Skip to Main Content
 

Global Search Box

 
 
 
 

Files

File List


ucin1177032411.pdf (7.3 MB)

ETD Abstract Container

Abstract Header

PERFORMANCE AND ENVIRONMENTAL IMPACT ASSESSMENT OF PULSE DETONATION BASED ENGINE SYSTEMS

GLASER, AARON J.
http://rave.ohiolink.edu/etdc/view?acc_num=ucin1177032411

Abstract Details

2007, PhD, University of Cincinnati, Engineering : Aerospace Engineering.
Experimental research was performed to investigate the feasibility of using pulse detonation based engine systems for practical aerospace applications. In order to carry out this work a new pulse detonation combustion research facility was developed at the University of Cincinnati. This research covered two broad areas of application interest. The first area is pure PDE applications where the detonation tube is used to generate an impulsive thrust directly. The second focus area is on pulse detonation based hybrid propulsion systems. Within each of these areas various studies were performed to quantify engine performance. Comparisons of the performance between detonation and conventional deflagration based engine cycles were made. Fundamental studies investigating detonation physics and flow dynamics were performed in order to gain physical insight into the observed performance trends. Experimental studies were performed on PDE-driven straight and diverging ejectors to determine the system performance. Ejector performance was quantified by thrust measurements made using a damped thrust stand. The effects of PDE operating parameters and ejector geometric parameters on thrust augmentation were investigated. For all cases tested, the maximum thrust augmentation is found to occur at a downstream ejector placement. The optimum ejector geometry was determined to have an overall length of LEJECT/DEJECT=5.61, including an intermediate-straight section length of LSTRT/DEJECT=2, and diverging exhaust section with 4 deg half-angle. A maximum thrust augmentation of 105% was observed while employing the optimized ejector geometry and operating the PDE at a fill-fraction of 0.6 and a frequency of 10 Hz. When operated at a fill-fraction of 1.0 and a frequency of 30 Hz, the thrust augmentation of the optimized PDE-driven ejector system was observed to be 71%. Static pressure was measured along the interior surface of the ejector, including the inlet and exhaust sections. The diverging ejector pressure distribution shows that the diverging section acts as a subsonic diffuser. To provide a better explanation of the observed performance trends, shadowgraph images of the detonation wave and starting vortex interacting with the ejector inlet were obtained. The acoustic signature of a pulse detonation engine was characterized in both the near-field and far-field regimes. Experimental measurements were performed in an anechoic test facility designed for jet noise testing. Both shock strength and speed were mapped as a function of radial distance and direction from the PDE exhaust plane. It was found that the PDE generated pressure field can be reasonably modeled by a theoretical point-source explosion. The effect of several exit nozzle configurations on the PDE acoustic signature was studies. These included various chevron nozzles, a perforated nozzle, and a set of proprietary noise attenuation mufflers. Experimental studies were carried out to investigate the performance of a hybrid propulsion system integrating an axial flow turbine with multiple pulse detonation combustors. The integrated system consisted of a circular array of six pulse detonation combustor (PDC) tubes exhausting through an axial flow turbine. Turbine component performance was quantified by measuring the amount of power generated by the turbine section. Direct comparisons of specific power output and turbine efficiency between a PDC-driven turbine and a turbine driven by steady-flow combustors were made. It was found that the PDC-driven turbine had comparable performance to that of a steady-burner-driven turbine across the operating map of the turbine.
Dr. Ephraim Gutmark (Advisor)
241 p.
Pulse Detonation Engines

Recommended Citations

Citations

  • GLASER, A. J. (2007). PERFORMANCE AND ENVIRONMENTAL IMPACT ASSESSMENT OF PULSE DETONATION BASED ENGINE SYSTEMS [Doctoral dissertation, University of Cincinnati]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1177032411

    APA Style (7th edition)

  • GLASER, AARON. PERFORMANCE AND ENVIRONMENTAL IMPACT ASSESSMENT OF PULSE DETONATION BASED ENGINE SYSTEMS. 2007. University of Cincinnati, Doctoral dissertation. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=ucin1177032411.

    MLA Style (8th edition)

  • GLASER, AARON. "PERFORMANCE AND ENVIRONMENTAL IMPACT ASSESSMENT OF PULSE DETONATION BASED ENGINE SYSTEMS." Doctoral dissertation, University of Cincinnati, 2007. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1177032411

    Chicago Manual of Style (17th edition)

ucin1177032411
1,093
© 2007, all rights reserved.
This open access ETD is published by University of Cincinnati and OhioLINK.