Experimental and Numerical
Investigation of Non-reacting Flow
in Can Combustor for Microgas Turbine
Engine
V. Kirubakaran and David S. Bhatt
Abstract Generally, microgas turbines are in the range of 30–200 kW. So, here it is
proposed to develop a microgas turbine engine with a capacity of 3 kW which will
have applications in unmanned aerial vehicle (UAV) and standalone power generation for domestic use. In this study, the behavior of non-reacting flow pattern inside a
swirl stabilized can combustor is studied. Total pressure loss, which is an important
performance parameter, is predicted numerically and compared with that from experiments. Good agreement is achieved between experimental and numerical results.
The combustor total pressure drop was found to be negligible; in the range of 0.002–
0.06% at an inlet velocity ranges from 1.7 to 10.19 m/s. Flow pattern indicates strong
vortex formation due to secondary air entrainment inside the flame tube.
Keywords CFD · Can combustor · Total pressure loss
1 Introduction
The microgas turbines are more suitable for compact power generation; the engines
are classified on power ranges less than 200 kW. It has advantages futures like high
power density, fuel flexibility, low emission, less maintenance and operational costs
[1–4]. In literature, more emphasis is given for the development of engines more than
30 kW. However, for domestic power generation and UAVs, small engines of capacity
from 1 to 10 kW are needed. So, it is aimed to develop such an engine. At the outset, the
focus is to develop a small can combustor for this type of engine. The development
of microgas turbine combustor is a challenging task similar to large gas turbine
combustor. The combustor is one of the important components which decide the
V. Kirubakaran · D. S. Bhatt (B)
Department of Aeronautical Engineering, Vel Tech Rangarajan Dr. Sagunthala R&D
Institute of Science and Technology, Chennai, Tamil Nadu 600062, India
e-mail: davidbhatt@gmail.com
V. Kirubakaran
e-mail: kirubakaranvijayakumar@gmail.com
© The Editor(s) (if applicable) and The Author(s), under exclusive license
to Springer Nature Singapore Pte Ltd. 2021
N. Gascoin and E. Balasubramanian (eds.), Innovative Design, Analysis
and Development Practices in Aerospace and Automotive Engineering, Lecture Notes
in Mechanical Engineering, https://doi.org/10.1007/978-981-15-6619-6_14
131
Investigation of Non-reacting Flow
in Can Combustor for Microgas Turbine
Engine
V. Kirubakaran and David S. Bhatt
Abstract Generally, microgas turbines are in the range of 30–200 kW. So, here it is
proposed to develop a microgas turbine engine with a capacity of 3 kW which will
have applications in unmanned aerial vehicle (UAV) and standalone power generation for domestic use. In this study, the behavior of non-reacting flow pattern inside a
swirl stabilized can combustor is studied. Total pressure loss, which is an important
performance parameter, is predicted numerically and compared with that from experiments. Good agreement is achieved between experimental and numerical results.
The combustor total pressure drop was found to be negligible; in the range of 0.002–
0.06% at an inlet velocity ranges from 1.7 to 10.19 m/s. Flow pattern indicates strong
vortex formation due to secondary air entrainment inside the flame tube.
Keywords CFD · Can combustor · Total pressure loss
1 Introduction
The microgas turbines are more suitable for compact power generation; the engines
are classified on power ranges less than 200 kW. It has advantages futures like high
power density, fuel flexibility, low emission, less maintenance and operational costs
[1–4]. In literature, more emphasis is given for the development of engines more than
30 kW. However, for domestic power generation and UAVs, small engines of capacity
from 1 to 10 kW are needed. So, it is aimed to develop such an engine. At the outset, the
focus is to develop a small can combustor for this type of engine. The development
of microgas turbine combustor is a challenging task similar to large gas turbine
combustor. The combustor is one of the important components which decide the
V. Kirubakaran · D. S. Bhatt (B)
Department of Aeronautical Engineering, Vel Tech Rangarajan Dr. Sagunthala R&D
Institute of Science and Technology, Chennai, Tamil Nadu 600062, India
e-mail: davidbhatt@gmail.com
V. Kirubakaran
e-mail: kirubakaranvijayakumar@gmail.com
© The Editor(s) (if applicable) and The Author(s), under exclusive license
to Springer Nature Singapore Pte Ltd. 2021
N. Gascoin and E. Balasubramanian (eds.), Innovative Design, Analysis
and Development Practices in Aerospace and Automotive Engineering, Lecture Notes
in Mechanical Engineering, https://doi.org/10.1007/978-981-15-6619-6_14
131