Calculating performance of gas turbine engine with embedded PDC (pulse detonation combustor)

Keeping in mind what has been done in Refs.3 through 6 on the performance mentioned in the title, we develop our method of calculation and the necessary software. In the full paper, we explain in some detail our method of calculation and the analysis of calculated results. In this abstract, we just add some pertinent remarks to listing the three topics of explanation. The first topic is: gas turbine engine with embedded PDC. In the first topic, Fig.2 in the full paper shows the ideal thermodynamic cycle of gas turbine engine with embedded PDC. The second topic is: the method of performance calculation. In the second topic, although eqs. (1) through (6) are all well known, we explain how to utilize them in our performance calculation. The third topic is: calculated performance results and their analysis. In the third topic, we compare gas turbine engine with embedded PDC with a conventional gas turbine engine. The three subtopics of the third topic are: static performance at sea level (subtopic 3.1), the effect of flight speed on engine performance (subtopic 3.2), and the effect of flight altitude on engine performance (subtopic 3.3). In subtopic 3.1, Table 1 shows that the gas turbine engine with embedded PDC produces 27.1% higher specific thrust and has 21.3% lower specific fuel consumption than a conventional gas turbine engine. In subtopic 3.2, we give Figs.3 through 8 to show that the specific thrust decreases with increasing flight speed at a given flight altitude. In subtopic 3.3, Figs.9 through 14 show that the specific thrust increases with increasing flight altitude at a given flight speed.