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

Two-dimensional arc stagnation pressure measurements for the double-electrode GTAW process

2016 ◽  
Vol 21 (4) ◽  
pp. 275-280 ◽  
Author(s):  
M. B. Schwedersky ◽  
R. H. Gonçalves e Silva ◽  
J. C. Dutra ◽  
U. Reisgen ◽  
K. Willms
Keyword(s):  
Stagnation Pressure ◽  
Pressure Measurements ◽  
Two Dimensional ◽  
Double Electrode ◽  
Gtaw Process

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 Bayesian Mass Averaging in Rigs and Engines

2022 ◽  
pp. 1-15
Author(s):  
Pranay Seshadri ◽  
Andrew Duncan ◽  
George Thorne
Keyword(s):  
Random Field ◽  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Gaussian Random Field ◽  
Analytical Calculation ◽  
Sampling Procedure ◽  
Stagnation Pressure ◽  
Pressure Measurements

Abstract This paper introduces the Bayesian mass average and details its computation. Owing to the complexity of flow in an engine and the limited instrumentation and the precision of the sensor apparatus used, it is difficult to rigorously calculate mass averages. Building upon related work, this paper views any thermodynamic quantity's spatial variation at an axial plane in an engine (or a rig) as a Gaussian random field. In cases where the mass flow rate is constant in the circumferential direction but can be expressed via a polynomial or spline radially, this paper presents an analytical calculation of the Bayesian mass average. In cases where the mass flow rate itself can be expressed as a Gaussian random field, a sampling procedure is presented to calculate the Bayesian mass average. Examples of the calculation of the Bayesian mass average for temperature are presented, including with a real engine case study where velocity profiles are inferred from stagnation pressure measurements.

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.

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