Investigation of differences in lean blowout of liquid single-component fuels in a gas turbine model combustor

2016 ◽  
Author(s):  
Jasper Grohmann ◽  
Bastian Rauch ◽  
Trupti Kathrotia ◽  
Wolfgang Meier ◽  
Manfred Aigner
Keyword(s):  
Gas Turbine ◽  
Single Component ◽  
Lean Blowout ◽  
Turbine Model

scholarly journals Influence of Single-Component Fuels on Gas-Turbine Model Combustor Lean Blowout

2018 ◽  
Vol 34 (1) ◽  
pp. 97-107 ◽  
Author(s):  
J. Grohmann ◽  
B. Rauch ◽  
T. Kathrotia ◽  
W. Meier ◽  
M. Aigner
Keyword(s):  
Gas Turbine ◽  
Single Component ◽  
Lean Blowout ◽  
Turbine Model

scholarly journals Dynamics of lean blowout of a swirl-stabilized flame in a gas turbine model combustor

2011 ◽  
Vol 33 (2) ◽  
pp. 2953-2960 ◽  
Author(s):  
M. Stöhr ◽  
I. Boxx ◽  
C. Carter ◽  
W. Meier
Keyword(s):  
Gas Turbine ◽  
Lean Blowout ◽  
Turbine Model

Dynamical Properties of Combustion Instability in a Laboratory-Scale Gas-Turbine Model Combustor

2016 ◽  
Vol 139 (4) ◽  
Author(s):  
Hiroshi Gotoda ◽  
Kenta Hayashi ◽  
Ryosuke Tsujimoto ◽  
Shohei Domen ◽  
Shigeru Tachibana
Keyword(s):  
Gas Turbine ◽  
Combustion Instability ◽  
Turbulent Flame ◽  
Surrogate Data ◽  
Permutation Entropy ◽  
Lean Blowout ◽  
Lean Premixed ◽  
Free Running ◽  
Nonlinear Forecasting ◽  
Turbine Model

We present an experimental study on the nonlinear dynamics of combustion instability in a lean premixed gas-turbine model combustor with a swirl-stabilized turbulent flame. Intermittent combustion oscillations switching irregularly back and forth between burst and pseudo-periodic oscillations exhibit the deterministic nature of chaos. This is clearly demonstrated by considering two nonlinear forecasting methods: an extended version (Gotoda et al., 2015, “Nonlinear Forecasting of the Generalized Kuramoto-Sivashinsky Equation,” Int. J. Bifurcation Chaos, 25, p. 1530015) of the Sugihara and May algorithm (Sugihara and May, 1990, “Nonlinear Forecasting as a Way of Distinguishing Chaos From Measurement Error in Time Series,” Nature, 344, pp. 734–741) as a local predictor, and a generalized radial basis function (GRBF) network as a global predictor (Gotoda et al., 2012, “Characterization of Complexities in Combustion Instability in a Lean Premixed Gas-Turbine Model Combustor,” Chaos, 22, p. 043128; Gotoda et al., 2016 (unpublished)). The former enables us to extract the short-term predictability and long-term unpredictability of chaos, while the latter can produce surrogate data to test for determinism by a free-running approach. The permutation entropy based on a symbolic sequence approach is estimated for the surrogate data to test for determinism and is also used as an online detector to prevent lean blowout.

Gas Turbine Model Combustor Emissions of Liquid Single-Component Fuels

2017 ◽  
Author(s):  
Jasper Grohmann ◽  
Wolfgang Meier ◽  
Manfred Aigner
Keyword(s):  
Gas Turbine ◽  
Mie Scattering ◽  
Single Component ◽  
Liquid Fuels ◽  
Phase Doppler Anemometry ◽  
Spray Flames ◽  
Linear Alkanes ◽  
Nitric Oxide Emissions ◽  
Chain Lengths ◽  
Turbine Model

Alternative liquid fuels can contain hydrocarbons of different types and chain lengths and the fuel composition has an influence on combustion behavior. In this study, the influence of liquid single-component fuels on exhaust gas emissions of a gas turbine model combustor for swirl-stabilized spray flames was investigated under atmospheric pressure. The nozzle exhibited a dual-swirl geometry and a prefilming airblast atomizer. The spray was characterized by Phase Doppler Anemometry (PDA) and Mie scattering measurements and the flame CH* chemiluminescence was measured. Six single-component hydrocarbons were chosen: three linear alkanes (n-hexane, n-nonane, n-dodecane), one cyclic alkane (cyclohexane), one branched alkane (iso-octane) and one aromatic hydrocarbon (toluene). Kerosene Jet A-1 was used as a technical reference. Results show minor differences in CO emissions and significant differences in NOx emissions of the various fuels at comparable flow conditions and adiabatic flame temperatures. The measurements indicate a correlation between the nitric oxide emissions and the spray quality.

Comparison of the Combustion Characteristics of Liquid Single-Component Fuels in a Gas Turbine Model Combustor

2016 ◽  
Author(s):  
Jasper Grohmann ◽  
William O’Loughlin ◽  
Wolfgang Meier ◽  
Manfred Aigner
Keyword(s):  
Gas Turbine ◽  
Alternative Fuels ◽  
Numerical Models ◽  
Flame Structure ◽  
Mie Scattering ◽  
Single Component ◽  
Liquid Fuels ◽  
Reacting Flow ◽  
Spray Flames ◽  
Turbine Model

Alternative production pathways for liquid fuels provide the opportunity to adjust the chemical composition of the product in order to improve combustion performance. In this study, flame characteristics of selected single-component fuels were investigated to provide a basis for a better understanding of the influence of specific fuel components on the combustion behaviour. The measurements were performed in a redesigned gas turbine model combustor for swirl-stabilised spray flames under atmospheric pressure. The combustor features a dual-swirl geometry and a prefilming airblast atomiser. The combustion chamber provides good optical access and yields well-defined boundary conditions. As part of different projects in the field of alternative fuels, two liquid single-component fuels (n-hexane, n-dodecane) and kerosene Jet A-1 were investigated. Flow fields of the nonreacting and reacting flow were measured using stereo particle image velocimetry. The flame structure and spray distribution were derived from CH* chemiluminescence and Mie scattering respectively. Lean blowout limits were measured. Results show noticeable differences in combustion behaviour of the chosen fuels at comparable flow conditions. Furthermore, the results provide a detailed data base for the validation of numerical models.

Dynamical Properties of Combustion Instability in a Laboratory-Scale Gas-Turbine Model Combustor

2016 ◽  
Author(s):  
Hiroshi Gotoda ◽  
Kenta Hayashi ◽  
Ryosuke Tsujimoto ◽  
Shohei Domen ◽  
Shigeru Tachibana
Keyword(s):  
Gas Turbine ◽  
Radial Basis Function Network ◽  
Combustion Instability ◽  
Turbulent Flame ◽  
Surrogate Data ◽  
Permutation Entropy ◽  
Lean Blowout ◽  
Free Running ◽  
Turbine Model

We present an experimental study on nonlinear dynamics of combustion instability in a lean premixed gas-turbine model combustor with a swirl-stabilized turbulent flame. Intermittent combustion oscillations switching irregularly back and forth between a burst and pseudo-periodic oscillations exhibit the deterministic nature of chaos. This is clearly demonstrated by considering two nonlinear forecasting methods: the extended version [1] of the Sugihara & May algorithm [2] as a local predictor, and the generalized radial basis function network as a global predictor [3], [4]. The former enables us to extract the short-term predictability and long-term unpredictability nature of chaos, while the latter can produce surrogate data to test for determinism as a free running approach. Permutation entropy is estimated by a symbolic sequence approach for the surrogate data to test for determinism and is also used as an online detector to prevent lean blowout.

Plasma-Assisted Combustor Dynamics Control at Ambient and Realistic Gas Turbine Conditions

2017 ◽  
Author(s):  
Wookyung Kim ◽  
Jeffrey Cohen
Keyword(s):  
Gas Turbine ◽  
Ambient Pressure ◽  
Plasma Discharge ◽  
Inlet Temperature ◽  
Pulsed Plasma ◽  
Plasma Power ◽  
Lean Blowout ◽  
Wide Range ◽  
Baseline Temperature ◽  
Increasing Temperature

The central objective of this study is to investigate the effectiveness of implementing a plasma discharge to improve combustor dynamics and flame stability. Specifically, a nano-second pulsed plasma discharge (NSPD) was applied to a premixed gaseous fuel/air dump combustor for mitigation of dynamic combustion instabilities with a minimal NOX penalty. This paper addresses the scaling of this technology from ambient pressure and temperature conditions to more realistic gas turbine combustor conditions. A model combustor operating at representative conditions of O (102) m/s flow velocity, ∼ 580 K combustor inlet temperature, and ∼ 5 atm in-combustor pressure was selected to simulate a typical low-power environment of future aero engine gas turbine combustors. Fully premixed methane or propane was utilized as a fuel. Similar to a previous ambient-pressure study, a significant reduction of pressure fluctuation level was observed, by a factor of 2X to 4X over a wide range of velocity at the baseline temperature and pressure. The plasma power required for the reduction increased linearly with increasing velocity. The change of fuel from methane to propane showed that propane requires significantly (2X) higher plasma power to achieve a similar level of noise reduction. It was also observed that the lean blowout (LBO) limit was significantly extended in the presence of the plasma, however, substantial incomplete combustion occurs in the extended regime. NOX measurements showed that the incremental NOX production due to the presence of the plasma was low (∼ < 1EINOX) in general, however, it increased with decreasing velocity and pressure, and increasing temperature.

Sign in / Sign up

Export Citation Format

Share Document