Lean-limit combustion instabilities of a lean premixed prevaporized gas turbine combustor

Dhanuka, Sulabh K.; Temme, Jacob; Driscoll, James F.

doi:10.1016/j.proci.2010.07.011

Cited by 75 publications

(32 citation statements)

References 10 publications

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“…A number of experimental studies have been performed on LJICF over the years (Wu et al, 1997(Wu et al, , 1998Dhanuka et al, 2011). Most of these studies discuss experiments at nearatmospheric conditions due to the obvious difficulty in setting up the experiments at high pressure and temperature conditions.…”

Section: Introductionmentioning

confidence: 99%

Detailed Numerical Simulations of Atomization of a Liquid Jet in a Swirling Gas Crossflow

et al. 2019

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Breakup of a liquid jet in a high speed gaseous crossflow finds wide range of engineering and technological applications, especially in the combustors of the gas turbine engines in aerospace industry. In this study, we present volume-of-fluid method based direct numerical simulations of a liquid jet injected into a swirling crossflow of gas. The liquid is injected radially outwards from a central tube to a confined annular space with a swirling gas crossflow. The essential features of the jet breakup involving jet flattening, surface waves and stripping of droplets from the edges of the jet are captured in the simulations. We discuss the effect of swirl on the spray characteristics such as jet trajectory, column breakup-length, and size, shape-factor and velocity distribution of the drops. Drop size increases with swirl and penetration is slightly reduced. Moreover, the trajectory follows an angle (azimuthal) that is smaller than the geometric angle of the swirl at inlet. Interestingly, we also observe coalescence events downstream of the jet that affect the final droplet size distribution for the geometry considered in this study.

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Section: Introductionmentioning

confidence: 99%

Detailed Numerical Simulations of Atomization of a Liquid Jet in a Swirling Gas Crossflow

et al. 2019

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“…Over the past few years, ARL and NASA have conducted various in-house and contractual efforts to understand the combustion dynamics of LDI concepts. Some of those efforts utilized a single injector specifically designed to generate combustion instabilities in a laboratory setting [10][11][12][13]. Others utilized multiple injectors more closely resembling an actual engine configuration and were experimentally evaluated at inlet conditions close to actual engine conditions.…”

Section: I Introductionmentioning

confidence: 99%

Comparison of Combustion Dynamic Characteristics of Two Advanced Multi-Cup Fuel Injectors

Acosta

Chang

2018

2018 Joint Propulsion Conference

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An experimental investigation of the combustion dynamic characteristics of two advanced multi-cup lean direct injectors (LDI) under simulated gas turbine combustor conditions was conducted. The objective was to gain a better understanding of the physical phenomena inside a pressurized flame tube combustion chamber and study the effects of injector flow number on combustion dynamics. The injectors are known as Three-zone Injectors one and two or 3ZI-1 and 3ZI-2, respectively. The injectors were experimentally evaluated at inlet pressures up to 1.724 MPa, non-vitiated air temperatures up to 828K, and adiabatic flame temperatures up to 1975K. Dynamic pressure measurements were taken upstream of the injectors and in the combustion zone. The combustion dynamic behavior of the two injectors was measured over a range of inlet pressures, inlet temperatures, fuel air ratios, and fuel flow splits.

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“…As experimental conditions become harsher (high pressure and temperature, thermo-acoustic instabilities), setting laser diagnostics however start to present technical difficulties explaining why their use in somewhat realistic conditions is limited. For the analysis of instabilities in gas turbine type combustors at elevated pressure, mostly low frequency laser diagnostics such as Particle Image Velocimetry (PIV) or Planar Laser-Induced Fluorescence (PLIF) have been used [6][7][8][9]. Boxx et al [10], used 3 kHz simultaneous PIV/OH-PLIF measurements to study a 388 Hz thermo-acoustic instability in a natural gas fueled combustor at 5 bars.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study of Thermo-Acoustic Instability Triggering in a Staged Liquid Fuel Combustor Using High-Speed OH-PLIF

Renaud

Tachibana

Arase

et al. 2017

Volume 4A: Combustion, Fuels and Emissions

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A staged injector developed by JAXA and fueled with kerosene is studied in a high-pressure combustion experiment. With a stable pilot fuel flow rate, the fuel flow rate in the main stage is progressively increased. A high-speed OH-PLIF system is used to record the flame motion at 10,000 fps. In the beginning of the recording, the flame behavior is dominated by relatively low-frequency rotation due to the swirling motion of the flow. These rotational motions then coexist with a thermo-acoustic instability around 475 Hz which increases the amplitude of the pressure fluctuations inside the chamber. DMD analyses indicate that this instability is associated with a widening of the flame occurring when the pressure fluctuations are the highest, giving the instability a positive feedback. The instability frequency then abruptly switches to 500 Hz while the mode shape remains

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Lean-limit combustion instabilities of a lean premixed prevaporized gas turbine combustor

Cited by 75 publications

References 10 publications

Detailed Numerical Simulations of Atomization of a Liquid Jet in a Swirling Gas Crossflow

Detailed Numerical Simulations of Atomization of a Liquid Jet in a Swirling Gas Crossflow

Comparison of Combustion Dynamic Characteristics of Two Advanced Multi-Cup Fuel Injectors

Experimental Study of Thermo-Acoustic Instability Triggering in a Staged Liquid Fuel Combustor Using High-Speed OH-PLIF

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