Abstract:
Various methods and systems are provided for an engine with an exhaust gas treatment system. In one example, under a first condition, a first fuel is delivered for combustion in the engine. Under a second condition, a second fuel is delivered for combustion in the engine, the second fuel different than the first fuel. Under a third condition, the first fuel is delivered as a reductant for the exhaust gas treatment system.
Abstract:
A cryogenic fuel storage system 10 for an aircraft is disclosed including a cryogenic fuel tank 22 having a first wall 23 forming a storage volume 24 capable of storing a cryogenic liquid fuel 12; an inflow system 32 capable of flowing the cryogenic liquid fuel 12 into the storage volume 24; an outflow system 30 adapted to deliver the cryogenic liquid fuel 12 from the cryogenic fuel storage system 10; and a vent system 40 capable of removing at least a portion of a gaseous fuel 19 formed from the cryogenic liquid fuel 12 in the storage volume 24.
Abstract:
A cryogenic fuel storage system 10 for an aircraft is disclosed including a cryogenic fuel tank 22 having a first wall 23 forming a storage volume 24 capable of storing a cryogenic liquid fuel 12; an inflow system 32 capable of flowing the cryogenic liquid fuel 12 into the storage volume 24; an outflow system 30 adapted to deliver the cryogenic liquid fuel 12 from the cryogenic fuel storage system 10; and a vent system 40 capable of removing at least a portion of a gaseous fuel 19 formed from the cryogenic liquid fuel 12 in the storage volume 24.
Abstract:
Novel salts of rosuvastatin and processes for their preparation are disclosed. Pharmaceutical compositions comprising a therapeutically effective amount of one or more salts of rosuvastatin selected from the group consisting of a barium salt, strontium salt, zinc salt, cesium salt, cadmium salt and mixtures thereof are also disclosed.
Abstract:
A dual fuel propulsion system 100 is disclosed including a gas turbine engine 101 capable of generating a propulsive thrust using a cryogenic liquid fuel 1 12. A method of operating an aircraft engine 101 is disclosed using a selected proportion of a first fuel 1 1 and a second fuel 12 during selected portions of a flight profile 120 to generate hot gases that drive a gas turbine engine 101.
Abstract:
An engine (100) contains a compressor stage (101), a pulse detonation combustion stage (105) and a turbine stage (103). The pulse detonation combustion stage contains at least one pulse detonation combustor (109) which has an inlet portion (111). The pulse detonation combustor is oriented longitudinally and/or tangentially with respect to a centerline of the engine. A plenum (115), a casing (107), a diffuser (119) and a shroud (113) can be added in this combustion stage to achieve better performances.
Abstract:
The present invention provides novel intermediates of tadalafil and processes for their preparation. The present invention also provides for the preparation of tadalafil or a pharmaceutically acceptable salt or solvate thereof using the intermediates.
Abstract:
The present invention provides novel crystalline forms of a.lfuzosin and alfuzosin hydrochloride and processes for their preparation. Also provided are pharmaceutical compositions containing the new crystalline forms.
Abstract:
Novel salts of rosuvastatin and processes for their preparation are disclosed. Pharmaceutical compositions comprising a therapeutically effective amount of one or more salts of rosuvastatin selected from the group consisting of a barium salt, strontium salt, zinc salt, cesium salt, cadmium salt and mixtures thereof are also disclosed.
Abstract:
A substantially pure dextrorotatory isomer of zopiclone or a pharmaceutically acceptable salt thereof and crystalline forms thereof are provided. Also provided is a process for its preparation and pharmaceutical compositions containing same.