Development of a Pulse Detonation Combustor for a Several kW-class Micro Gas Turbine

2010 Fiscal Year Final Research Report

• Project/Area Number: 21760653
• Research Category: Grant-in-Aid for Young Scientists (B)
• Allocation Type: Single-year Grants
• Research Field: Aerospace engineering
• Research Institution: Tokyo Metropolitan University
• Principal Investigator: SAKURAI Takashi Tokyo Metropolitan University, システムデザイン研究科, 助教 (10433179)
• Project Period (FY): 2009 – 2010
• Keywords: パルスデトネーション燃焼器 / デトネーション / 超小型ガスタービン / PDE / 航空宇宙推進

Research Abstract

A small, pulse detonation combustor with a length of 20cm and a volume of 120cm^3 was developed for several kW-class micro gas turbines. As a method to increase the cycle frequency, the counterflow and parallel fuel injection methods were proposed, and the premixture flow behavior and concentration distribution were measured. By using the turbulent flame jet-type initiators, detonation was attained in a hydrogen-fueled combustor. The exhaust behavior of the burned gas was observed. To shorten the exhaust process, the increase of the air flow velocity was effective.