Experimental Investigations of an Axial Turbine Driven by a Multi-Tube Pulsed Detonation Combustor System

Influence of Unsteadiness on the Analysis of Pressure Gain Combustion Devices

“…Equation (23) complicates the PGC Atkinson T-s diagram of Figure 2 since each infinitesimal unit of mass not only has a different P t4 , and T t4 , but also has a different T 9 . In other words, each unit of mass follows a different path to the specified exit static pressure line.…”

“…u u u ′ + = , where 9 u′ represent a deviation from the mass averaged value obtained via Equation (17). Squaring this quantity yields Taking the mass average of 2 9 u and noting that 0 9 = ′ u by definition yields u′ is greater than zero for all periodic unsteady flows, it follows that 2 9 9 u u ≤ .…”

The Influence of Unsteadiness on the Analysis of Pressure Gain Combustion Devices

“…A more general statement than Equation (19) can be made on the relationship between 9 u and 2 9 u . Consider an arbitrary periodic exit velocity profile arising from detonative or deflagrative PGC.…”

“…(5)). The net specific thrust is therefore found by subtracting the (assumed steady) inlet velocity from 9 u .…”

Thermo-acoustic characterization of the burner-turbine interface in a can-annular combustor using CFD

“…In the current study the reflection coefficient study is performed in parallel to a transmission coeffi- cient analysis between two cans in order to observe their acoustic interaction. Papers by Rasheed et al [29], [30], Baptista et al [31] and Caldwell et al [32] show the most recent development related to experimental studies concerning acoustic interaction between multi-tube combustor and single-stage axial turbines. Also the work of Deng et al [33] investigates the interaction of a pulse detonation combustor integrated with a turbine hybrid system.…”