ZuoTi.Pro
Question

A single-spool turbofan engine has the following data Ambient temperature Ambient pressure BPR Overall pressure ratio Fan pressure ratio Fuel heating value Turbine inlet temperature Diffuser pressure recovery factor Compressor efficiency Fan efficiency Combustion efficien Burner pressure recovery factor Turbine efficiency Nozzle efficiency Flight Mach number 288 K 101.3 kN/m2 0.7 25 3.375 44,000 kJ/kg 2000 K 0.9 0.89 0.91 0.98 0.95 0.98 1.0 0.3 Calculate 1. 2. 3. Thrust per unit mass flow rate TSFC Thermal, propulsive and overall efficiencies

engineering   Mechanical-Engineering   
0 0
Add a comment Improve this question Transcribed image text
Next > < Previous
Sort answers by oldest

Homework Answers

Answer #1

2 1ntake 2Та 24 з 184 .K la 288 !!_fr.gfmpressor-ㄧㄧ·→Pa f2 LLe 3.37s 2c00 ー -0.028 T3-T2Date λ. 2qy1 YL S223.6

0 0
Add a comment
Know the answer?
Add Answer to:
A single-spool turbofan engine has the following data Ambient temperature Ambient pressure BPR Overall pressure ratio...
Your Answer:

Post as a guest

Your Name:

What's your source?

Earn Coins

Coins can be redeemed for fabulous gifts.

Log In

Sign Up

Not the answer you're looking for? Ask your own homework help question. Our experts will answer your question WITHIN MINUTES for Free.
Similar Homework Help Questions

  • Consider a turbofan engine with a bypass ratio of 6. The cruising Mach number is 0.85...

    Consider a turbofan engine with a bypass ratio of 6. The cruising Mach number is 0.85 at an altitude of 12000 m with an ambient temperature of 217 K. The ratio of stagnation pressure and ambient pressure for the fan and the core engine is 1.6. The stagnation temperature is 600 K at the exit of the core engine and 340 K at the exit of the fan. (a) If the fan and core streams expand in separate nozzles to...

  • 3.7 A simple twin-spoot turbofan is designed for a business jet. The cruise design point for a Ma...

    3.7 A simple twin-spoot turbofan is designed for a business jet. The cruise design point for a Mach number of 0-75 and altitude of 12 500 m (T, " 216.7 K, P.-0-1793 bar, a = 295.1 m/s) is as follows: 9-6 kg/s Airflow Bypass ratio Fan pressure ratio Compressor pressure ratio Turbine inlet temperature Polytropic efficiency (all) 1220K 0.90 Combustion pressure loss Compressor delivery pressure 5% Mechanical efficiencies Combustion efficiency Intake efficiency Nozzle efficiencies 0.99 0-98 0-96 1-00 Separate exhausts...

  • . A turbofan aircraft engine is flying at 720 km/h at an altitude of 6100 m,...

    . A turbofan aircraft engine is flying at 720 km/h at an altitude of 6100 m, where the ambient conditions are 50 kPa and -12°C (a negative value). The pressure ratio across the compressor is 13, and the turbine inlet temperature (TIT) is 1330 K. Assuming ideal operation for all components and constant specific heats for the air at room temperature (cold air model). (a) Sketch the T-s diagram of the cycle, and determine: (b) The Mach number of the...

ADVERTISEMENT
Free Homework Help App
Download From Google Play
Scan Your Homework
to Get Instant Free Answers
Need Online Homework Help?
Ask a Question
Get Answers For Free
Most questions answered within 3 hours.
ADVERTISEMENT
ADVERTISEMENT
ADVERTISEMENT