Design and Fabrication of a 400kW Pre-Prototype Engine

Williams, J.M.

doi:10.2172/913090

Cited by 1 publication

(11 citation statements)

References 18 publications

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“…The losses associated with the inlet guide vane (IGV) were reported in a previous report by Williams (2007). Due to mechanical constraints, the inlet duct was not installed for those tests.…”

Section: Inlet Guide Vane Performancementioning

confidence: 99%

“…The numerical scheme and turbulence model described in section 3.1 has been used to verify and refine the Rampressor design described in Williams (2007). Successful prediction of Rampressor rotor performance at design point and off-design requires accurate capture of boundary layer development, diffusing flows and separation, shock wave/boundary layer interaction, and a variety of compressor related phenomena such as tip clearance flow and passage secondary flow vorticity.…”

Section: Analysis Of the Rampressor Rotormentioning

confidence: 99%

“…The closest upstream total pressure measurement available was in the plenum upstream of the inlet bellmouth and inlet guide vane (IGV). In a previous report (Williams, 2007), the losses associated with the IGV were reported. Due to mechanical constraints, the Rampressor forward frame was connected directly to the bellmouth so the inlet duct was not installed for those tests.…”

Section: Inlet Performancementioning

confidence: 99%

“…As expected, the continuity corrected flow angle at location 2 was higher than that of location, although the difference was only about 1°. Figure 4-24 shows the mass averaged total pressure ratio data from Figure 4-18 plotted with the data reported by Williams (2007)…”

Section: Igv Flow Anglementioning

confidence: 99%

“…Testing of the inlet guide vanes (IGV) was also conducted under that contract. The details of the design and the results of the IGV tests are detailed in a report by Williams (2007). Testing was conducted at Boeing's Nozzle Test Facility located in Seattle, Washington.…”

Section: Introductionmentioning

confidence: 99%

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High Efficiency Low Cost CO2 Compression Using Supersonic Shock Wave Technology

Williams¹,

Aarnio²,

Grosvenor³

et al. 2010

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Development and testing results from a supersonic compressor are presented. The compressor achieved record pressure ratio for a fully-supersonic stage and successfully demonstrated the technology potential.Several tasks were performed in compliance with the DOE award objectives. A high-pressure ratio compressor was retrofitted to improve rotordynamics behavior and successfully tested. An outside review panel confirmed test results and design approach. A computational fluid dynamics code used to analyze the Ramgen supersonic flowpath was extensively and successfully modified to improve use on high-performance computing platforms. A comprehensive R&D implementation plan was developed and used to lay the groundwork for a future full-scale compressor demonstration. Conceptual design for a CO2 demonstration compressor was developed and reviewed.Ramgen Document 0080-00220 iv Baseline Rampressor (Ram-2) DevelopmentThrough an extensive verification procedure, Ramgen demonstrated that its CFD tool was capable of modeling Rampressor flow physics. Verification cases included boundary layer development, separation due to adverse pressure gradients, centrifugal compressor flows, and shock wave/boundary layer interactions. CFD simulations of the inlet flow were found to be in agreement with experiment. Simulations of the rotor flow predicted a total pressure ratio of up to approximately 8.55:1 for a tip gap of 0.001 inch and of approximately 5.81:1 for a tip gap of 0.003 inches. These simulations were found to be in good agreement with test results.During the test program, Ramgen measured the performance of the annulus-shaped inlet and found the total pressure loss to be approximately 0.5%. IGV losses were also measured and found to be in good agreement with the CFD simulations. During starting tests the rotor was found to start at approximately 100% speed provided that full bleed was available. Performance testing demonstrated a rotor total pressure ratio of 7.8:1 which was in agreement with CFD simulations. A higher pressure ratio is achievable with further development of the supersonic flow path. Testing showed that the Rampressor concept is capable of achieving high total pressure ratios across the rotor.The Rampressor-2 test program has proven that high total pressure ratio, single stage, supersonic compression is viable, that Ramgen's tools accurately predict test performance, and lay the groundwork for further development and commercial demonstration. During the test program Ramgen achieved a rotor only total pressure ratio of 7.8:1 which is a substantial improvement over the previous Rampressor test program which obtained a total pressure ratio of 2.3:1. Ramgen's commercial targets are a total pressure ratio of 10:1 and a stage efficiency of approximately 85%. More work is required prior to commercial introduction of a Rampressor product, but Ramgen is confident the commercial targets are achievable. Critical Risk Factor Risk ReductionKey risk factors, learned during Rampressor-2 testing, have been identifie...

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Section: Inlet Guide Vane Performancementioning

confidence: 99%

Section: Analysis Of the Rampressor Rotormentioning

confidence: 99%

Section: Inlet Performancementioning

confidence: 99%

Section: Igv Flow Anglementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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