Analysis of Deflagrative Combustion in a Wave-Rotor Constant-Volume Combustor

Elharis, Tarek M.; Wijeyakulasuriya, Sameera; Nalim, M. Razi; Matsutomi, Yu

doi:10.2514/6.2011-583

Cited by 10 publications

(9 citation statements)

References 4 publications

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“…6 Use perfect gas relations to compute pressure losses downstream of this station, to compute the stagnation pressure and temperature at the rotor plane. 7…”

Section: Dynamic Model Executionmentioning

confidence: 99%

“…6 The software used to perform these analyses is a derivative of software developed for generic wave rotor analysis, and documented in Paxson 12 ,13 ,14 ,15 ,16 , and Nalim. 17 The original code developed by NASA is often referred to as the NASA quasi one-dimensional (Q1D) wave rotor code.…”

Section: Nasa Combustion Wave Rotor Computer Softwarementioning

confidence: 99%

“…Elharis 4 further elaborated on the aerothermal design and provided the model validation of the rig. This WRCRV rig has also been the subject of other papers including a detailed experimental investigation paper by Matsutomi 5 and an analysis of the deflagrative combustion process by Elharis et al 6 …”

Section: Introductionmentioning

confidence: 99%

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Coupled Analysis of the Inlet and Fuel Systems of a Wave Rotor Constant-Volume Combustor

Smith¹,

Nalim²

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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A wave rotor constant-volume combustor (WRCVC) test rig was designed and built, and was tested initially in 2009. Instrumentation of the WRCVC rig inlet flow included temperature and pressure transducers and at the fuel delivery plane, as well as upstream of a mass-flow controlling choked venturi. Other instrumentation included exhaust pressures and temperatures. In addition, ion sensors, dynamic pressure sensors, thermocouples, and accelerometers were used to instrument the rotating hardware, and delivered data via a slip ring. The rig hardware included inlet guide vanes immediately upstream of the rotor, which together with concern for ingestion damage potential, prevented use of any stagnation pressure transducers at the entrance to the rotor. For this reason, a complete understanding of the conditions at the WRCVC inlet is unavailable, requiring simulations of the WRCVC to estimate the inlet pressure at a specific operating condition based on airflow. Thermal limits of the instrumentation and other rig features limit the firing period of the rig to a few seconds. The operation of a WRCVC rig test consists of a sequence of events that include rotor spinup and introduction of the main air flow, followed by timesequenced delivery of fuel, lighting of the ignition source, and the combustion sequence. The fast changing conditions necessitate a time-dependent computation of the rig inlet system including its volume dynamics in order to simulate the overall rig operation. A time-dependent lumped-volume model of the inlet section hardware is presented, using a finite difference modified Euler predictor-corrector method for computing the continuity and energy equations. This is coupled with prediction of venturi air and fuel flow rates, pressure drag losses at the fuel nozzles, pressure losses by mass addition, friction losses, and a correlation of the non-dimensional flow characteristics of the WRCVC. The flow characteristics of the WRCVC are computed by varying the non-dimensional inlet stagnation pressure and the WRCVC's operational conditions, assuming constant rotational speed and inlet stagnation temperature. A computer simulation of the entire WRCVC rig was created, to understand the pressure losses in the inlet system and the dynamic coupling of the inlet section and the WRCVC, so that an accurate prediction of the WRCVC rotor inlet conditions can be computed. Documented are the computational development of the WRCVC upstream rig dynamic model, the background behind supporting computations, and results for one test sequence. The simulation predicts the pressures at the rotor inlet and the measured values. Measured pressures correlate with the simulation values and the simulation illustrates the dynamic response of the WRCVC. NomenclatureA Area a Sonic velocity c p

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“…6 Use perfect gas relations to compute pressure losses downstream of this station, to compute the stagnation pressure and temperature at the rotor plane. 7…”

Section: Dynamic Model Executionmentioning

confidence: 99%

Section: Nasa Combustion Wave Rotor Computer Softwarementioning

confidence: 99%

See 1 more Smart Citation

Coupled Analysis of the Inlet and Fuel Systems of a Wave Rotor Constant-Volume Combustor

Smith¹,

Nalim²

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

show abstract

“…For a gas turbine engine, pressure gain combustion has a strong potential to significantly improve the performance and reduce emissions [1]. The constant-volume pressure gain combustion could achieve an ideal Humphrey cycle.…”

Section: Introductionmentioning

confidence: 99%

“…Elharis et al conducted a preliminary testing of a WRC using ethylene as fuel and a wave rotor speed of 2100 rpm [1]. High-frequency dynamic pressure sensors were installed at different positions to measure the variation of pressure with time, and self-pressurized combustion was realized within the WRC.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Pressure Rise and Flame Acceleration Characteristics in a Single Channel of Wave Rotor Combustor with Spoilers

Zhang

Wei³

et al. 2019

International Journal of Aerospace Engineering

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A simplified single channel wave rotor combustor (WRC) experimental rig was established, in which the spoilers with different blockage ratios (BR) could be conveniently installed and disassembled. The spoilers were firstly used for WRC to improve the pressure rise. The effects of different blockage ratios on the pressure rise and flame acceleration characteristics in a single channel of the WRC were investigated. The addition of spoilers could remarkably improve the pressure rise and flame propagation speed in a single channel of the WRC. While the blockage ratio of the spoiler increases, both pressure rise and mean flame propagation speed are improved. When the spoilers with a blockage ratio of 38.91% are used, the peak pressure increases by 200% compared to that of WRC without the spoilers. When the spoilers of different blockage ratios (23.35%, 31.13%, and 38.91%) are used, it is found that the flame propagation speed is significantly improved with the increasing of the blockage ratio. Specifically, the maximum flame propagation speed reaches 55 m/s, and the maximum mean flame propagation speed is 36.95 m/s. Furthermore, combustion becomes more intense, and the flame is brighter around the spoiler.

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Research on the working characteristics of wave rotor combustor hot jet igniter and its validation

Gong,

Hao,

Cao

2023

Applied Thermal Engineering

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Analysis of Deflagrative Combustion in a Wave-Rotor Constant-Volume Combustor

Cited by 10 publications

References 4 publications

Coupled Analysis of the Inlet and Fuel Systems of a Wave Rotor Constant-Volume Combustor

Coupled Analysis of the Inlet and Fuel Systems of a Wave Rotor Constant-Volume Combustor

Investigation of Pressure Rise and Flame Acceleration Characteristics in a Single Channel of Wave Rotor Combustor with Spoilers

Research on the working characteristics of wave rotor combustor hot jet igniter and its validation

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