Abstract: A turbocharger configuration, particularly in or for a motor vehicle, includes at least one turbocharger stage, which has a turbine and a compressor that are mechanically decoupled from each other. A turbochargeable internal combustion engine having such a turbocharger configuration, is also provided.

Abstract: There is described an arrangement comprising at least one luminescent heat insulating layer which is disposed on a carrier body, for preventing heat transfer between the carrier body and the surrounding area of the carrier body. The heat insulating layer comprises at least one luminous substance which can be excited, with the aid of an excitation light having a determined excitation wave length for emitting a luminescent light having a determined luminescent wave length. At least one additional heat insulating layer, which is essentially free from the luminous substance, is provided. The additional heat insulating layer is essentially opaque to the excitation light in order to excite the emission of luminous light and/or for the luminous light of the luminescent substance.

Abstract: The invention relates to a turbine comprising at least four stages and to the use of a rotor blade with a reduced mass. In prior art, rotor blades in the fourth stage of a gas turbine, which exceed 50 cm in length, cause problems relating to mechanical strength, as centrifugal forces of too great a magnitude occur during the rotation of the rotor blades. An inventive rotor blade in the fourth row of a gas turbine has a reduced density as a result of a high proportion of a ceramic, thus reducing the centrifugal force.

Abstract: A device for and method of packaging electronic components (1) using injection-molding. For this purpose, a multiplicity of components (1) are arranged in predetermined positions on a first side (2) of a leadframe (3). The leadframe (3) has interconnects (5) with contact terminal areas (6) for connecting to contact areas (7) of the electronic components (1) and contact vias (8) to external contacts on a second side (10) of the leadframe (3). In this case, the leadframe (3) includes a ceramic substrate (11) with a first side (2) having edge regions (12) configured with a ductile, annular metal layer (13).

Abstract: An apparatus for monitoring the structural integrity of a component. A monitoring structure is applied to a component that is subject to structural degradation. The monitoring structure includes an electrical conductor that becomes cracked if the component becomes structurally degraded. When the component is a ductile metal component that may be degraded by bending, the electrical conductor is formed of a brittle material that cracks when the ductile metal component is bent. When the component is a brittle ceramic heat shield wherein a crack having a critical length is of concern, the electrical conductor is located at a predetermined location wherein a critical length crack in the component will propagate into the conductor. A crack in the electrical conductor is detected with a monitoring device to indicate a degraded structural condition in the component.

Abstract: An arrangement of at least one heat-insulation layer for a carrier body for preventing heat transfer between the body and a surrounding area includes at least one type of luminous substance which is excitable by an excitation light having a determined excitation wavelength for emitting a luminescent light having a defined emission wavelength and at least a second heat-insulation layer substantially free of the luminous substance. The second heat-insulation layer is opaque with respect to the excitation light used for initiating the luminescent light emission and/or to a luminous substance light. The luminous substance contains at least one type of mixed oxide selected from a perovskite group of total formula AA?O3, and/or of pyrochlore of total formula A2B2O7, wherein A and A? is the trivalent metal, respectively and B is a tetravalent metal.

Abstract: A heat-insulation material for a heat-insulation layer (3) for a carrier body (2) for preventing heat transfer between the carrier body and a surrounding area (7) therearound includes at least one luminous substance which is excitable for emitting luminescent light having a defined emission wavelength and includes at least one type of metal oxide containing at least one trivalent metal (A). Also described is an arrangement of at least one heat-insulation layer which contains the heat-insulation material and is applied to the carrier body. The described heat-insulation material is characterised in that the metal oxide is embodied in the form of a mixed oxide selected in a perovskite group of total formula AA?O3, and/or of pyrochlore of total formula A2B2O7, wherein A? is the trivalent metal and B is a tetravalent metal. The heat-insulation layer containing the heat-insulation material is preferably used for a gas turbine.

Abstract: A method and device for layer thickness determination allows for the layer thickness to be determined in situ during the coating process. This is achieved using a sensor which has an electrical property which, as a result of the coating process, changes in a manner which is representative of the layer thickness which has been reached. As such, this property can be measured.

Abstract: The invention relates to an assembly that consists of a structural element and at least one control element for detecting degradation of said structural element. Said control element comprises an electroconducting control structure that is decoupled from a functionality of the structural element and that has a defined electrical property. The control structure and the structural element are firmly interlinked to such an extent that the degradation of the structural element effects a degradation of the control structure and thus a change of the defined electrical property of the control structure. The structural element is for example a ceramic heat shield of a combustion chamber of a gas turbine. The control structure consists of a brittle ceramic conductor material.

Abstract: A method and device for layer thickness determination allows for the layer thickness to be determined in situ during the coating process. This is achieved using a sensor which has an electrical property which, as a result of the coating process, changes in a manner which is representative of the layer thickness which has been reached. As such, this property can be measured.

Abstract: The invention relates to a turbine comprising at least four stages and to the use of a rotor blade with a reduced mass. In prior art, rotor blades in the fourth stage of a gas turbine, which exceed 50 cm in length, cause problems relating to mechanical strength, as centrifugal forces of too great a magnitude occur during the rotation of the rotor blades. An inventive rotor blade in the fourth row of a gas turbine has a reduced density as a result of a high proportion of a ceramic, thus reducing the centrifugal force.

Abstract: Thermal barrier coating systems according to the prior art are exposed to mechanical loads, and in particular ceramic layers tend to form cracks or to flake off on account of their brittleness. A thermal barrier coating system (19) according to the invention includes a second phase (34), which mechanically reinforces the matrix (31) of the layer (25, 28).

Abstract: The invention relates to a product (1), particularly a gas turbine blade that can be exposed to a hot aggressive gas (7). The product (1) has a metallic basic body (2), which is provided with a thermal barrier coating (4) having a spinel of the composition AB2O4.

Abstract: The invention relates to a heat shield block, in particular for lining a combustion chamber wall, having a hot side which can be subjected to a hot medium, a wall side opposite the hot side, and a peripheral side adjoining the hot side and the wall side. A tension element which can be prestressed to a prestress (Fz) is attached to the peripheral side, release of a fragment, formed during a fracture, of the heat shield block being reliably prevented by the prestress (Fz) of the tension element. The invention also relates to the use of a heat shield block, in particular for lining a combustion chamber wall of a gas turbine.

Abstract: A method and device for layer thickness determination allows for the layer thickness to be determined in situ during the coating process. This is achieved using a sensor which has an electrical property which, as a result of the coating process, changes in a manner which is representative of the layer thickness which has been reached. As such, this property can be measured.

Abstract: A device for and method of packaging electronic components (1) using injection-molding. For this purpose, a multiplicity of components (1) are arranged in predetermined positions on a first side (2) of a leadframe (3). The leadframe (3) has interconnects (5) with contact terminal areas (6) for connecting to contact areas (7) of the electronic components (1) and contact vias (8) to external contacts on a second side (10) of the leadframe (3). In this case, the leadframe (3) includes a ceramic substrate (11) with a first side (2) having edge regions (12) configured with a ductile, annular metal layer (13).

Abstract: An article that is particularly well suited for use as a gas turbine engine component has a metallic substrate and a ceramic thermal barrier layer including a mixed metal oxide system comprising a compound selected from the group consisting of (i) a lanthanum aluminate and (ii) a calcium zirconate, the calcium in which is partially replaced by at least one calcium-substitute element, such as strontium (Sr) or barium (Ba). In addition, the lanthanum in the lanthanum aluminate can be partially replaced by a lanthanum-substitute element from the lanthanide group, particularly gadolinium (Gd). A process for producing such an article comprises providing a pre-reacted mixed metal oxide system as described above and applying it to the substrate by plasma spraying or an evaporation coating process.

Abstract: The invention relates to a heat shield block, in particular for lining a combustion chamber wall, having a hot side which can be subjected to a hot medium, a wall side opposite the hot side, and a peripheral side adjoining the hot side and the wall side. A tension element which can be prestressed to a prestress (Fz) is attached to the peripheral side, release of a fragment, formed during a fracture, of the heat shield block being reliably prevented by the prestress (Fz) of the tension element. The invention also relates to the use of a heat shield block, in particular for lining a combustion chamber wall of a gas turbine.

Abstract: An article that is particularly well suited for use as a gas turbine engine component has a metallic substrate and a ceramic thermal barrier layer including a mixed metal oxide system comprising a compound selected from the group consisting of (i) a lanthanum aluminate and (ii) a calcium zirconate, the calcium in which is partially replaced by at least one calcium-substitute element, such as strontium (Sr) or barium (Ba). In addition, the lanthanum in the lanthanum aluminate can be partially replaced by a lanthanum-substitute element from the lanthanide group, particularly gadolinium (Gd). A process for producing such an article comprises providing a pre-reacted mixed metal oxide system as described above and applying it to the substrate by plasma spraying or an evaporation coating process.

Abstract: An article that is particularly well suited for use as a gas turbine engine component has a metallic substrate and a ceramic thermal barrier layer including a mixed metal oxide system comprising a compound selected from the group consisting of (i) a lanthanum aluminate and (ii) a calcium zirconate, the calcium in which is partially replaced by at least one calcium-substitute element, such as strontium (Sr) or barium (Ba). In addition, the lanthanum in the lanthanum aluminate can be partially replaced by a lanthanum-substitute element from the lanthanide group, particularly gadolinium (Gd). A process for producing such an article comprises providing a pre-reacted mixed metal oxide system as described above and applying it to the substrate by plasma spraying or an evaporation coating process.