Abstract: Described herein is a process for the total synthesis of macrolactones and macrolactams of formula I including E- and Z-configuration thereof, in particular, nannocystins.

Abstract: Compounds that inhibit HIF-2?, and compositions containing the compound(s) and methods for synthesizing the compounds, are described herein. Also described are the use of such compounds and compositions for the treatment of a diverse array of diseases, disorders, and conditions, including cancer- and immune-related disorders that are mediated, at least in part, by HIF-2?.

Abstract: A gas turbine engine includes a compressor delivering air into a combustion section. The combustion section and the compressor are housed in a housing. An air supply system communicates through the housing to deliver air from a location between an upstream end of the compressor, and an upstream end of the combustor. A diffuser is positioned downstream of the compressor. An opening in the housing supplies air to the inlet end. The diffuser has an outer shroud and an inner shroud with intermediate vanes. The outer shroud ends at a location upstream of a downstream end of the inner shroud at locations circumferentially aligned with the inlet end. The outer shroud only ends at the upstream location at circumferential locations associated with the inlet end, but extends further downstream at other locations.

Abstract: A method and system for implementing verification within data transfer are provided. The method includes obtaining a user card identifier and a data transfer password of a selected user card through a data transfer request interface. A data transfer verification request to a data transfer server is initiated, the data transfer verification request being generated according to the user card identifier, the data transfer password and a data transfer user identifier. A current time valid identifier that is returned by the data transfer server is received when the data transfer verification is passed, the current time valid identifier being issued when the data transfer server determines that the current time does not exceed a valid period of card-binding time of the selected user card. A secondary verification interface is skipped according to the current time valid identifier. A data transfer confirmation interface is entered.

Abstract: Disclosed herein are expression constructs and methods for producing a protein of interest. According to some examples, an expression construct includes a nucleotide sequence encoding a fusion protein. To produce the protein of interest, the expression construct is transformed into a host cell, which is cultured under conditions that allow the expression of the fusion protein. The fusion protein has at least one expression unit; each expression unit has, sequentially, an affinity tag moiety, a spacer moiety, an enzymatic cleavage site, and a protein of interest moiety. The fusion protein is isolated from the host cell, solubilized, and refolded. The refolded fusion protein is cleaved to release the protein of interest.

Abstract: A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case. At least one spoke includes a fluid passage that is in fluid communication with a channel on a radially inner end of the fluid passage. The channel is directed in a radially inward and circumferential direction. A cavity is located radially inward from the mid-turbine frame and is in fluid communication with the channel.

Abstract: A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90°. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.

Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.

Abstract: A method and system for implementing verification within data transfer are provided. The method includes obtaining a user card identifier and a data transfer password of a selected user card through a data transfer request interface. A data transfer verification request to a data transfer server is initiated, the data transfer verification request being generated according to the user card identifier, the data transfer password and a data transfer user identifier. A current time valid identifier that is returned by the data transfer server is received when the data transfer verification is passed, the current time valid identifier being issued when the data transfer server determines that the current time does not exceed a valid period of card-binding time of the selected user card. A secondary verification interface is skipped according to the current time valid identifier. A data transfer confirmation interface is entered.

Abstract: Described herein is a process for the total synthesis of macrolactones and macrolactams of formula I including E- and Z-configuration thereof, in particular, nannocystins.

Abstract: A turbine engine includes a frame assembly including an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A baffle within the outer cavity includes a plurality of openings for directing cooling airflow into the outer cavity for preventing impingement on a radially inner wall of the outer cavity for maintaining a desired temperature of the cooling air within the outer cavity.

Abstract: An axially extending outer case for a gas turbine engine comprises an arcuate case wall, an opening, a boss and contouring. The arcuate case wall has an inner surface and an outer surface. The opening extends through the arcuate case wall. The boss extends radially from the outer surface of arcuate case wall and surrounds the opening. The contouring surrounds the opening along the inner surface of the arcuate case wall within the boss.

Abstract: A turbine engine includes a frame assembly including an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A baffle within the outer cavity includes a plurality of openings for directing cooling airflow into the outer cavity for preventing impingement on a radially inner wall of the outer cavity for maintaining a desired temperature of the cooling air within the outer cavity.

Abstract: A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case. At least one spoke includes a fluid passage that is in fluid communication with a channel on a radially inner end of the fluid passage. The channel is directed in a radially inward and circumferential direction. A cavity is located radially inward from the mid-turbine frame and is in fluid communication with the channel.

Abstract: A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.

Abstract: The invention relates to video image compression technologies, and discloses a method and system for upsampling a spatial scalable coded video image so that during upsampling computation complexity may be reduced while coding performance is substantially unchanged. In the invention, the principle that human eyes are far less sensitive to a chrominance components than to a luminance components is utilized, and a simpler filter is adopted for the chrominance components than that for the luminance components during upsampling in I_BLINTRA_Base inter-layer prediction or residual samples image inter-layer prediction, thereby reducing effectively calculation complexity while coding performance is substantially unchanged.

Abstract: An axially extending outer case for a gas turbine engine comprises an arcuate case wall, an opening, a boss and contouring. The arcuate case wall has an inner surface and an outer surface. The opening extends through the arcuate case wall. The boss extends radially from the outer surface of arcuate case wall and surrounds the opening. The contouring surrounds the opening along the inner surface of the arcuate case wall within the boss.

Abstract: A bleed air supply system for a gas turbine engine comprising a duct having an inlet end and extending to an outlet end. The inlet end of the duct is provided with a central insert. In another feature, there may be a plurality of ducts, and inlet ends of the plurality of ducts being spaced by at least 90°. In another feature, a compressor may have a diffuser with a shroud ending upstream of the downstream end of an inner shroud, having an outer shroud ending at a location upstream of a downstream end of an inner shroud at locations circumferentially aligned with an inlet end of the duct.

Abstract: A stator assembly for a gas turbine engine is provided having an annular body, an inner gas path platform, a plurality of fairings, and at least one nozzle. The annular body has an outer gas path platform and a circumferentially extending annular cavity disposed radially outside of the outer gas path platform. The fairings extend radially between the inner gas path platform and the outer gas path platform. Each fairing includes a gas passage extending from the annular cavity through the inner gas path platform. The at least one nozzle has an inlet orifice disposed outside of the annular cavity and an exit orifice disposed within the annular cavity. The exit orifice is oriented within the annular cavity such that cooling air exiting the nozzle travels in a substantially circumferential direction within the annular cavity.