Abstract: A highly accurate non-invasive prenatal testing methodology that allows accurate fetal rhesus determination and fetal DNA fraction measurement in a single assay is provided. The disclosed testing may be administered as early as at week 10 of pregnancy and can be conveniently combined with prenatal genetic disease testing and detection.

Abstract: In some implementations, a credit decision platform may receive a credit request from an applicant and obtain domestic historical data associated with the applicant from a credit bureau device. The credit decision platform may obtain access to an email account associated with the applicant based on determining that the domestic historical data associated with the applicant is insufficient to process the credit request. The credit decision platform may identify, using one or more machine learning models, a set of email messages included in the email account that are relevant to the credit request and may analyze content included in the set of email messages to generate non-domestic historical data associated with the applicant. The credit decision platform may generate a decision on the credit request based on an estimated creditworthiness of the applicant, which may be determined based on the non-domestic historical data.

Abstract: A highly accurate non-invasive prenatal testing methodology that allows accurate fetal rhesus determination and fetal DNA fraction measurement in a single assay is provided. The disclosed testing may be administered as early as at week 10 of pregnancy and can be conveniently combined with prenatal genetic disease testing and detection.

Abstract: A method is provided for separating CO2 from an exhaust gas flow of a combustion process. The method includes: compressing the gas flow and cooling the compressed gas flow. The method also includes feeding the cooled gas flow to a swirl nozzle and separating the CO2 from the gas flow in the swirl nozzle. The method also includes discharging the CO2 which is separated in the swirl nozzle from the swirl nozzle for separate further treatment. A CO2 separating device is also provided that separates CO2 from an exhaust gas flow of a combustion process that operates with fossil fuels. The device includes a swirl nozzle which is exposed to through-flow of the gas flow, a compressor located upstream or downstream of the swirl nozzle, and a plurality of cooling devices which are provided upstream of the swirl nozzle for cooling of the gas flow which comes from the compressor.

Abstract: A burner arrangement is provided including a swirl-generating premix burner for providing a fuel/air mixture produced with a first fuel as well as a mixing pipe adjoining the premix burner downstream thereof and extending into a combustion chamber. In the case of such a burner arrangement, safer operation with highly reactive, in particular H2-rich fuel is achieved by the mixing pipe having a constriction downstream of the outlet of the swirl generator, and by a feeder for spraying in the highly reactive, in particular H2-rich fuel being arranged at the level of the constriction.

Abstract: A combustion chamber (1), in particular in a gas turbine, has at least two burners (A-H) that are connected to a fuel supply (3) via controllable fuel valves (2? and 2). Each burner (A to H) is assigned at least one optical measuring device (4) for detecting chemiluminescent radiation, and the combustion chamber (1) is assigned a pressure sensor (7) for detecting a combustion chamber pressure. The optical measuring device (4) and the pressure sensor (7) are connected to a computing and control device, which calculates a correlation value from the incoming measured values. A high correlation value signifies that the associated burner is prone to pulsation. The computing and control device (6) is designed in such a way that it determines the burner or a burner group with the highest correlation and controls the associated fuel valve(s) in such a way that more fuel is fed to the respective burner or the respective burner group, and the pulsation tendency thereof is thereby reduced.

Abstract: A method is provided for separating CO2 from an exhaust gas flow of a combustion process. The method includes: compressing the gas flow and cooling the compressed gas flow. The method also includes feeding the cooled gas flow to a swirl nozzle and separating the CO2 from the gas flow in the swirl nozzle. The method also includes discharging the CO2 which is separated in the swirl nozzle from the swirl nozzle for separate further treatment. A CO2 separating device is also provided that separates CO2 from an exhaust gas flow of a combustion process that operates with fossil fuels. The device includes a swirl nozzle which is exposed to through-flow of the gas flow, a compressor located upstream or downstream of the swirl nozzle, and a plurality of cooling devices which are provided upstream of the swirl nozzle for cooling of the gas flow which comes from the compressor.

Abstract: A combustion chamber (1), in particular in a gas turbine, has at least two burners (A-H) that are connected to a fuel supply (3) via controllable fuel valves (2? and 2). Each burner (A to H) is assigned at least one optical measuring device (4) for detecting chemiluminescent radiation, and the combustion chamber (1) is assigned a pressure sensor (7) for detecting a combustion chamber pressure. The optical measuring device (4) and the pressure sensor (7) are connected to a computing and control device, which calculates a correlation value from the incoming measured values. A high correlation value signifies that the associated burner is prone to pulsation. The computing and control device (6) is designed in such a way that it determines the burner or a burner group with the highest correlation and controls the associated fuel valve(s) in such a way that more fuel is fed to the respective burner or the respective burner group, and the pulsation tendency thereof is thereby reduced.

Abstract: In an atomizer device for the production of a liquid-gas mixture (4), the mixture (4) is introduced, particularly for compression, into a nozzle arrangement (3) in which the kinetic energy of the mixture (4) is in large part converted into compression energy by a pressure rise of the air. The atomizer device (2) includes a central air feed (16) and a nozzle chamber (18) for the supply of liquid surrounding the air feed. At or in the atomizing device, means (17) are arranged in the nozzle chamber for producing a swirled liquid flow in the nozzle chamber (18), and the swirled liquid flow emerges via a nozzle aperture (19) surrounding the air feed.

Abstract: In a method and a device for intermediate cooling during compression in a gas turbine system, the gas turbine system includes at least one first (1) and one second compressor (2), a combustion chamber (3), and a turbine (4). At least one intermediate cooler (9) is located between the first (1) and second compressor (2). The intermediate cooling takes place at least in part or for the most part isentropically.

Abstract: In an atomizer device for the production of a liquid-gas mixture (4), the mixture (4) is introduced, particularly for compression, into a nozzle arrangement (3) in which the kinetic energy of the mixture (4) is in large part converted into compression energy by a pressure rise of the air.

Abstract: In a method and a device for intermediate cooling during compression in a gas turbine system, the gas turbine system comprises at least one first (1) and one second compressor (2), a combustion chamber (3), and a turbine (4). At least one intermediate cooler (9) is located between the first (1) and second compressor (2). The intermediate cooling takes place at least in part or for the most part isentropically.

Abstract: In a combustion device (10), particularly for driving gas turbines, comprising a plurality of burners (12, . . . , 15) of identical thermal power output, which work parallel to an axis (28) into a common combustion chamber (11), an effective suppression of thermoacoustic combustion instabilities is achieved in a simple way in that the burners (12, . . . , 15) are designed differently from one another in such a way that the flames (24, . . . , 27) or flame fronts generated by them are positioned so as to be distributed along the axis (28).

Abstract: In a combustion device (10), particularly for driving gas turbines, comprising a plurality of burners (12, . . . , 15) of identical thermal power output, which work parallel to an axis (28) into a common combustion chamber (11), an effective suppression of thermoacoustic combustion instabilities is achieved in a simple way in that the burners (12, . . . , 15) are designed differently from one another in such a way that the flames (24, . . . , 27) or flame fronts generated by them are positioned so as to be distributed along the axis (28).

Abstract: In a combustion apparatus (10), in particular for driving gas turbines, in which combustion apparatus (10) a gaseous fuel in a burner (11) is sprayed through a plurality of separate fuel-injection devices (15, 16) into a gas flow containing combustion air, and the resulting mixture flows into a combustion chamber (12) for combustion and burns there, the acoustic impedance or stiffness of the fuel-injection devices (15, 16) is selected to be different in order to avoid thermoacoustic combustion instabilities.

Abstract: In a combustion device (10), particularly for driving gas turbines, comprising a plurality of burners (12, . . . , 15) of identical thermal power output, which work parallel to an axis (28) into a common combustion chamber (11), an effective suppression of thermoacoustic combustion instabilities is achieved in a simple way in that the burners (12, . . . , 15) are designed differently from one another in such a way that the flames (24, . . . , 27) or flame fronts generated by them are positioned so as to be distributed along the axis (28).