Vortex combustor concept for gas turbine engines

Roquemore, W. M.; Shouse, Dale T.; Burrus, D.; Johnson, A. W.; Cooper, Clayton S.; Duncan, B. S.; Hsu, Kuang–Yu; Katta, Viswanath R.; Sturgess, G. J.; Vihinen, I.

doi:10.2514/6.2001-483

Cited by 70 publications

(50 citation statements)

References 16 publications

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“…The second critical design feature involves transporting and mixing the heat from the vortex, or cavity, region into the main flow. As described in previous work (Roquemore et al 1999; Roquemore et al 2001), this is generally accomplished by using wake regions generated by bodies, or struts, immersed in the main flow. This approach ignites the incoming fuel-air mixture by lateral mixing, instead of a back-mixing process.…”

Section: A-4mentioning

confidence: 99%

“…In the early 1990s, Hsu et al (1998) proposed using this feature to stabilize reactions in gas turbine combustors for aeropropulsion applications. Since then, several papers ; Roquemore et al 2001) and patents (Roquemore et al 1999) have described the results from using this AVC concept to achieve stable and low emission combustor results. However, in the years prior to 2002, AVC efforts have focused primarily on aero-propulsion applications.…”

Section: Introductionmentioning

confidence: 99%

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Design and Fabrication of a 400kW Pre-Prototype Engine

Williams¹

2006

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Section: A-4mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Design and Fabrication of a 400kW Pre-Prototype Engine

Williams¹

2006

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“…Figure 16 shows a comparison of the φ cav value at blowout for the high pressure and atmospheric pressure data, along with data from the TVC 1 . Of interest is the fact that the UCC and TVC have very similar LBO performance.…”

Section: Figure 15: Pressure Effects On Combustion Efficiency As a Fumentioning

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

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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...

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“…The performance indicators of aircraft, such as thrust weight ratio, economic efficiency and control performance, raise higher requirements for aircraft engines [1][2][3]. These requirements bring the need for more adjustable variables in the engines, which means the engine control system has multi-inputs and multi-outputs.…”

Section: Introductionmentioning

confidence: 99%

A New Robust Tracking Control Design for Turbofan Engines: H∞/Leitmann Approach

et al. 2017

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In this paper, a H ∞ /Leitmann approach to the robust tracking control design is presented for an uncertain dynamic system. This new method is developed in the following two steps. Firstly, a tracking dynamic system with simultaneous consideration of parameter uncertainty and noise is modeled based on a linear system and a reference model. Accordingly, a "nominal system" from the tracking system is defined and controlled by a H ∞ control to obtain the asymptotical stability and noise resistance. Secondly, by making use of a Lyapunov function and the norm boundedness, a new robust control with the "Leitmann approach" is designed to cope with the uncertainty. The two controls collaborate with each other to achieve "uniform tracking boundedness" and "uniform ultimate tracking boundedness". The new approach is then applied to an aircraft turbofan control design, and the numerical simulation results show the prescribed performances of the closed-loop system and the advantage of the developed approach.

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Vortex combustor concept for gas turbine engines

Cited by 70 publications

References 16 publications

Design and Fabrication of a 400kW Pre-Prototype Engine

Design and Fabrication of a 400kW Pre-Prototype Engine

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

A New Robust Tracking Control Design for Turbofan Engines: H∞/Leitmann Approach

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