Abstract: A gas turbine engine having a waste heat recovery system is provided. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath, the exhaust section including a primary exhaust flowpath and a waste heat recovery flowpath parallel to the primary exhaust flowpath; and the waste heat recovery system includes a heat source exchanger positioned in thermal communication with a first portion of the waste heat recovery flowpath.

Abstract: The invention relates to a method for measuring a concentration of a gas in a gas mixture, said method comprising that: a light beam modulated in a ramp shape and/or in a step shape in its wavelength and additionally periodically modulated, in particular in its wavelength, is transmitted from a light source, in particular a laser, into a measurement zone; the modulated light beam passes through a gas mixture in the measurement zone and is detected as reception light by a detector, wherein the reception light is converted by the detector into a detector signal; a derivative signal is determined based on the detector signal by performing a transformation of the detector signal into the frequency range, in particular by a Fourier transform of the detector signal, wherein an evaluation of the detector signal transformed into the frequency range is performed, in particular only, for an n-fold of the frequency of the modulated light beam in order to obtain the derivative signal; and at least two measurement values

Abstract: A gas turbine engine having a waste heat recovery system is provided. The gas turbine engine includes a compressor section, a combustion section, a turbine section, and an exhaust section in serial flow order and together defining a core air flowpath, the exhaust section including a primary exhaust flowpath and a waste heat recovery flowpath parallel to the primary exhaust flowpath; and the waste heat recovery system includes a heat source exchanger positioned in thermal communication with a first portion of the waste heat recovery flowpath.

Abstract: A method for making a cooled component for a turbine engine includes casting an airfoil assembly having an airfoil with an airfoil cooling passage and extending from a platform with at least one platform cooling passage, and forming a connecting passage between the airfoil cooling air passage and the platform cooling air passage via a tool inserted into a breakout opening in a slashface of the platform.

Abstract: Systems and methods for handling autonomous vehicle faults are provided. A system includes a plurality of function nodes arranged in a directed graph architecture. The function nodes include a plurality of detector nodes and a plurality of fault handler nodes. Each detector node is communicatively connected to at least one function node and an associated fault handler node. The detector node is configured to obtain output from the function node, detect a fault, and provide a fault event to the associated fault handler node. Each fault handler node can be associated with a fault severity and a corresponding vehicle action. The associated fault handler node can receive the fault event from the detector node and initiate a fault response. The fault response can include initiating a respective vehicle action in response to the fault.

Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and extending in a chord-wise direction between a leading edge and a trailing edge, and also extending radially between a root and a tip. A tip rail including at least one tip cooling cavity can project from the tip, and cooling holes can be provided in the tip rail.

Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail at the tip. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.

Abstract: Described is a detection device, a head-up display (HUD) and a method for operating a HUD. The detection device, the HUD and the method for operating an HUD are designed to protect an imager of the HUD from damage by incident radiation and to avoid or at least significantly reduce a glare effect of the HUD. The detection device comprises an optical element with a reflecting area and a passband, where the optical transparency of the passband is greater than the optical transparency of the reflecting area. The passband is completely enclosed by the reflecting area, the surface of the passband is smaller than the surface of the reflecting area, and the detection device is optically coupled to the passband. The detection device determines the intensity of a radiation incident on the detection device.

Abstract: An apparatus and method for cooling an airfoil or engine component can include an outer wall defining an interior. A cooling circuit can be provided in the interior for directing flow of fluid and defining a flow direction. A plurality of cooling conduits can be arranged in the cooling circuit and organized into two or more sets of rows.

Abstract: A method of securing a modulation range of a wavelength-variable radiation source as part of the measurement of an absorption line of a substance comprises: the radiation source being controlled to transmit radiation such that the wavelength of the radiation runs through the modulation range in accordance with a time pattern; the radiation being filtered by means of a filter in whose pass band the absorption line is disposed and which has at least one filter flank whose actual wavelength is within the modulation range; a spectrum of the filtered radiation being determined in that the intensity of the filtered radiation is detected with respect to the time pattern; and a determination being made whether the spectrum has the at least one filter flank.

Abstract: A tip cooling apparatus for a turbine airfoil includes: a tip cap; a pair of spaced-apart tip walls connected to, extending around, and projecting outwardly from the tip cap so as to surround a central portion of the tip cap; a pocket defined by the tip walls; at least one feed hole passing through the tip cap or tip walls, communicating with the pocket; and a cooling matrix disposed in the pocket, the cooling matrix being an organized structure including an inlet surface having a plurality of inlets communicating with the pocket, and an outlet surface having a plurality of outlets, and further comprising a plurality of interior passages interconnecting the inlets to the outlets, with no line-of-sight therebetween.

Abstract: Described is an optical system and method for operating an HUD. The optical system includes an imaging system that generates optical radiation based on image information, a display system that projects the optical radiation, a deflection device that deflects the projected optical radiation, and at least one optically transparent pane-shaped element that at least partially reflects the deflected optical radiation. The deflection device guides the projected optical radiation onto the pane-shaped element, the optical radiation hitting the pane-shaped element at an angle. The imaging system, the display system, the deflection device and the pane-shaped element are arranged to generate a virtual image of optical radiation containing the image information. The optical system includes first and second edge points of the pane-shaped element. The first edge point has a minimal distance (dmin(1)) to the deflection device and the second edge point has a minimal distance (dmin(2)) to the imaging system.

Abstract: An airfoil for a turbine engine can include an outer wall bounding an interior and extending in a chord-wise direction between a leading edge and a trailing edge, and also extending radially between a root and a tip. A tip rail including at least one tip cooling cavity can project from the tip, and cooling holes can be provided in the tip rail.

Abstract: A rotary flow forming apparatus for producing light alloy rims contains a main spindle with a clamping apparatus for a rim blank. An outer pressure roller is provided and is deliverable radially from the outside in and is movable parallel to the spindle axis, for producing an outer contour of the light alloy rim. The apparatus does not require massive internal dies and thereby significantly reduces the production costs and significantly improves the efficiency of rim production, which is achieved by the fact that the rotary flow forming apparatus has an inner pressure roller for generating an inner contour of the light alloy rim, which is arranged in the region of the inner side of the rim blank opposite the outer pressure roller and is mounted so as to be movable parallel to the spindle axis, rotatable, and deliverable radially from the inside outward to the rim blank.

Abstract: An apparatus and method for cooling an airfoil or engine component can include an outer wall defining an interior. A cooling circuit can be provided in the interior for directing flow of fluid and defining a flow direction. A plurality of cooling conduits can be arranged in the cooling circuit and organized into two or more sets of rows.

Abstract: A method for making a cooled component for a turbine engine includes casting an airfoil assembly having an airfoil with an airfoil cooling passage and extending from a platform with at least one platform cooling passage, and forming a connecting passage between the airfoil cooling air passage and the platform cooling air passage.

Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.

Abstract: An apparatus and method for cooling an airfoil tip for a turbine engine can include an airfoil, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the airfoil at the tip. A plurality of cooling holes can be provided in the tip rail at the tip. A flow of cooling fluid can be provided through the cooling holes from the interior of the airfoil to cool the tip of the airfoil.

Abstract: Described is an arrangement for the transformation of laser radiation. A projection system for generating spatially modulated laser radiation includes an optical arrangement for transforming laser radiation, a field lens, a spatial light modulator and a projection arrangement. By means of the optical arrangement, incidental laser radiation in a first direction (E) is reflected on an aspherically curved, reflective surface in a second direction (R), where in a plane perpendicular to the first direction (E) the laser radiation has an inhomogeneous beam profile (GB1, G2) with a first beam axis (A) and a second beams axis (B) perpendicular to the latter, and the aspherical curvature is designed, during the reflection on the reflective surface, to transform the inhomogeneous beam profile of the laser radiation for the first beam axis (A) and/or the second beam axis (B) respectively into a homogenous top-hat beam profile (H).

Abstract: The invention relates to a method of determining the concentration of a gas component comprising the steps: generating and guiding a light beam having a wavelength variable in a wavelength range through a measurement volume in which the gas component having an absorption in the wavelength range is present; tuning the wavelength range; detecting the intensity of the light beam after passage through the measurement volume; storage of measurement points during the tuning that respectively consist of a point in time and an associated intensity value, to obtain a direct absorption line; generating an artificial measurement curve from the stored measurement points by shifting the measurement points on the time axis; wherein the shift takes place so that an artificial modulation results in the wavelength time extent; and evaluating the artificial measurement curve in accordance with the method of the wavelength modulation spectroscopy and determining a first concentration value therefrom.