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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 is capable of providing a total compressor pressure ratio of over 20:1.
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.
Table 2 illustrates the effect of altitude on the compressor pressure ratio for a Voyager 550 type engine system, with an air vehicle mach number of .4.
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