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Engine inlet distortion complications have plagued the turbine engine development community for decades, and engineers have developed countless methods to identify and combat the harmful effects of inlet distortion. One such type of distortion that has gained much attention in recent years is known as inlet swirl, which results in a significant flow angularity at the face of the engine. This flow angularity can affect the pressure rise and flow capacity of the fan or compressor, and subsequently affect compressor and engine performance. Previous modeling and simulation efforts to predict the effect inlet swirl can have on fan and compressor performance have made great strides, yet still leave a lot to be desired. In particular, a one-dimensional parallel compressor model called DYNTECC (Dynamic Turbine Engine Compressor Code) has been used to analyze the effects of inlet swirl on fan and performance operability of the Honeywell F109 turbofan engine. However, when compared to experimental swirl data gathered at the United States Air Force Academy (USAFA), the model predictions were found to be inaccurate. This paper documents work done to compare the initial predictions generated by DYNTECC to the latest set of experimental swirl data, analyze the potential shortcomings of the initial model, and modify the existing model to more accurately reflect test data. Extensive work was completed to create a methodology that can calibrate the model to existing clean inlet fan map data. In addition, an in depth study of fan/compressor stalling criteria was conducted, and the model was modified to use an alternate stalling criteria that more accurately predicted the point of stall for various swirl inlet conditions. The prediction of the fan stall pressure ratio for all inlet swirl conditions tested is within 2% of the ground test stall point at the same referred fan speed and referred mass flow.

The SpaceCube™ v2.0 system is a high performance, reconfigurable, hybrid data processing system that can be used in a multitude of applications including those that require a radiation hardened and reliable solution. This paper provides an overview of the design architecture, flexibility, and the advantages of the modular SpaceCube v2.0 high performance data processing system for space applications.

This paper details the design architecture, design methodology, and the advantages of the SpaceCube v2.0 high performance data processing system for space applications. The purpose in building the SpaceCube v2.0 system is to create a superior high performance, reconfigurable, hybrid data processing system that can be used in a multitude of applications including those that require a radiation hardened and reliable solution. The SpaceCube v2.0 system leverages seven years of board design, avionics systems design, and space flight application experiences. This paper shows how SpaceCube v2.0 solves the increasing computing demands of space data processing applications that cannot be attained with a standalone processor approach.

A Ni(II)-binding serpin, pNiXa, is abundant in Xenopus oocytes and embryos. Kinetic assays show that purified pNiXa strongly inhibits bovine α-chymotrypsin (K i = 3 mM), weakly inhibits porcine elastase (K 1 = 0.5 μM), and does not inhibit bovine trypsin. The reversible, slow-binding inhibition of α-chymotrypsin by pNiXa is unaffected by Ni(II). Ovochymase in egg exudates is inhibited by pNiXa, but to a limited extent, even at high pNiXa concentrations. An octadecapeptide that models the His-rich domain (-HRHRHEQQGHHD-SAKHGH-) of pNiXa forms six-coordinate, octahedral Ni(II)-complexes when the N-terminus is acetylated, and a square-planar Ni(ll)-complex when the N-terminus is unblocked. Spectroscopy reveals two distinct types of octahedral Ni(II)-coordination to the N-acetylated octadecapeptide, involving, respectively, 3-4 and 5-6 imidazole nitrogens ; the octadecapeptide undergoes partial, reversible precipitation in pH- and Ni(II)-dependent fashion, suggesting an insoluble, Ni(II)-doupled (Hx) n -dimer. Such (Hx) n -peptide interaction is confirmed by an enzyme-linked biotin-avidin assay with N-biotin-KHRHRHE-amide and N-acetyl-KHRHRHE-resin beads, which become coupled after adding Ni(II) or Zn(II). H 2 O 2 oxidation of 2'-deoxyguanosine to mutagenic 8-hydroxy-2'-deoxyguanosine is enhanced by the octahedral Ni(II)-octadecapeptide complex, although the effect is more intense with the square-planar Ni(II)-octadecapeptide complex. Immunoperoxidase staining of whole mounts with pNiXa antibody shows that pNiXa is distributed throughout gastrula-stage embryos and is localized during organogenesis in the brain, eye, spinal cord, myotomes, craniofacial tissues, and other sites of Ni(II)-induced anomalies. Patterns of pNiXa staining are similar in controls and Ni(II)-exposed embryos. Binding of Ni(II) to pNiXa may cause embryotoxicity by enhancing oxidative reactions that produce tissue injury and genotoxicity. Although the natural target proteinases for pNiXa inhibition have not been established, pNiXa may be an important regulator of proteolysis during embryonic development.

The localization of metallothionein in control and Zn-exposed embryos of Xenopus laevis was studied by whole-mount immunohistochemical staining. The embryos were grown according to the FETAX (Frog Embryo Teratogenesis Assay: Xenopus) protocol from N/F stage 8 to stage 47, with or without addition of ZnCl2 (300 microM) to the medium. At stages 27, 38, 42, 45 and 47, control and Zn-exposed embryos were fixed in buffered formalin, and whole mounts were stained by an immunoperoxidase technique, using monoclonal murine antibody to equine metallothionein. Staining of metallothionein was evident in myotomal cell nuclei of developing somites by stage 27, stomatodeum, oropharynx, and gills by stage 38, developing kidneys (mesonephros) by stage 45, and liver by stage 47. The staining of metallothionein at these sites was more intense in Zn-exposed embryos than controls. The central nervous system (especially the spinal cord) and the yolk mass were faintly stained for metallothionein in controls and Zn-exposed embryos. Staining of metallothionein in myotomal cell nuclei was most prominent at stage 38, diminished at stages 42 and 45, and practically disappeared by stage 47. This is the first report that metallothionein is expressed in myotomal cell nuclei of Xenopus embryos during normal somitogenesis and becomes increased when the embryos are exposed to teratogenic levels of Zn2+.

The integration of the airframe and its propulsion system is a key design issue in the development and deployment of military aircraft. The external airframe and inlet system must capture flow from the freestream and deliver it to the installed engine at Mach numbers commensurate with fan or compressor requirements. During aircraft maneuvers, the airflow to the engine becomes non-uniform or distorted. The aircraft developer and engine manufacturer must consider the compatibility of the inlet and the engine throughout the design process. The objective of the effort reported in this paper was to demonstrate an improved integrated test and evaluation (IT&E) capability that combines propulsion system numerical simulations (inlet-engine unsteady 3D aerodynamic codes) into the current test and evaluation process. The primary concern is to identify how to enhance the existing engine-inlet compatibility analysis and design methodology (ARP-1420) through the use of modeling and simulation (M&S) that integrates the aircraft and the propulsion system in a single computation process domain for the purpose of identifying system level improvements.