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The XE is a development of the Mosquito Air, with a cockpit fairing and a more sophisticated exhaust system, plus a rotor diameter increased by 40 cm (15.7 in) to support the higher gross weight. The aircraft was designed to comply with the US Experimental – Amateur-built and European microlight aircraft rules.
The Mosquito Air was designed to comply with the United States FAR 103 Ultralight Vehicles, including the category's maximum empty weight of 254 lb (115 kg). The aircraft has a standard empty weight of 254 lb (115 kg).
The Mosquito PR Mk.IX, 90 of which were built, was the first Mosquito variant with two-stage, two-speed engines to be produced in quantity; the first of these, LR405, first flew in April 1943. [153] The PR Mk.IX was based on the Mosquito B Mk.IX bomber and was powered by two 1,680 hp (1,250 kW) Merlin 72/73 or 76/77 engines.
The Solar T62 Titan is an American gas turbine engine used mainly as a aircraft auxiliary power unit (APU), conventional power generator, turboprop engine for fixed-wing aircraft or turboshaft engine for helicopters. A new turbine version was developed as the Solar T66.
LHTEC (Light Helicopter Turbine Engine Company) is a joint venture between Rolls-Royce and Honeywell. The company was originally a partnership between the Allison Engine Company and AlliedSignal Aerospace. [1] In 1995 Rolls-Royce acquired Allison, and AlliedSignal merged with Honeywell in 1999, and adopted its name.
Turboshaft engine with a maximum and normal power rating of 2,200 and 1,850 shp (1,640 and 1,380 kW) and a pressure ratio of 6:1; high-speed version of the T55-L-3 [21] allowed for use on the Chinook instead of the geared YT55-L-3 engine due to August 1958 engine contract modification, with the reduction gearing now provided in the helicopter ...
The propelling nozzle converts a gas turbine or gas generator into a jet engine. Power available in the gas turbine exhaust is converted into a high speed propelling jet by the nozzle. The power is defined by typical gauge pressure and temperature values for a turbojet of 20 psi (140 kPa) and 1,000 °F (538 °C). [18]
The Turmo was initially developed with a single-stage centrifugal compressor, annular combustion chamber and single stage turbine. Power output was from a single-stage free power turbine and was initially 200 kW (270 hp). [1] During early post-war helicopter development, the use of cold and hot rotor tip-jets was widely investigated. To provide ...