propelling nozzle वाक्य
उदाहरण वाक्य
मोबाइल
- The exhaust is ejected through a propelling nozzle, generating thrust.
- The propelling nozzle provides a relatively small proportion of the thrust generated by a turboprop.
- Propelling nozzles accelerate the available gas to convergent-divergent ( C-D ).
- Further expansion of the gases occurs in the propelling nozzle, where the gases exhaust to atmospheric pressure.
- Consequently, even at cruise flight speeds, the cold ( or mixed final ) propelling nozzle is unchoked.
- The turbine exit gases still contain considerable energy that is converted in the propelling nozzle to a high speed jet.
- A "'propelling nozzle "'converts a gas turbine or gas generator into a jet engine.
- The specification for the aircraft required engine installations which permitted the fitting of different air intakes, engines and propelling nozzles.
- The propulsion system consisted of the intake, engine, nacelle or secondary airflow and ejector nozzle ( propelling nozzle ).
- As well as supplying air to the engine, the intake also supplied air through the ramp bleed to the propelling nozzle.
- The fundamental performance task for a single shaft turbojet is to match the operation of the compressor, turbine and propelling nozzle.
- Matching may be defined as designing, sizing, and manipulating the operating characteristics of the compressor, turbine and propelling nozzle.
- Turbojets consist of an inlet, a compressor, a combustor, a turbine ( that drives the compressor ) and a propelling nozzle.
- According to the type of engine, it is discharged into the atmosphere through an exhaust pipe, flue gas stack, or propelling nozzle.
- The most efficient atmospheric pressure at which a conventional propelling nozzle works is set by the geometry of the SSTO engine must use a single set of nozzles.
- Turbofan engines may have an additional and separate propelling nozzle which produces a high speed propelling jet from the energy in the air that has passed through the fan.
- For example, the way the compressor operates is determined by the flow resistances behind it, which occur in the combustor, turbine, tailpipe and propelling nozzle.
- In addition, the flow resistance seen by the compressor is determined by the two restrictors downstream, namely the turbine nozzle area and the propelling nozzle exit area.
- The propelling nozzle at speeds above about Mach 2 usually has extra internal thrust losses because the exit area is not big enough as a trade-off with external afterbody drag.
- Most of the compressor bleed was required for cooling the afterburner duct and propelling nozzle and the remainder was used, together with the turbine exhaust, to burn the afterburner fuel flow.
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