Numerical and Experimental Tests of Supersonic Inlet Utilizing a Pylon Set for Mixing, Combustion and Thrust Enhancement

Gilinsky, Mikhail; Khaikine, Vitali; Akyurtlu, Ates; Akyurtlu, Jale F.; Trexler, Carl A.; Baurle, Robert A.; Emami, Saied

doi:10.2514/6.2005-21

“…16,[18][19][20][21][22][27][28][29][30][31][32][33] Using pylons as fueling devices or components of fuel injection systems has also been studied by many researchers. 2,3,12,13,30,[34][35][36][37][38][39][40][41][42][43][44][45][46][47] The way pylons are utilized varies. In many instances pylons are used as shields for fuel injector ports.…”

Section: Introductionmentioning

confidence: 99%

Pylon Fuel Injector Design for a Scramjet Combustor

Doster¹,

King²,

Gruber³

et al. 2007

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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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 Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. 16. SECURITY CLASSIFICATION OF: 17. LIMITATION

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“…Recently, Gilinsky et al [15,16] and Akyurtlu et al [17] initiated experimental and computational studies using a supersonic inlet fitted with a series of pylons. Initial results from these investigations suggest that the pylons can enhance mixing before the fuel-air mixture reaches the combustor and that the pylons may improve certain aspects of inlet performance.…”

Section: Nomenclaturementioning

confidence: 99%

Experimental Studies of Pylon-Aided Fuel Injection into a Supersonic Crossflow

Gruber¹,

Carter²,

Montes³

et al. 2008

Journal of Propulsion and Power

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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 AFRL-RZ-WP-TP-2008-2170 SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSORING/MONITORING AGENCY ACRONYM(S)Air Force SPONSORING/MONITORING AGENCY REPORT NUMBER(S) AFRL-RZ-WP-TP-2008-2170 DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution unlimited. SUPPLEMENTARY NOTESPAO case number AFRL/WS07-0430, 28 February 2007. This is a work of the U.S. Government and is not subject to copyright protection in the United States. Document contains color. ABSTRACTAn investigation of the nonreacting flow associated with pylon-aided gaseous fuel injection into a Mach 2 crossflow is described. In this study, a small pylon was positioned just upstream of a circular flush-wall fuel injector. Three pylon geometries were studied, along with a no-pylon reference case. In all cases, a typical cavity-based flameholder was positioned downstream of the fuel injector. The injectant plume characteristics were interrogated using a variety of laser-based and probe-based measurement techniques. Planar laser-induced fluorescence of nitric oxide was used to study the instantaneous plume structure. Spontaneous vibrational Raman scattering provided time-averaged plume characteristics and mixing information. Probe-based instrumentation was used in conjunction with the mixing data to estimate the total pressure losses associated with each configuration. Each pylon had a unique influence on the fuel-injection plume. In all cases, the presence of the pylon resulted in improved fuel penetration into the supersonic crossflow without significantly changing the total pressure-loss characteristics. Mixing efficiencies of the pylonaided injection cases were not substantially different from the reference case. An investigation of the nonreacting flow associated with pylon-aided gaseous fuel injection into a Mach 2 crossflow is described. In this study, a small pylon was positioned just upstream of a circular flush-wall fuel injector. Three pylon geometries were studied, along with a no-pylon reference case. In all cases, a typical cavity-based flameholder was positioned downstream of the fuel injector. The injectant plume characteristics were interrogated using a variety of laser-based and probe-based measurement techniques. Planar laser-induced fluorescence of nitric oxide was used to study the instantaneous plume structure. Spontaneous vibrational Raman scattering provided time-averaged plume characteristics and mixing information. Probe-based instrumentation was u...

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A systematic literature review based on different fuel injection strategies used in scramjet combustors

Gugulothu

¹

2019

Heat Trans. Asian Res.

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A supersonic combustion ramjet engine is an airbreathing propulsive system aimed at futuristic hypersonic vehicles. The profound advantages observed in the area of defence applications has attracted researchers' attention towards improving the fluid flow dynamics of scramjet engines. The present effort summarizes the fundamental problems and latest advances in fuel injection techniques. Improvements and application of modern fuel injection technologies have a profound impact on the scramjet engine, increasing capacity in terms of flight speed, efficiency in fuel mixing, and combustion. The fuel injection system has a direct impact on the engine's combustion processes, determining the scramjet engine's thrust power and its flight speed. A systematic database including brief descriptions of mixing enhancement mechanisms was analyzed numerically and experimentally, identifying the needed and existing fuel injection strategies. The numerical and computational analysis directly related to the experimental investigations is also included. K E Y W O R D S cavity, propulsion system, scramjet, transverse injection, vortex generator T A B L E 4 Active communities and their focus of research StudiesResearch focus

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Numerical and Experimental Tests of Supersonic Inlet Utilizing a Pylon Set for Mixing, Combustion and Thrust Enhancement

Cited by 5 publications

References 4 publications

Pylon Fuel Injector Design for a Scramjet Combustor

Pylon Fuel Injector Design for a Scramjet Combustor

Experimental Studies of Pylon-Aided Fuel Injection into a Supersonic Crossflow

A systematic literature review based on different fuel injection strategies used in scramjet combustors

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