Hermann, J. ; Greifenstein, M. ; Böhm, B. ; Dreizler, A. (2019)
Experimental Investigation of Global Combustion Characteristics in an Effusion Cooled Single Sector Model Gas Turbine Combustor.
In: Flow, Turbulence and Combustion, 102 (4)
doi: 10.1007/s10494-018-9999-y
Artikel, Bibliographie
Kurzbeschreibung (Abstract)
This paper presents experimental investigations in an effusion cooled single sector gas turbine combustor under close-to-reality boundary conditions, i.e. elevated pressure and combustor inlet temperature, under varying staging conditions. Flow field, flame structure and gas-phase temperature measurements are performed using particle image velocimetry (PIV), planar laser induced fluorescence of the hydroxyl radical (OH-PLIF) and coherent anti-Stokes Raman scattering (CARS), respectively. Additionally, isothermal mixing of the pilot and main stage is investigated using Acetone-PLIF. The influence of the pilot on the measured quantities can be identified up to 30 mm downstream of the burner head plate. These measurements are conducted within a novel test rig dedicated to the investigation of swirl-stabilized pressurized flames and effusion-cooling. The rig features full optical access for non-intrusive laser diagnostics from three sides and a modular effusion liner geometry. Important process parameters can be controlled independently in a wide range, providing a high versatility and reliability in terms of boundary conditions. Oxidizer and cooling air mass flows can be conditioned independently to 773 K and 973 K, respectively. Fuel staging can be gradually varied between 0% (fully premixed) and 100% (pilot only) at thermal loads up to 150 kW and a maximum pressure of 1,0 MPa. A movable block radial swirler allows for varying geometrical swirl numbers.
| Typ des Eintrags: | Artikel |
|---|---|
| Erschienen: | 2019 |
| Autor(en): | Hermann, J. ; Greifenstein, M. ; Böhm, B. ; Dreizler, A. |
| Art des Eintrags: | Bibliographie |
| Titel: | Experimental Investigation of Global Combustion Characteristics in an Effusion Cooled Single Sector Model Gas Turbine Combustor |
| Sprache: | Englisch |
| Publikationsjahr: | April 2019 |
| Verlag: | Springer Science+Business Media B.V. |
| Titel der Zeitschrift, Zeitung oder Schriftenreihe: | Flow, Turbulence and Combustion |
| Jahrgang/Volume einer Zeitschrift: | 102 |
| (Heft-)Nummer: | 4 |
| DOI: | 10.1007/s10494-018-9999-y |
| Kurzbeschreibung (Abstract): | This paper presents experimental investigations in an effusion cooled single sector gas turbine combustor under close-to-reality boundary conditions, i.e. elevated pressure and combustor inlet temperature, under varying staging conditions. Flow field, flame structure and gas-phase temperature measurements are performed using particle image velocimetry (PIV), planar laser induced fluorescence of the hydroxyl radical (OH-PLIF) and coherent anti-Stokes Raman scattering (CARS), respectively. Additionally, isothermal mixing of the pilot and main stage is investigated using Acetone-PLIF. The influence of the pilot on the measured quantities can be identified up to 30 mm downstream of the burner head plate. These measurements are conducted within a novel test rig dedicated to the investigation of swirl-stabilized pressurized flames and effusion-cooling. The rig features full optical access for non-intrusive laser diagnostics from three sides and a modular effusion liner geometry. Important process parameters can be controlled independently in a wide range, providing a high versatility and reliability in terms of boundary conditions. Oxidizer and cooling air mass flows can be conditioned independently to 773 K and 973 K, respectively. Fuel staging can be gradually varied between 0% (fully premixed) and 100% (pilot only) at thermal loads up to 150 kW and a maximum pressure of 1,0 MPa. A movable block radial swirler allows for varying geometrical swirl numbers. |
| Fachbereich(e)/-gebiet(e): | 16 Fachbereich Maschinenbau 16 Fachbereich Maschinenbau > Fachgebiet Reaktive Strömungen und Messtechnik (RSM) |
| Hinterlegungsdatum: | 07 Okt 2019 07:39 |
| Letzte Änderung: | 14 Sep 2022 13:18 |
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