Abstract: A gas turbine engine includes a fan, a nacelle arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow from the fan. A nozzle associated with the fan bypass passage is operative to control the bypass airflow. The nozzle includes a shape memory material having a first solid state phase that corresponds to a first nozzle position and a second solid state phase that corresponds to a second nozzle position.

Abstract: The present disclosure shows, unexpectedly, that variations in cell culture performance in large-scale cell culture systems such as, for example, those used in commercial manufacturing processes, in some instances, can be attributed to often subtle variations among shear-protectant additives used during cell culture. Assessing the quality of shear-protective additives using such large-scale systems, however, is inaccurate, time-consuming and costly. To solve the problem identified, the present disclosure provides methods and compositions for evaluating the suitability of shear-protectant additives without resorting to large scale cell growth and/or protein production tests.

Abstract: A gas turbine engine (10) includes a fan (14), a nacelle (28) arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage (30) downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow (1) from the fan. A nozzle (40) associated with the fan bypass passage is operative to control the bypass airflow. The nozzle includes a shape memory material having a first solid state phase that corresponds to a first nozzle position and a second solid state phase that corresponds to a second nozzle position.

Abstract: In one aspect, the disclosure provides methods for using NMR and NIR to evaluate biological samples. In some embodiments, the methods include a step of performing a Nuclear Magnetic Resonance (NMR) analysis on a sample to obtain an NMR spectrum, a step of performing a Near Infrared Spectroscopy (NIR) analysis on the sample to obtain an NIR spectrum, and/or a step of performing a data fusion analysis to evaluate the NIR spectrum.

Abstract: An object-oriented query to retrieve data from a data source stored on a data storage device connected to a computer is processed. One implementation involves receiving a Java Query Language (JQL) user query, compiling the JQL query using a Java compliant compiler, and detecting any compilation error due to a syntax error in the JQL query. If a compilation error is detected, then informing the user of the compilation error such that the user may correct the syntax error in the JQL query. Otherwise if a compilation error is not detected, then processing the JQL query for execution.

Abstract: A gas turbine engine includes a core engine having a compressor section fluidly connected to a combustor section that is also fluidly connected to a turbine section. A core nacelle surrounds the core engine and includes a core nozzle. A fan is connected to the compressor section and is arranged upstream from the core engine. A gear train interconnects the turbine section to the fan. A fan nacelle at least partially surrounds the core nacelle and includes a fan nozzle. The fan is disposed in the fan nacelle. At least one of the fan nozzle and core nozzle includes circumferentially fixed chevrons that provide a fixed exit area throughout engine operation.

Abstract: A system for minimizing non-integral vibrations in rotor blades located in a compressor section of a gas turbine engine includes a casing having a plurality of bleed slots, at least one of the bleed slots being located in close proximity to a row of rotor blades, a plurality of structural ligaments, at least one of the structural ligaments extending between two adjacent ones of the bleed slots; and a channel for reducing the height of at least one of the structural ligaments so as to minimize the non-integral vibrations in the rotor blades in the row.

Abstract: A liner assembly for an aircraft engine housing includes a noise attenuation structure that is covered by a face sheet. The face sheet covering the noise attenuation structure includes a surface having a plurality of circumferentially spaced apart acoustic energy absorption areas that are interspersed between a corresponding plurality of acoustic energy reflective areas. The acoustic energy reflective areas scatter higher order acoustic modes into a plurality of lower order modes. The difficult to attenuate lower order acoustic modes produced by the various acoustic energy cancel each other out to provide significant improvement in liner noise reduction efficiency.

Abstract: An exemplary geared turbomachine assembly includes an acoustic treatment that is in an unducted area of a geared turbomachine.

Abstract: An exemplary geared turbomachine assembly includes an acoustic treatment that is in an unducted area of a geared turbomachine.

Abstract: A propfan assembly includes a plurality of blades that each include an internal cavity containing a noise attenuation structure. Acoustic energy is communicated to the internal cavity through a plurality of openings in the blade surfaces. The cavities include features for attenuating noise energy to reduce generation of noise emitted from the propfan assembly.

Abstract: An object-oriented query to retrieve data from a data source stored on a data storage device connected to a computer is processed. One implementation involves receiving a Java Query Language (JQL) user query, compiling the JQL query using a Java compliant compiler, and detecting any compilation error due to a syntax error in the JQL query. If a compilation error is detected, then informing the user of the compilation error such that the user may correct the syntax error in the JQL query. Otherwise if a compilation error is not detected, then processing the JQL query for execution.

Abstract: A gas turbine engine (10) includes a fan (14), a nacelle (28) arranged about the fan, and an engine core at least partially within the nacelle. A fan bypass passage (30) downstream of the fan between the nacelle and the gas turbine engine conveys a bypass airflow (1) from the fan. A nozzle (40) associated with the fan bypass passage is operative to control the bypass airflow. The nozzle includes a shape memory material having a first solid state phase that corresponds to a first nozzle position and a second solid state phase that corresponds to a second nozzle position.

Abstract: Prevention of Acute Renal Failure following myoglobinemia in cases of rhabdomyolysis by means of trapping myoglobin released to circulation following striated muscles injury using a temporary intravenous filter, hence prophylaxis of Acute Renal Failure, which commonly follows this situation. It is directed to all cases of rhabdomyolysis especially for “In situ prevention” in cases of disasters, crush injuries, and reperfusion injury in a limb.

Abstract: A propfan assembly includes a plurality of blades that each include an internal cavity containing a noise attenuation structure. Acoustic energy is communicated to the internal cavity through a plurality of openings in the blade surfaces. The cavities include features for attenuating noise energy to reduce generation of noise emitted from the propfan assembly.

Abstract: A liner assembly for an aircraft engine housing includes a noise attenuation structure that is covered by a face sheet. The face sheet covering the noise attenuation structure includes a surface having a plurality of circumferentially spaced apart acoustic energy absorption areas that are interspersed between a corresponding plurality of acoustic energy reflective areas. The acoustic energy reflective areas scatter higher order acoustic modes into a plurality of lower order modes. The difficult to attenuate lower order acoustic modes produced by the various acoustic energy cancel each other out to provide significant improvement in liner noise reduction efficiency.