C134 Flame stabilization mechanism of coaxial oxygen-jet diffusion flame in a high-pressure environment

2012 ◽  
Vol 2012 (0) ◽  
pp. 93-94
Author(s):  
Shun Shirakawa ◽  
Manabu Kumagami ◽  
Taku Kudo ◽  
Hideaki Kobayashi
Keyword(s):  
High Pressure ◽  
Diffusion Flame ◽  
Flame Stabilization ◽  
Stabilization Mechanism ◽  
High Pressure Environment

Flow Field and Hot Streak Migration Through a High Pressure Cooled Vanes With Representative Lean Burn Combustor Outflow

2018 ◽  
Vol 141 (4) ◽  
Author(s):  
Tommaso Bacci ◽  
Tommaso Lenzi ◽  
Alessio Picchi ◽  
Lorenzo Mazzei ◽  
Bruno Facchini
Keyword(s):  
Experimental Data ◽  
High Pressure ◽  
Flow Field ◽  
Fuel Injection ◽  
Leading Edge ◽  
Flame Stabilization ◽  
Lean Burn ◽  
Aero Engine ◽  
University Of Florence ◽  
Hot Streak

Modern lean burn aero-engine combustors make use of relevant swirl degrees for flame stabilization. Moreover, important temperature distortions are generated, in tangential and radial directions, due to discrete fuel injection and liner cooling flows respectively. At the same time, more efficient devices are employed for liner cooling and a less intense mixing with the mainstream occurs. As a result, aggressive swirl fields, high turbulence intensities, and strong hot streaks are achieved at the turbine inlet. In order to understand combustor-turbine flow field interactions, it is mandatory to collect reliable experimental data at representative flow conditions. While the separated effects of temperature, swirl, and turbulence on the first turbine stage have been widely investigated, reduced experimental data is available when it comes to consider all these factors together.In this perspective, an annular three-sector combustor simulator with fully cooled high pressure vanes has been designed and installed at the THT Lab of University of Florence. The test rig is equipped with three axial swirlers, effusion cooled liners, and six film cooled high pressure vanes passages, for a vortex-to-vane count ratio of 1:2. The relative clocking position between swirlers and vanes has been chosen in order to have the leading edge of the central NGV aligned with the central swirler. In order to generate representative conditions, a heated mainstream passes though the axial swirlers of the combustor simulator, while the effusion cooled liners are fed by air at ambient temperature. The resulting flow field exiting from the combustor simulator and approaching the cooled vane can be considered representative of a modern Lean Burn aero engine combustor with swirl angles above ±50 deg, turbulence intensities up to about 28% and maximum-to-minimum temperature ratio of about 1.25. With the final aim of investigating the hot streaks evolution through the cooled high pressure vane, the mean aerothermal field (temperature, pressure, and velocity fields) has been evaluated by means of a five-hole probe equipped with a thermocouple and traversed upstream and downstream of the NGV cascade.

Experimental Investigation of CH4/Air Inverse Diffusion Flame Stabilization by Nonequilibrium Plasma

2019 ◽  
Vol 35 (6) ◽  
pp. 1151-1162
Author(s):  
Wansheng Nie ◽  
Siyin Zhou ◽  
Tianyi Shi ◽  
Tikai Zheng ◽  
Xueke Che
Keyword(s):  
Experimental Investigation ◽  
Diffusion Flame ◽  
Nonequilibrium Plasma ◽  
Flame Stabilization ◽  
Inverse Diffusion ◽  
Inverse Diffusion Flame

Optical access to the large volume, high pressure environment

1998 ◽  
Vol 69 (7) ◽  
pp. 2802-2803 ◽  
Author(s):  
R. A. Secco ◽  
P. S. Balog
Keyword(s):  
High Pressure ◽  
Large Volume ◽  
Optical Access ◽  
High Pressure Environment

Investigation of Combustor-Turbine-Interaction in a Rotating Cooled Transonic High-Pressure Turbine Test Rig: Part 2 — Numerical Modelling and Simulation

2019 ◽  
Author(s):  
Simon Gövert ◽  
Federica Ferraro ◽  
Alexander Krumme ◽  
Clemens Buske ◽  
Marc Tegeler ◽  
...  
Keyword(s):  
High Pressure ◽  
Flame Stabilization ◽  
Test Facility ◽  
Test Rig ◽  
High Pressure Turbine ◽  
Lean Burn ◽  
Turbine Inlet ◽  
Measurement Results ◽  
Aero Engine ◽  
Inlet Conditions

Abstract Reducing the uncertainties in the prediction of turbine inlet conditions is a crucial aspect to improve aero engine designs and further increase engine efficiencies. To meet constantly stricter emission regulations, lean burn combustion could play a key role for future engine designs. However, these combustion systems are characterized by significant swirl for flame stabilization and reduced cooling air mass flows. As a result, substantial spatial and transient variations of the turbine inlet conditions are encountered. To investigate the effect of the combustor on the high pressure turbine, a rotating cooled transonic high-pressure configuration has been designed and investigated experimentally at the DLR turbine test facility ‘NG-Turb’ in Göttingen, Germany. It is a rotating full annular 1.5 stage turbine configuration which is coupled to a combustor simulator. The combustor simulator is designed to create turbine inlet conditions which are hydrodynamically representative for a lean-burn aero engine. A detailed description of the test rig and its instrumentation as well as a discussion of the measurement results is presented in part I of this paper. Part II focuses on numerical modeling of the test rig to further extend the understanding of the measurement results. Integrated simulations of the configuration including combustor simulator and nozzle guide vanes are performed for leading edge and passage clocking position and the effect on the hot streak migration is discussed. The simulation and experimental results at the combustor-turbine interface are compared showing a good overall agreement. The relevant flow features are correctly predicted in the simulations, proving the suitability of the numerical model for application to integrated combustor-turbine interaction analysis.

Experimental study of CO2 corn stover char gasification using iron nitrate as a catalyst under a high-pressure environment

Fuel ◽  
2020 ◽  
Vol 267 ◽  
pp. 117237 ◽  
Author(s):  
Rathziel Roncancio ◽  
Mehmed S. Ulcay ◽  
Jorge E. Arango ◽  
Jay P. Gore
Keyword(s):  
Experimental Study ◽  
High Pressure ◽  
Corn Stover ◽  
Iron Nitrate ◽  
Char Gasification ◽  
High Pressure Environment

scholarly journals Combustion states distinction of the methane/oxygen laminar co-flow diffusion flame at high pressure

Fuel ◽  
2019 ◽  
Vol 243 ◽  
pp. 221-229 ◽  
Author(s):  
Yifei Ge ◽  
Sen Li ◽  
Xiaolin Wei
Keyword(s):  
High Pressure ◽  
Diffusion Flame
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