The Behavior of an Ultra-Compact Combustor (UCC) Based on Centrifugally-Enhanced Turbulent Burning Rates

Zelina, Joseph; Sturgess, G. J.; Shouse, Dale T.

doi:10.2514/6.2004-3541

Cited by 48 publications

(42 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The turbine inter-guide-vane burner (TIB) engines, compared to the conventional non-reheat engines, are shown to have a higher specific thrust with no or only small increase in thrust specific fuel consumption. High-G loading (jet-swirl flow scheme) has been researched for several years by the Air Force Research Laboratory [8][9][10][11], and several experiments as well as numerical studies on the ultra compact combustor using a fueled cavity type flame holder in a turbine guide vane, with an angled injection of air and fuel from the outer casing, have been carried out. The ability to achieve short and efficient flames was demonstrated in these studies.…”

Section: Introductionmentioning

confidence: 99%

Effect of Secondary Jet-flow Angle on Performance of Turbine Inter-guide-vane Burner Based on Jet-vortex Flow

Zheng

Tang

et al. 2014

International Journal of Turbo &Amp; Jet-Engines

View full text Add to dashboard Cite

Four different secondary airflow angles for the turbine inter-guide-vane burners with trapped vortex cavity were designed. Comparative analysis between combustion performances influenced by the variation of secondary airflow angle was carried out by using numerical simulation method. The turbulence was modeled using the Scale-Adaptive Simulation (SAS) turbulence model. Four cases with different secondary jet-flow angles (-45°, 0°, 30°, 60°) were studied. It was observed that the case with secondary jet-flows at 60° angle directed upwards (1) has good mixing effect; (2) mixing effect is the best although the flow field distributions inside both of the cavity and the main flow passage for the four models are very similar; (3) has complete combustion and symmetric temperature distribution on the exit section of guide vane (X = 70 mm), with uniform temperature distribution, less temperature gradient, and shrank local high temperature regions in the notch located on the guide vane.

show abstract

Section: Introductionmentioning

confidence: 99%

Effect of Secondary Jet-flow Angle on Performance of Turbine Inter-guide-vane Burner Based on Jet-vortex Flow

Zheng

Tang

et al. 2014

International Journal of Turbo &Amp; Jet-Engines

View full text Add to dashboard Cite

show abstract

“…Studies on the UCC are underway at the Air Force Research Laboratory, Wright-Patterson Air Force Base, Ohio (29,53,54). This type of combustor incorporates several of the principles of the turbine burner, and the UCC also provides a major point of interaction between our project and AFRL.…”

Section: Ultra Compact Combustor (Ucc)mentioning

confidence: 99%

Turbine Burners: Flameholding in Accelerating Flow

Sirignano¹,

Dunn‐Rankin²,

Liu³

et al. 2009

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

A review of turbine-burner research and some relevant background issues is presented. Previous work on thermal cycle analysis for augmentative combustion in the passages of the turbine on a turbojet or turbofan engine is discussed, identifying the potential for improvement in performance. Previous researches on reacting mixing layers in accelerating flows, flameholding in high-speed flows, and various types of compact combustors are reviewed. An overview is given of experimental and computational research at UCI on the use of cavities to stabilize flames in accelerating and turning flows. Some indications for optimizing the cavity design are presented. Effects of the cavity length and depth, injection orientation for fuel and air into the cavity, and Reynolds number magnitude are discussed. The needs for future work are identified.

show abstract

“…The idea is to burn rich in the circumferential cavity, allowing much of the required combustion residence time to take place in the circumferential direction of the engine, rather than the axial as is done conventionally. The flow within this cavity will be swirled to generate high "g" loading and improve fuel-air mixing 4,8 . Flame stabilization occurs as combustion products are recirculated in the cavity.…”

Section: Introductionmentioning

confidence: 99%

“…These systems employ improved mixing devices, geometric features to expand combustor operability 1,2,3 , and dramatic changes to combustor flowfields to reduce combustor size and pollutant emissions [4][5][6][7][8] . This paper focuses on vortexstabilized combustor technologies that can enable the design of compact, high-performance combustion systems.…”

Section: Introductionmentioning

confidence: 99%

Operability and Efficiency Performance of Ultra-Compact, High Gravity (g) Combustor Concepts (Postprint)

Zelina¹,

Greenwood²,

Shouse³

2007

Self Cite

View full text Add to dashboard Cite

The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Department of Defense, Washington Headquarters Services, Directorate for Information SPONSORING/MONITORING AGENCY REPORT NUMBER(S) AFRL-PR-WP-TP-2007-235 DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution unlimited. SUPPLEMENTARY NOTESConference paper published in the Proceedings of ASME TURBO EXPO '06. This is a work of the U.S. Government and is not subject to copyright protection in the United States. PAO Case Number: AFRL/WS 05-1781, 23 Aug 2005. ABSTRACTThis paper presents a parametric design study of the Ultra-Compact Combustor (UCC), a novel design based on trapped-vortex combustor (TVC) work that uses high swirl in a circumferential cavity to enhance reaction rates via high cavity g-loading on the order of 3000 g's. Increase in reaction rates translates to a reduced combustor volume. Three combustor geometric features were varied during experiments which included (1) high-g cavity flame-holding method, (2) high-g cavity to main airflow transport method, and (3) fuel injection method. Experimental results are presented for these combustor configurations and results have shown promise for advanced engine applications. Lean blowout fuel-air ratio limits at 25-50% the value of current systems were demonstrated. Combustion efficiency was measured over a wide range of UCC operating conditions. This data begins to build the design space required for future engine designs that may use these novel, compact, high-g combustion systems. Proceedings of ASME TURBO EXPO '06: 51 th ASME International Gas Turbine and Aeroengine Congress and Exposition May 2006, Barcelona, Spain SUBJECT TERMS GT2006-90119 OPERABILITY AND EFFICIENCY PERFORMANCE OF ULTRA-COMPACT, HIGH GRAVITY (g) COMBUSTOR CONCEPTSJ. Zelina, R. T. Greenwood, and D. T. Shouse Air Force Research Laboratory WPAFB, OH ABSTRACT Future gas turbine engines are required to be more capable than their predecessors. This often implies severe demands on the engine that translate into increasing compressor and combustor exit temperatures, higher combustion pressures and higher fuel/air ratio combustors with greater turn-down ratios (wider operating limits between idle and maximum power conditions). Major advances in combustor technology are required to meet the conflicting challenges of improving performance, increasing durability and maintaining cost. Unconventional combustor configurations are one promising approach to address these challenges. Ultra-short combustors to minimize residence time, with special flame-holding mechanisms to cope with increased through-velocities a...

show abstract

The Behavior of an Ultra-Compact Combustor (UCC) Based on Centrifugally-Enhanced Turbulent Burning Rates

Cited by 48 publications

References 7 publications

Effect of Secondary Jet-flow Angle on Performance of Turbine Inter-guide-vane Burner Based on Jet-vortex Flow

Effect of Secondary Jet-flow Angle on Performance of Turbine Inter-guide-vane Burner Based on Jet-vortex Flow

Turbine Burners: Flameholding in Accelerating Flow

Operability and Efficiency Performance of Ultra-Compact, High Gravity (g) Combustor Concepts (Postprint)

Contact Info

Product

Resources

About