An innovative design of a gas turbine annular combustor is investigated analytically and numerically. Its principal feature is the helical arrangement of the burners around the turbine shaft. Hence, a shorter combustor with lower aerodynamic losses and cooling air demand might be realized. A generic model of the combustor is developed and analyzed by means of a parametric study. Scaling laws for the geometry of the flame tube and the burners are derived. Thereby, the relevant similarity parameters for fluid flow, combustion, and heat transfer are maintained constant. Subsequently, nonreacting and reacting flow regimes of selected design variants are numerically investigated. It is shown that a double annular (DA) configuration with a tilting angle of β = 45 deg, where circumferentially adjacent swirls are corotating and radially are counter-rotating, is the superior design in terms of (1) maintaining the relevant similarity rules, (2) size and location of the recirculation zones and swirl flames, and (3) flow pattern at the combustor exit. The deflection angle of the nozzle guide vanes (NGV) as well as the axial length of such a short helical combustor (SHC) could be reduced by approximately 30%.
Skip Nav Destination
Article navigation
March 2016
Research-Article
Short Helical Combustor: Concept Study of an Innovative Gas Turbine Combustor With Angular Air Supply
B. Ariatabar,
B. Ariatabar
Institute of Thermal Turbomachinery,
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
e-mail: ariatabar@kit.edu
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
e-mail: ariatabar@kit.edu
Search for other works by this author on:
R. Koch,
R. Koch
Institute of Thermal Turbomachinery,
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
Search for other works by this author on:
H.-J. Bauer,
H.-J. Bauer
Institute of Thermal Turbomachinery,
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
Search for other works by this author on:
D.-A. Negulescu
D.-A. Negulescu
Senior Fellow
Aerothermal Systems,
Rolls-Royce Deutschland Ltd. & Co. KG,
Eschenweg 11,
Dahlewitz 15827, Germany
Aerothermal Systems,
Rolls-Royce Deutschland Ltd. & Co. KG,
Eschenweg 11,
Dahlewitz 15827, Germany
Search for other works by this author on:
B. Ariatabar
Institute of Thermal Turbomachinery,
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
e-mail: ariatabar@kit.edu
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
e-mail: ariatabar@kit.edu
R. Koch
Institute of Thermal Turbomachinery,
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
H.-J. Bauer
Institute of Thermal Turbomachinery,
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
Karlsruhe Institute of Technology (KIT),
Kaiserstr. 12,
Karlsruhe 76131, Germany
D.-A. Negulescu
Senior Fellow
Aerothermal Systems,
Rolls-Royce Deutschland Ltd. & Co. KG,
Eschenweg 11,
Dahlewitz 15827, Germany
Aerothermal Systems,
Rolls-Royce Deutschland Ltd. & Co. KG,
Eschenweg 11,
Dahlewitz 15827, Germany
1Corresponding author.
Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 14, 2015; final manuscript received August 4, 2015; published online September 22, 2015. Editor: David Wisler.
J. Eng. Gas Turbines Power. Mar 2016, 138(3): 031503 (10 pages)
Published Online: September 22, 2015
Article history
Received:
July 14, 2015
Revised:
August 4, 2015
Citation
Ariatabar, B., Koch, R., Bauer, H., and Negulescu, D. (September 22, 2015). "Short Helical Combustor: Concept Study of an Innovative Gas Turbine Combustor With Angular Air Supply." ASME. J. Eng. Gas Turbines Power. March 2016; 138(3): 031503. https://doi.org/10.1115/1.4031362
Download citation file:
Get Email Alerts
Shape Optimization of an Industrial Aeroengine Combustor to reduce Thermoacoustic Instability
J. Eng. Gas Turbines Power
Dynamic Response of A Pivot-Mounted Squeeze Film Damper: Measurements and Predictions
J. Eng. Gas Turbines Power
Review of The Impact Of Hydrogen-Containing Fuels On Gas Turbine Hot-Section Materials
J. Eng. Gas Turbines Power
Effects of Lattice Orientation Angle On Tpms-Based Transpiration Cooling
J. Eng. Gas Turbines Power
Related Articles
Damkohler Number Analysis in Lean Blow-Out of Toroidal Jet Stirred Reactor
J. Eng. Gas Turbines Power (October,2018)
A Large-Eddy Simulation–Linear-Eddy Model Study of Preferential Diffusion Processes in a Partially Premixed Swirling Combustor With Synthesis Gases
J. Eng. Gas Turbines Power (March,2017)
Stabilization Mechanisms of Swirling Premixed Flames With an Axial-Plus-Tangential Swirler
J. Eng. Gas Turbines Power (August,2018)
Linearized Euler Equations for the Prediction of Linear High-Frequency Stability in Gas Turbine Combustors
J. Eng. Gas Turbines Power (March,2017)
Related Chapters
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Flow and Heat Transfer Characteristics in the Finned Back Turn Channel of a Natural Gas Combustor
Inaugural US-EU-China Thermophysics Conference-Renewable Energy 2009 (UECTC 2009 Proceedings)
Alternative Systems
Turbo/Supercharger Compressors and Turbines for Aircraft Propulsion in WWII: Theory, History and Practice—Guidance from the Past for Modern Engineers and Students