This paper presents a series of experiments and numerical simulations using commercial software (ANSYS) to determine the behaviour and impact on the blowoff process with various geometries and simulated syngas compositions at fixed power outputs. Experiments were performed using a generic premixed swirl burner. The Central Recirculation Zone and the associated turbulent structure contained within it were obtained through CFD analyses providing details of the structures and the Damkolher Number (Da) close to blowoff limits. The results show how the strength and size of the recirculation zone are highly influenced by the blend, with a shift of Da and turbulence based on carbon-hydrogen ratio, shearing flows and Reynolds number. Instabilities such as thermoacoustics, flashback, autoignition and blowoff are highly affected by the flow structures and chemical reactions/diffusivity. Moreover, it has been observed that turbulence close to the boundaries of the central recirculation zone, a region of high stability for swirling flows, is highly altered by the chemical characteristics of the fuel blends. In terms of blowoff, the phenomenon is still not entirely understood. As the process occurs, its theoretical limits do not match its real behaviour. Therefore, one possibility could be the difference in turbulence and Da numbers across the flame, being critical at the base of the flame where the system is stabilized.
In recent decades there has been a strong trend towards the use of lean premixed combustion in order to produce gas turbine systems that are compliant with air quality regulations. Additional growing interest in using alternative fuels has drawn many problems in terms of operational stability, thus there have been extensive investigations to achieve more stable and reliable combustion systems. Flame flashback has been one of the major instability problems that have the potential of causing considerable damage to the combustion system hardware in addition to significant increase of emissions such as CO and NOx. Swirl combustors are proven as effective flame stabilisers over wide range of operation conditions due to swirl structures which provide a low velocity region that enables flame anchoring. However the interaction between swirl structures and swirl burner geometries can considerably alter the stability regime downstream the burner exit plane. Using central injectors either as a central bluff body or to inject fuel diffusively have been used successfully to achieve wide stability limits and prevent upstream flame propagation. However, central injectors in swirl combustors can be subject to large amounts of heat, which can cause flashback, subsequently increasing maintenance cost and reducing the predicted operating life of the system. This paper present a series of experiments using a well-characterised tangential swirl burner to investigate the effect of using diffusive air injection on flow field characteristics and how it can affect the lower instability limits through altering the flashback mechanism by Combustion Induced Vortex Breakdown (CIVB). Results show that using diffusive air stream injection affects flashback trends significantly by providing a wider range of stability limits both in terms of equivalence ratio and mass flow rate which implies the possibility of working at higher power outputs compared to the case when using a central body injector. This technique can be considered a promising technology in terms of flexibility of operation because it enables switching to another air stream diameter while maintaining full load operation as opposed to the use of central body injectors.
This study characterizes the central recirculation zones formed under combustion conditions, with natural gas as fuel with different geometries and degrees of premixing using a swirl combustor firing into a confinement representative of gas turbine combustors. Phase-locked particle image velocimetry is used as the main method of characterization. The technique enables characterization of the time-dependent behavior of the central recirculation zone and a three-dimensional reconstruction of its boundaries. The central recirculation zone typically had an asymmetric lobed shape and precessed about the central axis. Partially premixed combustion at near-stoichiometric equivalence ratios reduced the coherence of the central recirculation zone and often caused it to nearly disappear, although a small remnant of recirculation could still be found in the three-dimensional space. Lower equivalence ratios strengthened the central recirculation zone considerably, for both non-premixed and partially premixed combustion. Although the central recirculation zone was asymmetric in shape and precessed about the central axis, the precessing vortex core, commonly found in these flows, was found to be significantly suppressed especially when central fuel injectors were used. Its occurrence then became intermittent and irregular. A quarl exit nozzle with a divergent lip was found to reduce flame attachment to the fuel injector.
Combustion instabilities are considered one of the most serious challenges for developing combustion systems through the years. Undesirable issues linked to these phenomena represent a risk for such systems especially in gas turbines and propulsion devices where the propagation of these instabilities can even lead to considerable damages. Flame flashback from the combustion chamber into premixer represents one of the most important combustion instability issue in swirl combustors used in gas turbines. This study proposes an experimental and numerical approach to validate the use of a central air injection in swirl combustors to reduce flame flashback propensity via controlling the turbulence generation at the tip of the flame while pushing the CRZ, thus retarding the appearance of the CIVB, to mitigate the progression of combustion into the system. Results showed the potential of this technique to affect turbulence generation and pushing back the flame into the combustion chamber, increasing operability limits. Very good agreement was achieved between experimental and numerical results, demonstrating that the use of injection through the central core of the system not only controls the position of the recirculation zone but also affects turbulence and mitigates other forms of flame flashback.
Swirl stabilized flows are the most widely deployed technology used to stabilize gas turbine combustion systems. However, there are some coherent structures that appear in these flows close to the nozzle whose occurrence and stability are still poorly understood during transition. The external recirculation zone and the Precessing Vortex Core to/from the Coanda effect are some of them. Thus, in this paper the transition of an Open Jet Flow-Medium Swirl flow pattern to/from a Coanda jet flow is studied using various geometries at a fixed Swirl number. Phase Locked Stereo Particle Image Velocimetry and High Speed Photography experiments were conducted to determine fundamental characteristics of the phenomenon. It was observed that the coherent structures in the field experience a complete annihilation during transition, with no dependency between the structures formed in each of the flow states. Moreover, transition occurs at a particular normalized step size whilst some acoustic shifts in the frequencies of the system were noticed, a phenomenon related to the strength of the vortical structures and vortices convection. It is concluded that a transient, precessing, Coanda Vortex Breakdown is formed, changing flow dynamics. The structure progresses to a less coherent Trapped Vortex between the two states. During the phenomenon there are different interactions between structures such as the Central Recirculation Zone, the High Momentum Flow Region and the Precessing Vortex Core that were also documented.
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Finding alternative value-added usage for glycerol is imperative as existing uses are inadequate due to the vast excesses of glycerol generated mainly as a result of increased biodiesel production. This paper explores a mid-term, cost-efficient, technically viable utilisation in power generation applications and exposes the nature of its combustion. Blended with methanol to avoid the heat loss and fuel coking problems associated with preheating, glycerol was combusted in a model swirl-stabilised gas turbine burner utilising a standard pressure-swirl injector for fuel atomisation. Stable flames resulting from the tested blends – 70/30 and 50/50 combinations of methanol/glycerol by volume – were achieved over an equivalence ratio (ER) range between 0.29 and 0.51. The upper and lower limits of stable operating ER for the 70/30 case were accompanied by significant flame lift-off from the nozzle exit orifice – a phenomenon that was not pronounced in the 50/50 case. Also, the temporal variation of CH* species integral intensity suggested a reduction in the fluctuation of heat release rate, hence better flame stability, as ER increased for both blends. Overall, the 50/50 case showed greater flame stability compared with the 70/30 case based on the CH* chemiluminescence data and spectral analysis by means of fast Fourier transform.