Article details

Title: New Constructive Solutions for Aircraft Turbojet Engine Combustion Chamber
Author(s): Constantin Rotaru   Mihai Mihăilă-Andres   Paul Renard         

Abstract: An additional combustion chamber placed in the inner part of the nozzle has the potential to increase the efficiency and the specific thrust of current gas turbine engines. This new constructive solution analyzed in the present paper introduces certain challenges concerning the injection, mixing, ignition and burning of fuel with a short residence time in a space characterized by large three-dimensional acceleration. The injection of the fuel into a primary combustion zone is examined having a low-speed flow field for mixing and flame holding. By extracting the flow stream after turbine in the inner nozzle, this solution could allow a lower engine rotational speed, a lower temperature in front of the first stage of the turbine and the use of the ceramic matrix composite in the high-pressure turbine.

Keywords: aircraft engine, combustion chamber, CFD

References:

[1] J.D. MATTINGLY – Elements of Propulsion: Gas Turbines and Rockets, American Institute of Aeronautics and Astronautics, Reston, VA, 2006
[2] J.D. MATTINGLY, W.H. HEISER, D.T. PRATT – Aircraft Engine Design, Second Edition, American Institute of Aeronautics and Astronautics, Reston, VA, 2002
[3] F. SHAUER, J. STUTRUD, R. BRADLEY – Detonation Initiation Studies and Performance Results from Pulsed Detonation Engine Applications, 39th AIAA Aerospace Sciences Meeting & Exhibit, 8-11 Jan. 2001, Reno, NV
[4] F. SHAUER, R. BRADLEY, J. HOKE – Interaction of a Pulsed Detonation Engine with a Turbine, 41st AIAA Aerospace Sciences Meeting & Exhibit, 8-11 Jan. 2001, Reno, NV