An empirical model for stagnation pressure gain in rotating detonation combustors

2020 ◽  
Author(s):  
Eric Bach ◽  
C. Oliver Paschereit ◽  
Panagiotis Stathopoulos ◽  
Myles D. Bohon
Keyword(s):  
Empirical Model ◽  
Stagnation Pressure ◽  
Rotating Detonation

scholarly journals Performance analysis of a rotating detonation combustor based on stagnation pressure measurements

2020 ◽  
Vol 217 ◽  
pp. 21-36 ◽  
Author(s):  
Eric Bach ◽  
Panagiotis Stathopoulos ◽  
Christian Oliver Paschereit ◽  
Myles D. Bohon
Keyword(s):  
Performance Analysis ◽  
Stagnation Pressure ◽  
Pressure Measurements ◽  
Rotating Detonation

Propagation characteristics of rotating detonation wave in plane–radial structure with different pressure conditions

2018 ◽  
Vol 233 (7) ◽  
pp. 2378-2392 ◽  
Author(s):  
Zhenjuan Xia ◽  
Hu Ma ◽  
Changfei Zhuo ◽  
Changsheng Zhou
Keyword(s):  
Detonation Wave ◽  
Pressure Ratio ◽  
Stagnation Pressure ◽  
Back Pressure ◽  
Propagation Characteristics ◽  
Flow Parameters ◽  
Radial Structure ◽  
Concave Boundary ◽  
Rotating Detonation ◽  
Peak Value

This paper simulates the propagation characteristics of rotating detonation wave in the plane–radial structure for mixtures of 2H2 + O2 + 3.76N2. Two-dimensional numerical simulation was modeled, and two kinds of typical flow field and corresponding operating range were obtained under various pressure conditions. Due to the influence of curvature, the detonation wave is strengthened near the outer concave boundary and weakened near the inner convex one. The pressure ratio was varied from 1.6 to 10 by varying both stagnation and back pressure for detonation parameters and flow parameters. It is found that these parameters are dependent only on stagnation pressure for higher pressure ratio. While the pressure ratio is low, the back pressure also has an effect on them. The detonation wave height initially increases and then decreases as stagnation pressure increases, and the pressure ratio has a significant effect on it for lower pressure ratio. The inlet block ratio varies slightly from 14% to 21%. The exit average Mach number has small fluctuations between 0.89 and 1.05. The exit supersonic flow ratio varies from 14% to 74%, and the peak value is gained when pressure ratio is 6. The exit pressure amplifying ratio varies from 1.45 to 1.95, and the maximum value is obtained when pressure ratio is 2.5.

Advancement of Empirical Model for Stagnation Pressure Gain in RDCs

2022 ◽  
Author(s):  
Eric Bach ◽  
Christian O. Paschereit ◽  
Panagiotis Stathopoulos ◽  
Myles Bohon
Keyword(s):  
Empirical Model ◽  
Stagnation Pressure

Numerical Modeling of the RDE

2020 ◽  
Vol 0 (0) ◽  
Author(s):  
Michal Folusiak ◽  
Karol Swiderski ◽  
Piotr Wolański
Keyword(s):  
Combustion Chamber ◽  
Turbine Engine ◽  
Rotating Detonation Engine ◽  
University Of Technology ◽  
Detonation Combustion ◽  
Detonation Engine ◽  
Innovative Economy ◽  
Turboshaft Engine ◽  
The University ◽  
Rotating Detonation

AbstractThe idea of using the phenomenon of rotating detonation to propulsion has its roots in fifties of the last century in works of Adamson et al. and Nicholls et al. at the University of Michigan. The idea was recently reinvented and experimental research and numerical simulations on the Rotating Detonation Engine (RDE) are carried in numerous institutions worldwide, in Poland at Warsaw University of Technology (WUT) since 2004. Over the period 2010-2014 WUT and Institute of Aviation (IOA) jointly implemented the project under the Innovative Economy Operational Programme entitled ‘Turbine engine with detonation combustion chamber’. The goal of the project was to replace the combustion chamber of turboshaft engine GTD-350 with the annular detonation chamber.This paper is focused on investigation of the influence of a geometry and flow conditions on the structure and propagation stability of the rotating detonation wave. Presented results are in majority an outcome of the aforementioned programme, in particular authors’ works on the development of the in-house code REFLOPS USG and its application to simulation of the rotating detonation propagation in the RDE.

A stagnation pressure probe for droplet-laden air flow

1985 ◽  
Author(s):  
S. MURTHY ◽  
M. LEONARDO ◽  
C. EHRESMAN
Keyword(s):  
Air Flow ◽  
Stagnation Pressure ◽  
Pressure Probe

Propulsive Performane of Cylindrical Rotating Detonation Engine with Propellant Injection Cooing

2021 ◽  
Author(s):  
Keisuke Goto ◽  
Kosei Ota ◽  
Akira Kawasaki ◽  
Hiroaki Watanabe ◽  
Nobotu Itouyama ◽  
...  
Keyword(s):  
Rotating Detonation Engine ◽  
Detonation Engine ◽  
Rotating Detonation

High-Bandwidth Laser-Absorption Measurements of Temperature, Pressure, CO, and H2O in the Annulus of a Rotating Detonation Rocket Engine

2021 ◽  
Author(s):  
Garrett C. Mathews ◽  
Matthew Blaisdell ◽  
Aaron I. Lemcherfi ◽  
Carson D. Slabaugh ◽  
Christopher S. Goldenstein
Keyword(s):  
Rocket Engine ◽  
Laser Absorption ◽  
High Bandwidth ◽  
Rotating Detonation ◽  
Absorption Measurements
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