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A smaller displacement engine would typically require a higher manifold pressure which increases structural loading and impacts turbomachinery pressure ratio, size, and weight.
In addition, it is not uncommon for a Diesel engine to require a 40-60 PSIA manifold pressure (15-20 PSIA for turbocharged spark ignition) which impacts compressor pressure ratio requirements with a resulting substantial increase in turbomachinery size and weight.
The turbomachinery required for the previously described propulsion system supplies the proper inlet manifold pressure to the engine in order to maintain sea level power at altitude.
The engine can be flat rated from sea level to an altitude of 100,000 feet, providing adequate inlet air manifold pressure is maintained.
The number of stages required is dependent upon the total compressor pressure ratio which is influenced by three primary factors: ambient pressure, inlet manifold pressure, and system pressure losses which include heat exchanger and duct losses.
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