Periodic Reporting for period 2 - INSPIRE (INSpiring Pressure gain combustion Integration, Research, and Education)
Reporting period: 2023-01-01 to 2024-12-31
The primary, overarching, research objective of INSPIRE was to advance Pressure Gain Combustion (PGC) as the next generation of sustainable, highly efficient, and hydrogen-optimized combustion concepts toward achieving the performance and emissions goals of the next few decades. Thanks to the background of partners on PGC, INSPIRE brought relevant expertise together pursuing solutions on an integrated level. The following key objectives can be summarized:
1. Gain a deeper understanding of the impact of gas turbine integration on the specific combustion issues within both PGC solutions, including pressure effects, turbine interaction, performance losses, and ignition.
2. Investigate innovative turbine aerodynamics and cooling technologies designed to address the specific issues and unsteadiness associated with PGC;
3. Explore the application of PGC cycles in power generation and propulsion applications, including the provision of targets for the highest potential PGC applications for future research targets;
4. Raise the global awareness of the potential of PGC applications and communicate to the research community the coupled effects of the above objectives on existing and future technologies;
5. Raise and prepare a new generation of researchers, equipped with the skills to pursue such interdisciplinary problems as in PGC.
The network was organized into 15 ESR projects spread across 4 technical work packages (see Figure 1).
Overall, the project objectives were successfully achieved. All of the research projects were completed on time and the corresponding PhDs have been carried out or are expected shortly. It can be emphasised that the research and training programme developed in INSPIRE helped to instil in the recruited fellows an awareness of their global impact on the environment and on social responsibility. The overall quality of the produced results is confirmed by the scientific papers produced along the project, with more than 70 papers among which 18 journal articles, suggesting the possible relevant scientific impact of the outcomes in the near future.
1. Gain a deeper understanding of the impact of gas turbine integration on the specific combustion issues within both PGC solutions, including pressure effects, turbine interaction, performance losses, and ignition.
2. Investigate innovative turbine aerodynamics and cooling technologies designed to address the specific issues and unsteadiness associated with PGC;
3. Explore the application of PGC cycles in power generation and propulsion applications, including the provision of targets for the highest potential PGC applications for future research targets;
4. Raise the global awareness of the potential of PGC applications and communicate to the research community the coupled effects of the above objectives on existing and future technologies;
5. Raise and prepare a new generation of researchers, equipped with the skills to pursue such interdisciplinary problems as in PGC.
The network was organized into 15 ESR projects spread across 4 technical work packages (see Figure 1).
Overall, the project objectives were successfully achieved. All of the research projects were completed on time and the corresponding PhDs have been carried out or are expected shortly. It can be emphasised that the research and training programme developed in INSPIRE helped to instil in the recruited fellows an awareness of their global impact on the environment and on social responsibility. The overall quality of the produced results is confirmed by the scientific papers produced along the project, with more than 70 papers among which 18 journal articles, suggesting the possible relevant scientific impact of the outcomes in the near future.
ESR1 - Experimental investigation of Constant Volume Combustion and its reduced order model (Choomanee Runnoo, ENSMA)
Comprehensive ignition tests on the CV2 Constant Volume Combustion vessel at ENSMA were carried out. Example of fully premixed propane test in figure 2.
ESR2 - Numerical analysis of the interaction between a Rotating Detonation Combustor and an axial turbine (Gregory Uhl, SAFRAN)
Verification by the means of high-fidelity CFD how an exhaust ejector is capable of considerably reducing the total pressure fluctuations stemming from an RDC exhaust, a promising result for turbine integration (see figure 3).
ESR3 - Simulation of CVC combustor (Nicola Detomaso, CERFACS)
A wide set of LES calculations of the ENSMA CV2 combustor have been carried out using AVBP code linked to an ad-hoc developed reduced 2-step mechanism for propane. A good agreement with experiments was achieved (see figure 4).
ESR4 - Experimental characterization of ignition events in CVC like conditions (Maria Clara De Jesus Vieira, ENSMA)
A modified design of the TUMBLE combustor at ENSMA was realized to improve the control of turbulence intensities so as to optimize the ignition sequences. Figure 5 reports an example of measured MIE versus normalized turbulence intensity
ESR5 - Control and impact of RDC wave direction (Provence Barnouin, TUB)
Final outcome is the analysis of the propagation and interaction mechanisms of counter-rotating waves in RDCs with one-dimensional gas dynamics model to capture their dynamics (Figure 6)
ESR6 - LES of flow and combustion in a rotating detonation engine coupled to a turbine (Patrick Strempfl, CERFACS)
Investigation of the role of fuel-air mixing on RDc performance by the means of LES (Figure 7 example of results)
ESR7 - Experimental investigation of rotating detonation combustors including ignition processes and turbine-integration effects (Hongyi Wei, TUB)
Main outcome is the observation of the effect of combustor outlet restriction on the behaviour of the RDC (see Figure 8).
ESR8 - Computational aeroacoustics of the exhaust flow for noise assessment and control (Thomas Golliard, KTH)
Computational aeroacoustics calculations of the RDC exhaust plume and radiated noise were carried out for relevant operating conditions (see Figure 9).
ESR9 - Deflagration-Autoignition-Detonation transition (DADT) (Roseline Ngozi Ezekwesili, TUB)
Experimental investigations of the DADT phenomenon with 1-d model development (see example of exp results in Figure 10).
ESR10 - Numerical modelling and optimization of cooling solutions for PGC concepts (Shreyas Ramanagar Sridhara, UNIFI)
Design and LES CFD modelling of film cooling process in a RDC combustor (see computational grid and results in Figure 11)
ESR11 - Experimental study of cooling solutions for PGC concepts (Umberto Sandri, UNIFI)
Main ol was the experimental investigation of film cooling effectiveness with supersonic flow representative of RDC (see Schieleren measures in Figure 12)
ESR12 - Unsteady numerical simulation of the interaction between pressure-gain combustors and high-pressure turbine stages (Panagiotis Gallis, POLITO)
On of the main goal was the CFD study to develop a transition piece geometry for the CVC combustor available at ENSMA (Figure 13)
ESR13 - Power plant analysis and cycle thermo-economic optimization (Abhishek Dubey, UNIGE)
A complete thermodynamic analysis of gas turbine cycle with a CVC combustor was carried out with WTEMP code (Figure 14a)
ESR14 - Propulsion application with part load and dynamic analysis (Sreenath Purshothaman, UNIGE)
Modelling of a conventional aircraft engine (CFM56-3 high bypass turbofan engine) using TRANSEO simulation tool and preliminary analysis with a PGC combustor (Figure 14b)
ESR15 -Full gas dynamic and exergetic analysis of PGC cycles with rotating detonations (Gokkul Raj Varatharajulu Purgunan, TUB)
Development of a 1D-Euler based tool for turbine modelling (see example of results in Figure 15)
Comprehensive ignition tests on the CV2 Constant Volume Combustion vessel at ENSMA were carried out. Example of fully premixed propane test in figure 2.
ESR2 - Numerical analysis of the interaction between a Rotating Detonation Combustor and an axial turbine (Gregory Uhl, SAFRAN)
Verification by the means of high-fidelity CFD how an exhaust ejector is capable of considerably reducing the total pressure fluctuations stemming from an RDC exhaust, a promising result for turbine integration (see figure 3).
ESR3 - Simulation of CVC combustor (Nicola Detomaso, CERFACS)
A wide set of LES calculations of the ENSMA CV2 combustor have been carried out using AVBP code linked to an ad-hoc developed reduced 2-step mechanism for propane. A good agreement with experiments was achieved (see figure 4).
ESR4 - Experimental characterization of ignition events in CVC like conditions (Maria Clara De Jesus Vieira, ENSMA)
A modified design of the TUMBLE combustor at ENSMA was realized to improve the control of turbulence intensities so as to optimize the ignition sequences. Figure 5 reports an example of measured MIE versus normalized turbulence intensity
ESR5 - Control and impact of RDC wave direction (Provence Barnouin, TUB)
Final outcome is the analysis of the propagation and interaction mechanisms of counter-rotating waves in RDCs with one-dimensional gas dynamics model to capture their dynamics (Figure 6)
ESR6 - LES of flow and combustion in a rotating detonation engine coupled to a turbine (Patrick Strempfl, CERFACS)
Investigation of the role of fuel-air mixing on RDc performance by the means of LES (Figure 7 example of results)
ESR7 - Experimental investigation of rotating detonation combustors including ignition processes and turbine-integration effects (Hongyi Wei, TUB)
Main outcome is the observation of the effect of combustor outlet restriction on the behaviour of the RDC (see Figure 8).
ESR8 - Computational aeroacoustics of the exhaust flow for noise assessment and control (Thomas Golliard, KTH)
Computational aeroacoustics calculations of the RDC exhaust plume and radiated noise were carried out for relevant operating conditions (see Figure 9).
ESR9 - Deflagration-Autoignition-Detonation transition (DADT) (Roseline Ngozi Ezekwesili, TUB)
Experimental investigations of the DADT phenomenon with 1-d model development (see example of exp results in Figure 10).
ESR10 - Numerical modelling and optimization of cooling solutions for PGC concepts (Shreyas Ramanagar Sridhara, UNIFI)
Design and LES CFD modelling of film cooling process in a RDC combustor (see computational grid and results in Figure 11)
ESR11 - Experimental study of cooling solutions for PGC concepts (Umberto Sandri, UNIFI)
Main ol was the experimental investigation of film cooling effectiveness with supersonic flow representative of RDC (see Schieleren measures in Figure 12)
ESR12 - Unsteady numerical simulation of the interaction between pressure-gain combustors and high-pressure turbine stages (Panagiotis Gallis, POLITO)
On of the main goal was the CFD study to develop a transition piece geometry for the CVC combustor available at ENSMA (Figure 13)
ESR13 - Power plant analysis and cycle thermo-economic optimization (Abhishek Dubey, UNIGE)
A complete thermodynamic analysis of gas turbine cycle with a CVC combustor was carried out with WTEMP code (Figure 14a)
ESR14 - Propulsion application with part load and dynamic analysis (Sreenath Purshothaman, UNIGE)
Modelling of a conventional aircraft engine (CFM56-3 high bypass turbofan engine) using TRANSEO simulation tool and preliminary analysis with a PGC combustor (Figure 14b)
ESR15 -Full gas dynamic and exergetic analysis of PGC cycles with rotating detonations (Gokkul Raj Varatharajulu Purgunan, TUB)
Development of a 1D-Euler based tool for turbine modelling (see example of results in Figure 15)
The research obtained in the 15 PhD projects in the INSPIRE network certainly represents a significant progress beyond the state of the art in the investigation and comprehension of aerothermal phenomena in PGC combustors. Advanced experimental and numerical methodologies has permitted to describe complex phenomena such us ignition in CVC, the role of fuel air mixing and cooling process on RDC and the effects of combustors inflow and outflow geometry. Fundamental studies on deflagration-detonation transition, supersonic film cooling and aeroacoustics will allow to support future design of PGC combustors but could be exploited also in other technical areas. System level modelling showed the possible use and improvements when using CVC and RDC in practical implementations of gas turbines. The main exploitations of project outcomes can be point out in the enforcement of research capabilities and skills of the consortium members, with the further improvement of research collaborations among them and the involvement in the network of other relevant research groups and scientists from different countries.