Jackson, S. I. and Shepherd, J. E. (2002) The Development of a Pulse Detonation Engine Simulator Facility. California Institute of Technology , Pasadena, CA. (Unpublished) http://resolver.caltech.edu/CaltechGALCITFM:2002.006
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A facility has been constructed to simulate the flow in a pulse detonation engine. This report describes the design, construction, initial test results, and analyses of the basic operation of the facility. The principle of operation is that of a blow down wind tunnel with a pressurized supply reservoir of air emptying through a test section into a low pressure receiver vessel. The flow is started abruptly by rupturing a diaphragm that separates the downstream end of the test section from the receiver vessel. Following a short transient period of a wave propagation, a quasi-steady flow is set up in the rectangular test section of 100 x 100 mm cross section. The quasi-steady operation lasts about 0.15 s. During this time, a typical operating condition results in a test section Mach number of about 0.7 and a velocity of 200 m/s. The pressure and temperature in the test section can be adjusted by varying the conditions in the supply reservoir. The current implementation uses room temperature air at pressures up to 6 bar in the supply reservoir. Tests were carried out to determine the performance as a function of the pressures in the supply and receiver vessel. Measurements included pressure and temperature in the two vessels and pitot and static probe measurements of the test section flow. Flow visualization with a schlieren system was also carried out. The data were analyzed by using simple one-dimensional steady and unsteady gas dynamics. Some two-dimensional unsteady numerical simulations were also carried out to examine the influence of the diaphragm location on the flow starting process. A control-volume model has been developed to predict the variation of pressure with time in the supply and receiver vessels. This model and analyses of the tests indicates that choked flow results in a constant Mach number inside the test section. The duration of the choked flow regime and the conditions within the test section can be reliably estimated with this model.
|Item Type:||Report or Paper (Technical Report)|
|Additional Information:||December 16, 2002 (Revised August 18, 2003) This work was carried out under P.O. No. 00-592 for Advanced Projects Research, Inc. under AF contract F04611-99-C-0017. Contract administration, mechanical design, and fabrication of the major components of the facility including the test section, test section and driver supports, transition section, inlet nozzle and coupling to the driver tank, were carried out by Advanced Projects Research, Inc. Key participants from APRI included Toby Rossmann, Jay Marsh, Keith Robinson, Kevin Moore, and Tom Sobota. Toby Rossmann was the on-site representative who shouldered the primary responsibility for day-to-day interactions between our organizations and he worked together with Scott Jackson to finalize the assembly and carry out the tests. Hans Hornung carried out the numerical simulations with Amrita that are shown in Chapter 2.2 and we thank him for his willingness to undertake this task without remuneration.|
|Group:||Graduate Aeronautical Laboratories (Fluid Mechanics)|
|Usage Policy:||You are granted permission for individual, educational, research and non-commercial reproduction, distribution, display and performance of this work in any format.|
|Deposited By:||Imported from CaltechGALCITFM|
|Deposited On:||20 Oct 2006|
|Last Modified:||25 Feb 2014 20:51|
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