Dear Aeronautical/space engineers why we are using Multistage compressor & Turbines in Gas turbine engine?
there limit pressure ratio 1 can obtain each disk of compressor action, each stage has have several turbines. overall ratio needed imply either first disk spin fast size, or last compressor spin effective if part of same stage , spinning @ same rate. dividing compressor 2 (and in cases 3) stages allows better tuning of compression effect, making engines more efficient.
compressors needing spin @ different rate comes need drive them turbines spinning @ different rates 1 another.
downside of multistage of course greater mechanical complexity.
dear aeronautical/mechanical engineers
multi-staging of compressor & turbines preferred nowadays in gas turbine engines turbofan,jet,shaft & turbo propeller....why cant single stage...what technical reason using multistage....what pros & cons of both two?
Cars & Transportation Aircraft Next
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