in a pre-sintered braze sheet.

Abstract: A leaf seal for sealing a shaft rotating about an axis, in particular in a gas turbine, includes a plurality of spaced-apart leaves arranged in a concentric circle around the axis and fixed in position by brazing, the leaves having surfaces oriented essentially parallel to the axis. The leaves are brazed to one another via intermediate spacers made of a brazing foil, so that a brazed joint is produced by brazing alloy from the brazing foils. The brazing temperature may be set to an optimum value just above the solidus temperature of the brazing foil, at which partial melting of the brazing foil occurs and penetration of liquid brazing alloy into the gap between the leaves is avoided.

Abstract: It is disclosed a method of measuring the thickness and/or the depletion of Al and Cr of a ?/?? MCrAlY-coating after the use in a high temperature environment, the ?/? MCrAlY-coating exhibiting a non-equilibrium ?/??-microstructure at a temperature lower than the temperature during operation. Before the coating conductivity by means of a multifrequency eddy current system is measured a heat treatment is applied to transform the non-equilibrium ?/??-microstructure to a equilibrium microstructure having a ?-Cr phase. Subsequently the Al and/or Cr depletion of the coating from the coating conductivity and permeability is determined.

Abstract: It is disclosed a method of determining the exposure temperature of Al and Cr of a ?/?? MCrAlY-coating after the use in a high temperature environment, the ?/?? MCrAlY-coating exhibiting a non-equilibrium ?/??-microstructure at a temperature lower than the temperature during operation and the depletion of chromium from the ?/??-MCrAlY-coating still allows the ?-Cr phase to form. The coating conductivity and permeability by means of a multifrequency eddy current system is measured at different locations of the component and from the measured conductivity and permeability the exposure temperature of said different locations of the components is determined.

Abstract: A gas turbine component consists of a superalloy base material with a single crystal structure and a protective MCrAlY-coating (6). The MCrAlY-coating (6) has a g/g? single crystal structure, which is epitaxial with the base material. It has be determined the critical factors for the successful epitaxial and crack-free growth of the MCrAlY-coating (6).

Abstract: In a heat treatment process for a single-crystal or directionally solidified material body comprising a nickel-based superalloy, the material body is solution-annealed and then at a first temperature ?? particles of greater than 1 ?m are precipitated in a proportion by volume with Vtot?V1 of less than 50%, where Vtot is the total amount of ?? particles after complete heat treatment and V1 is the proportion of the ?? particles which is greater than 1 ?m, and at least at a second temperature ‘?’ particles of less than 1 ?m are precipitated. The ?? particles are preferably precipitated in a size of 2 pin or more with a proportion by volume of 0.25<(Vtot?V1)/(100?V1)<0.55 at the first temperature. The proportion by volume Vtot of the ?? particles will be at least 50%.

Abstract: It is disclosed a method of applying a coating (12) with a controlled laser metal forming process. A light source with a specific power and a signal capturing apparatus is moved over an article (1) to form locally a melt pool (7) on the surface (5) of the article (1) to which a coating powder (8) is injected. An optical signal (13) is captured from the melt pool (7), and the monitored optical signal (13) is used for the determination of the temperature and temperature fluctuations of the melt pool (7). Furthermore, a control system (16) is used to adjust at least one process parameter such as the power of the light source to obtain desired melt pool properties. Subsequently the melt pool (7) solidifies. The high degree of control over the microstructure provides an efficient tool for generating laser metal formed hard coatings (12) with optimised wear properties.

Abstract: A gas turbine component consists of a superalloy base material with a single crystal structure and a protective MCrAlY-coating. The MCrAlY-coating the MCrAlY has a ?/?-phase and single crystal structure, which is epitaxial with the base material.