For an engine with an additional burner between the high pressure turbine (HPT station 5) and the low pressure turbine (LPT station 6), more energy can be added in the engine because the limiting condition is the maximum metal temperature T4. More heat can be added in the ITB at station 6 because the temperature of the gases are reduced by expansion through the HPT at station 5.

The concept of a business jet using ITB was analyzed. Such an aircraft would have several advantages:

• Increased power during critical mission points
• Reduced peak combustion temperatures for increaed turbine life/reduced cooling
• Possible reduction in Specific Fuel consumption
• Decreased NOx emissions

Initial system studies did not show benefit for subsonic transport cruise.

NASA has a Partnership with AFL and Williams International to study Supersonic Business Jet and UAV options.

So far, we have completed initial ITB flame-holder designs and obtained CFD results. We have also initiated facility design for ITB test rig.

Researchers:

Dan Bulzan