Abstract: Processes for the preparation of an alpha polymorph of perindopril erbumine is provided comprising (a) forming a solution comprising perindopril erbumine in one or more ketones; (b) heating the solution to reflux; and (c) cooling the solution to a temperature sufficient to form the alpha polymorph of perindopril erbumine. The alpha polymorphs of perindopril erbumine obtained herein have a high purity level.

Abstract: Improved processes for the preparation of 3-hydroxy-3-methylglutaryl-coenzyme A (HMG-CoA) inhibitors, e.g., simvastatin, and their intermediates are provided. In one embodiment, a process for the preparation of a carboxylic acid amine salt of formula I is provided wherein R1 and R2 are as defined herein, the process comprising reacting lovastatin with an amine of formula III: in an aqueous medium to provide the carboxylic acid amine salt of formula I. The process further includes the steps of lithiating the carboxylic acid amine salt of formula I to form the corresponding 2,2-dimethylbutyrate intermediate of formula IIa lactonizing the 2,2-dimethylbutyrate intermediate (IIa) to provide simvastatin and pharmaceutically acceptable salts thereof. Also provided is an improved process for lactonization of the intermediates herein using peptide coupling reagents.

Abstract: A method for operating a gas turbine engine, including a first compressor, a second compressor, and a turbine, coupled together in serial flow arrangement. The method includes channeling compressed airflow discharged from the first compressor through an intercooler having a cooling medium flowing therethrough, operating the intercooler such that condensate is formed in the intercooler from the compressed airflow, and channeling the condensate to an inlet of the first or second compressor to facilitate reducing an operating temperature of the gas turbine engine.

Abstract: A system where heat energy is recovered from an intercooled gas turbine engine. This system comprises: (a) at least one gas turbine engine; (b) a compressed air stream that receives energy from the at least one gas turbine engine; (c) at least one intercooler that extracts the energy from the compressed air stream, and (d) at least one heating district. In this system, the at least one intercooler and the at least one heating district is connected by a fluid circulating loop to transfer the extracted energy from the at least one intercooler to the at least one heating district.. Another embodiment involves a method for controlling the ratio of heat energy to output shaft energy removed from an operating intercooled gas turbine engine, which comprises the step of: varying the amount of energy removed by at least one intercooler from a flowing gas stream of the gas turbine engine.

Abstract: An improved process for the preparation of pyrimidine derivatives is provided comprising reacting a Wittig reagent of the general formula wherein R is an alkyl of from 1 to 10 carbon atoms, aryl or arylalkyl, R1 is a substituted or unsubstituted hydrocarbon group, R2 and R3 are the same or different and are hydrogen or a substituted or unsubstituted hydrocarbon group; Z is sulfur, oxygen, sulfonyl, or imino which may be substituted by formyl, acetyl, propionyl, butyryl, isobutyryl, valeryl, isovaleryl, amino substituted by sulfonyl or alkylsulfonyl, and sulfonyl substituted by alkyl, amino or alkylamino and X is a halogen; with an aldehyde of the general formula wherein R4 is hydrogen, a lower alkyl or a cation capable of forming a non-toxic pharmaceutically acceptable salt and each R5 are the same or different and are hydrogen or a hydrolyzable protecting group, or each R5, together with the oxygen atom to which each is bonded, form a hydrolyzable cyclic protecting group, or each R5 is bonded to the

Abstract: A method for operating a gas turbine engine including a first compressor, a second compressor, a combustor and a turbine, coupled together in serial flow arrangement.

Abstract: Information storage devices are permanently deployed on individual components of turbine engines to permanently record operating, repair, and maintenance data on the parts that comprise the individual components. Ensuring that such data will not be lost when individual components or their parts are replaced in an engine, allows the use of life limited parts in turbine engines and improves their reliability. The information storage devices can be accessed to record maintenance or to record changes when repairs are done. They can also be attached to external circuitry for the purpose of analyzing, downloading or recording data remotely, allowing analysis of component operating, repair, and maintenance information.

Abstract: A gas turbine engine combustor can downstream of a pre-mixer has a pre-mixer flowpath therein and circumferentially spaced apart swirling vanes disposed across the pre-mixer flowpath. A primary fuel injector is positioned for injecting fuel into the pre-mixer flowpath. A combustion chamber surrounded by an annular combustor liner disposed in supply flow communication with the pre-mixer. An annular trapped dual vortex cavity located at an upstream end of the combustor liner is defined between an annular aft wall, an annular forward wall, and a circular radially outer wall formed therebetween. A cavity opening at a radially inner end of the cavity is spaced apart from the radially outer wall. Air injection first holes are disposed through the forward wall and air injection second holes are disposed through the aft wall. Fuel injection holes are disposed through at least one of the forward and aft walls.

Abstract: A method for operating a gas turbine engine including a compressor, combustor, and turbine is provided that includes channeling compressed airflow from the compressor to a heat exchanger having a working fluid circulating within, channeling the working fluid from the heat exchanger to a chiller, extracting energy from the working fluid to power the chiller, and directing airflow entering the gas turbine engine through the inlet chiller such that the temperature of the airflow is reduced prior to the airflow entering the compressor.