Week_11_recitation - properties at various states. For a...

Info iconThis preview shows page 1. Sign up to view the full content.

View Full Document Right Arrow Icon
Week 11 Recitation Bullet items Gas turbines, turbojets, turbofan, etc. The Brayton cycle and cycle modifications regeneration, reheat heat and intercooling. Using p-v and T-s diagrams, process paths The gas turbine and steam combined cycle Recitation Problem 1. A turbojet engine can be modified to obtain extra thrust by adding an afterburner between the turbine exhaust and the nozzle, as shown below. In the afterburner, fuel (heat) is added to and burned in the turbine exhaust gases at constant pressure. Assume that the working fluid is air with constant specific heats. Treat all processes as internally reversible, treat the compressor, turbine, and nozzle as isentropic, and the combustor and afterburner as constant pressure. See diagram below for information about
Background image of page 1
This is the end of the preview. Sign up to access the rest of the document.

Unformatted text preview: properties at various states. For a plane flying at 100 m/s: a. Draw the T-s diagrams for this jet engine (including the afterburner). b. Find the total heat added in the afterburner, per mass air (in kJ/kg) c. Find the nozzle exit velocity (in m/s), assuming the gases are fully expanded to atmospheric pressure in the nozzle, and assuming the hot gases enter the nozzle at zero velocity. Neglect changes in ke except in the nozzle. Also find the exit velocity without afterburning. diffuser compressor T 2 = -33 C P 2 = 35 kPa 1 2 3 Q 34 P 3 = 571.55 kPa T 4 = 1500 K 4 5 Q 56 6 7 afterburner nozzle turbine combustor T 6 = 1500 . . T 1 = -37 C P 1 = 32.84 kPA...
View Full Document

Ask a homework question - tutors are online