Introduction and contact info:
Name: Gokkul Raj Varatharajulu Purgunan
Work address: TU Berlin, Straße des 17. Juni 135,
10623 Berlin.
email: gokkul.raj.varatharajulu.purgunan@tu-berlin.de
PhD project:
Title: Full gas dynamics and exergetic analysis of PGC cycles with rotating detonations
The PhD topic for ESR 15 is “Full Gas dynamics and exergetic analysis of PGC cycles with Rotating Detonations”. The final expected result is the full cycle simulation of rotating detonation combustor (RDC) with the turbomachinery upstream and downstream of the combustor. The first task is to integrate the Turbine to the exhaust of the RDC using 1D unsteady Euler model. For the 1D Euler model, the source terms are calculated using mean-line analysis of turbine. Once, the turbine integration is done successfully, the compressor integration to RDC will be done. The procedure for compressor designing is similar to that of the turbine, that is, the compressor is modelled with unsteady 1D Euler model, and the source term for the 1D Euler, will be evaluated from mean-line analysis of compressor. The in-built code for RDC is 2D unsteady Euler model, and during the PhD, the reduced order model for the combustor will be derived from existing 2D unsteady Euler RDC model and CERFACS detailed 3D simulations. This reduced order model is aimed to develop in CERFACS during one of the secondments. This reduced order model will be integrated to the whole cycle model. Then, the secondary compressor will be modelled. The main role for the secondary compressor is to compress the air to the outlet pressure same as the RDC outlet pressure. The exhaust of the secondary compressor will be sent to the exhaust of the RDC in order to dampen the fluctuation before the burnt gas entering the turbine. The part of compressed air from secondary compressor will be used as bleed flow for the turbine blade cooling. Then, the second secondment (UNIGE) will be carried out to broaden the understanding on transient and time-dependent gas turbine simulation. Finally, having all the component modelled, a full cycle simulation will be carried out.
Supervisor: Prof. Panagiotis Stathopoulos
Mentor: Prof. Alessandro Sorce
Planned secondments:
- CERFACS (M18 – M20) – Aim to develop the reduced order model for the rotating detonation combustor that will be integrated to the whole model.
- UNIGE (M27 – M29) – To broaden the understanding on transient and time-dependent gas turbine simulations and assist the collegeaus there for the development of their own reduced order model for rotating detonation combustor.
Background:
- Born in Chennai, India
- Bachelors in AERONAUTICAL Engineering from Madras Institute of Technology, India (07/2014–04/2018).
- Master in AERONAUTIQUE et ESPACE with specialization in Energetics and Propulsion from ISAE-ENSMA, France (09/2018 – 01/2021).
Personal interests:
Sports (Cricket, squash, tennis), Cooking.
LinkedIn profile. https://www.linkedin.com/in/gokkul-raj-v-p/.
Research highlights:
Results Obtained:
- Meanline analysis of axial turbine to provide source terms for the unsteady 1D Euler turbine model.
- The integration of unsteady 1D Euler model with the downstream of Rotating Detonation Combustor
- Reduced order model for Optimization of Turbine to reduce the entropy generations and comparison with 3D CFD results.
- Implementation of film cooling in the unsteady 1D Euler turbine model by including two new source terms for the coolant and comparison with 3D CFD results and in collaboration with POLITO.
- Quasi 1D and 0D modelling of Rotating Detonation Combustor and comparison with 3D CFD results.
- 0D ejector model downstream to Rotating Detonation Combustor.
Next Steps:
- 0D cycle analysis of TurboJet and TurboFan configuration with the integration of Rotating Detonation Combustor.
- Unsteady 1D Euler compressor model.
- 1D cycle analysis during the secondment in UniGe
