A booster assembly for a gas turbine engine having a first rotor assembly comprising a low pressure turbine drivingly connected to a fan via a first shaft and a second rotor assembly comprising a second turbine drivingly connected to a high pressure compressor via a second shaft. The first and second rotor assemblies are arranged to undergo relative rotation in use about a common axis. The booster assembly comprises a further compressor arranged to be disposed about said common axis between the fan and high-pressure compressor in a direction of flow and a gearing having first and second input rotors and an output rotor. The first input rotor is arranged to be driven by the first rotor assembly and the second input rotor is arranged to be driven by the second rotor assembly such that the output rotor drives the further compressor in dependence upon the difference in rotational speed between the first and second rotor assemblies.

A low emission, high efficiency Gas Turbine engine operating on a combination of Natural Gas and Bio Gas as fuel, driving either a high efficiency turbo-blower or a high efficiency Turbo Pump system combined with heat recovery systems and in other embodiments is provided a generator of electricity or providing evaporate cooling from using the remaining waste heat in the exhaust gas.

Methods are provided for creating a fluidic barrier between the core stream and the bypass stream in a turbofan engine. A method comprises compressing the bypass and core streams with a fan between an upstream splitter and a downstream splitter which divides the bypass and core streams, and imparting a first momentum into the air stream proximate the fan in a region between the core and bypass streams and the upstream and downstream splitters to form a fluid barrier, wherein the first momentum of the air stream in the region is higher than a second momentum of the air stream adjacent the fluid barrier.

A technical object of the present invention is to provide an annular injection apparatus for wet compression which enables sprayed droplets to maximally evaporate without being drained as condensate water, thereby reducing compression work of the compressor. To this end, the annular injection apparatus for wet compression according to the present invention is an annular injection apparatus for wet compression which is used for a compressor including a nose cone and a bell mouth in an inlet of a flow path, in which droplets are sprayed to a portion except for portions directed toward the nose cone and the bell mouth.

A booster assembly for a gas turbine engine having a first rotor assembly comprising a low pressure turbine drivingly connected to a fan via a first shaft and a second rotor assembly comprising a second turbine drivingly connected to a high pressure compressor via a second shaft. The first and second rotor assemblies are arranged to undergo relative rotation in use about a common axis. The booster assembly comprises a further compressor arranged to be disposed about said common axis between the fan and high-pressure compressor in a direction of flow and a gearing having first and second input rotors and an output rotor. The first input rotor is arranged to be driven by the first rotor assembly and the second input rotor is arranged to be driven by the second rotor assembly such that the output rotor drives the further compressor in dependence upon the difference in rotational speed between the first and second rotor assemblies.

A booster assembly for a gas turbine engine having a first rotor assembly comprising a low pressure turbine drivingly connected to a fan via a first shaft and a second rotor assembly comprising a second turbine drivingly connected to a high pressure compressor via a second shaft. The booster assembly comprises a further compressor arranged to be disposed about said common axis between the fan and high-pressure compressor in a direction of flow and a gearing having first and second input rotors and an output rotor. The first input rotor is arranged to be driven by the first rotor assembly and the second input rotor is arranged to be driven by the second rotor assembly such that the output rotor drives the further compressor in dependence upon the difference in rotational speed between the first and second rotor assemblies.

The invention relates to a trunnion (23) for a high-pressure turbine (11), to be arranged between a shaft of a low-pressure turbine (9) and an inner surface (34) of a seal mounting (26) of the low-pressure turbine (8), the trunnion (23) being characterized in that it includes a drop-launching extension (32) arranged such as to extend opposite a flared portion (33) of the inner surface (34) of the seal mounting (26), such that when the trunnion (23) is rotated about the shaft of the low-pressure turbine (9), oil (H2), which tends to penetrate between the trunnion (23) and the seal mounting (26), is thrown by centrifugal effect from the drop-launching extension (32) toward the flared portion (33) of the inner surface (34) of the seal mounting (26).

A gas turbine engine. The engine includes a first compressor coupled to a first turbine by a first shaft, the first turbine having first and second turbine stages. A first combustor is provided downstream of the first compressor and upstream of the first stage of the first turbine. A second combustor is provided downstream of the first stage of the first turbine, and upstream of the second stage of the first turbine. A further turbine is provided downstream of the first turbine, and is coupled to a further compressor by a further shaft.

A gas turbine engine for a small aircraft such as a UAV having a bypass flow with a variable area bypass nozzle located at an outlet of the bypass channel, the nozzle having one position with a maximum flow area and a second position with a minimal flow area. The compressor is a twin stream compressor with an inner flow path for compressed air to the combustor and an outer flow path for the bypass channel. A fan stage can be used in front of the compressor.

A turbofan engine has a fan portion in fluid communication with a core stream and a bypass stream of air separated by splitters disposed both upstream and downstream of the fan portion. A fluid passage is defined between the splitters. The turbofan engine has a plurality of high pressure fluid jets originating from the low pressure side of the fan blades, the jets restricting the migration of the core stream into the bypass stream through the fluid passage.