Session: 04-23 Pressure Gain Combustion II

Paper Number: 152502

Effect of Film Cooling Hole Location on Flow Dynamics in a Rotating Detonation Combustor 

Detonation mode of combustion involves a flame with a leading shock front traveling at supersonic speeds, establishing a high fuel consumption rate, leading to greater energy release per unit area. This concept leads to high-power density combustors, the most advantageous of which are Rotating Detonation Combustors (RDC). The flow fields of RDC include axial bulk flow with detonation waves travelling around the combustor annulus along with an oblique shock wave connected to each detonation wave. The high combustor mass flow, greater heat release from the detonation wave, and periodic destruction of the boundary layer generates enormous wall thermal loads. Managing this high thermal load is essential for utilizing RDC for gas turbine applications. Earlier studies have shown that film cooling can be a possible solution for managing the harsh thermal load.  Film cooling is a well knowing cooling scheme for gas turbine applications however, it is still a novel concept for RDC. Hence, high fidelity numerical investigations are necessary for detailed assessment of the interactions of the film and the detonation. In this regard, film cooling is implemented within the TU Berlin RDC [MDB1] architecture and numerical investigations are conducted by performing LES using the AVBP code. Previous investigations of film cooling an RDC revealed that even with shockwave disruption, sufficient cooling was achieved. Moreover, the injected coolant reacted with the unburnt fuel leading to additional secondary deflagration heat release which increased the combustion efficiency.  In this study, film cooling is investigated within the detonation region of the RDC. The results show that the coolant penetrates up to half of the combustor annulus gap. The coolant jet in the detonation region modifies the initial mixture characteristics affecting the detonation combustion. Furthermore, the coolant jet interacts with the detonation deforming its shape.

 

 

 

Presenting Author: Shreyas Ramanagar Sridhara University of Florence

Presenting Author Biography: Researcher working on pressure gain combustion at University of Florence.

Authors:

Shreyas Ramanagar Sridhara University of Florence
Marc D. Polanka Air Force Institute of Technology
Myles D. Bohon Technical University Berlin
Antonio Andreini University of Florence