Abstract
This study focused on the computational design and static structural analysis of a smallscale turbojet engine (SSTE) that can power an unmanned aerial vehicle with a thrust of 50 N at a
speed of 8000 rpm. SOLIDWORKS 2018 was used to design the CAD geometry of the SSTE, and
to carry out a CFD analysis on the compressor to determine the pressure distribution across the
compressor and the compressor pressure ratio. The obtained pressure ratio was further used to carry
out a structural analysis of the SSTE with emphasis on the turbine component using ANSYS static
structural module. This is because the turbine component is more susceptible to maximum stresses
and temperature. However, this analysis was done to determine the level of deformation of the
chosen design material (stainless steel grade 310), the maximum and minimum stresses, factor of
safety, and its fatigue life. Design and CFD results obtained shows that the design is reliable as well
as the pressure distribution in the compressor. The 50N small scale turbojet engine showed higher
optimum performance from structural design and evaluation when compared to that of the 70N
thrust jet cat model. Results of the structural analysis shows that the turbine blades will experience
minimum and maximum deformation of 0 m and 2.2543×10^(-5) m at the leading edges and trailing
edges of the blade chord respectively. Also, maximum and minimum stresses will occur at
1.0632×10^5 Pa and 6.7192×10^7 Pa respectively. Conversely, the factor of safety was within
3.0807 to 15 which show that the design is adequate. Additionally, considering the fatigue life, the
SSTE is bound to fail completely at approximately 1.929×10^7 months. Therefore the SSTE with
the materials suggested above is capable of propelling an unmanned aerial vehicle considering the
results obtained.
speed of 8000 rpm. SOLIDWORKS 2018 was used to design the CAD geometry of the SSTE, and
to carry out a CFD analysis on the compressor to determine the pressure distribution across the
compressor and the compressor pressure ratio. The obtained pressure ratio was further used to carry
out a structural analysis of the SSTE with emphasis on the turbine component using ANSYS static
structural module. This is because the turbine component is more susceptible to maximum stresses
and temperature. However, this analysis was done to determine the level of deformation of the
chosen design material (stainless steel grade 310), the maximum and minimum stresses, factor of
safety, and its fatigue life. Design and CFD results obtained shows that the design is reliable as well
as the pressure distribution in the compressor. The 50N small scale turbojet engine showed higher
optimum performance from structural design and evaluation when compared to that of the 70N
thrust jet cat model. Results of the structural analysis shows that the turbine blades will experience
minimum and maximum deformation of 0 m and 2.2543×10^(-5) m at the leading edges and trailing
edges of the blade chord respectively. Also, maximum and minimum stresses will occur at
1.0632×10^5 Pa and 6.7192×10^7 Pa respectively. Conversely, the factor of safety was within
3.0807 to 15 which show that the design is adequate. Additionally, considering the fatigue life, the
SSTE is bound to fail completely at approximately 1.929×10^7 months. Therefore the SSTE with
the materials suggested above is capable of propelling an unmanned aerial vehicle considering the
results obtained.
| Original language | English |
|---|---|
| Journal | Advanced Research in Energy and Engineering |
| Volume | 2 |
| Issue number | 1 |
| Publication status | Published - 7 Dec 2020 |