In a turbo-prop engine, the compressor pressure ratio is 6/1

In a turbo-prop engine, the compressor pressure ratio is 6/1 and the maximum cycle temperature is 760oC. The stagnation isentropic efficiencies of compressor and turbine are 85% and 88% respectively. The mechanical efficiency of the drive is 99%. The aircraft velocity is 725 km//h and it is at an altitude with ambient condition of temperature = -7oC. Taking intake direct efficiency of 90%. Neglecting the pressure loss in the combustion chamber and assuming that the gases in the turbine expand to atmospheric pressure leaving the aircraft at 725 km/h relative to the aircraft.

For product gases, (CP = 1.15 kJ/kg. K  &   γ=1.333) & For air, (CP =1.005 kJ/kg. K  &   γ=1.4)

Calculate;

(a) Specific power output

(b) Cycle efficiency

How Our Website Works

1. FILL IN OUR SIMPLE ORDER FORM

It has never been easier to place your order. Fill in the initial requirements in the small order form located on the home page and press “continue” button to proceed to the main order form or press “order” button in the header menu. Starting from there let our system intuitively guide you through all steps of ordering process.

2. PROCEED WITH THE PAYMENT

All your payments are processed securely through PayPal. This enables us to guarantee a 100% security of your funds and process payments swiftly.

3. WRITER ASSIGNMENT

Next, we match up your order details with the most qualified freelance writer in your field.

4. WRITING PROCESS

Once we have found the most suitable writer for your assignment, they start working on a masterpiece just for you!

5. DELIVERY

Once finished, your final paper will be available for download through your personal dashboard. You will also receive an email notification with a copy of your paper attached to it. Sometimes, the writer may leave a note for you about the order in case there is any additional information that they need to give you.

Leave a Reply

Your email address will not be published.