Progress Report on the APTU Upgrade Activities

Garrard, Doug; Rigney, Sharon; Bates, Brent L.

doi:10.2514/6.2004-2496

Cited by 6 publications

(2 citation statements)

References 3 publications

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“…(4) The scramjet fuel feed was cut off while vitiated air was supplied into the scramjet combustor. (5) The test terminated as the VAH gas supply valve closed. The room-temperature GN 2 was supplied for purge.…”

Section: Scramjet Combustor Preliminary Test: Forced Ignitionmentioning

confidence: 99%

“…Abundant experimental studies have used a blowdown-type facility. An aerodynamic and propulsion test unit (APTU) was constructed and tested by Garrard et al The APTU produced vitiated air using a butane and liquid oxygen sudden-expansion burner and provided a Mach number of 4.5, a total pressure of 2.07 MPa, a total temperature of 1111 K, and 12 min of test duration [5]. Meng et al constructed a variable Mach number direct-connected supersonic combustor test facility using a heater.…”

Section: Introductionmentioning

confidence: 99%

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A Study on a Vitiated Air Heater for a Direct-Connect Scramjet Combustor and Preliminary Test on the Scramjet Combustor Ignition

Lee

Han

et al. 2023

Aerospace

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Vitiation air heater (VAH) combustion characteristics for a direct-connect scramjet combustor (DCSC) were experimentally studied. The VAH consists of a head, modular chamber, and circular-to-rectangular shape transition (CRST) nozzle. The CRST nozzle transforms the circular cross-sectioned rocket-type VAH into a rectangular cross-sectioned scramjet combustor. The CRST nozzle exit Mach numbers at the top, middle, and bottom were measured using a tungsten wedge. The oblique shock formed by the wedge was captured using Schlieren visualization and recorded with a high-speed camera. The θ-β-M relation showed that the exit Mach number was 2.04 ± 0.04 with a chamber pressure of 1.685 ± 0.07 MPa. With the VAH design point verified, preliminary scramjet combustor ignition tests were conducted. As the fuel was not auto-ignited by the vitiated air, the forced ignition method, in which VAH ignition flame ignites the scramjet fuel, was used. The Schlieren images showed that a cavity shear layer combustion mode was formed and also showed that the forced ignition method could be used as a reference model for the ignitor-ignition method.

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Section: Scramjet Combustor Preliminary Test: Forced Ignitionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%