Résumé of the Supersonic-Compressor Research at NACA Lewis Laboratory

Wilcox, Ward W; Tysl, E. R.; Hartmann, Melvin J.

doi:10.1115/1.4008560

Cited by 4 publications

(3 citation statements)

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“…While supersonic axial compressor stages have been suggested by a number of other investigators [1][2][3][4][5], those rotor stages have invariably been configured so as to resemble conventional axial flow rotors. They have relatively high blade counts and inefficient shock systems generated by those blade surfaces.…”

Section: Theory Of Operationmentioning

confidence: 99%

Insertion of Shock Wave Compression Technology Into Micro Turbines for Increased Efficiency and Reduced Costs

Steele

Baldwin

Kesseli

2005

Volume 1: Turbo Expo 2005

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The following analysis is presented to serve as a preliminary design guide for micro turbine engine designers to consider the potential advantages of incorporating the Rampressor into their recuperated engine designs. It is shown that the increase in compressor efficiency and the shift in optimum pressure will increase the efficiency of the engine and lower the recuperator inlet temperature and specific cost. This also provides the opportunity to increase the turbine inlet temperature and specific power without incorporating more costly air-cooled metal or ceramic components into the turbine design. Ramgen Power Systems, Inc. (RPS) is developing a family of high performance supersonic compressor designs that combine many of the aspects of shock compression systems, commonly used in supersonic flight inlet design, with turbo-machinery design practices employed in conventional axial and centrifugal compressor design. The result is a high efficiency compressor that is capable of single stage pressure ratios in excess of those available in existing axial or centrifugal compressor designs. This technology provides a tremendous opportunity for replacement and/or de-staging of multi-stage centrifugal or axial compressors in gas turbines for greater efficiency, less cost, fewer parts, lower weight, and reduced footprint. A conceptual single-stage supersonic compressor has been defined for integration with a micro turbine in the 200 to 500 kWe class. This configuration offers the potential to achieve the DOE Advanced Micro Turbine Systems goals of greater than 40% LHV electric efficiency and $500 per kWe package selling price.

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Section: Theory Of Operationmentioning

confidence: 99%

Insertion of Shock Wave Compression Technology Into Micro Turbines for Increased Efficiency and Reduced Costs

Steele

Baldwin

Kesseli

2005

Volume 1: Turbo Expo 2005

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“…The work of this period has been well-documented, both during and subsequent to the time in question. Example materials include Savage, Boxer and Erwin (1961), Lieblein and Johnsen (1961), Wilcox, Tysl, Hartmann (1959), Klapproth(1961), Serovy (1966) and Johnsen and Bullock (1965). '…”

Section: Programmentioning

confidence: 99%

Some Results of NASA-Iowa State University Research on Axial-Flow Pumps

Serovy

Okiishi

1993

Volume 3B: General

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This paper is a commentary on a small chapter in the recent history of turbomachinery research. It was written to describe the positive influence of an individual, Melvin J. Hartmann, working in a federal research center, on a particular university research program. However, in its final form, it cannot help but shed some light on the long-term effects of small-scale mission-oriented, federal agency funding of engineering research in universities. Secondarily, it will recall a series of experimental investigations of axial-flow pump configurations which produced data of possible relevance to current compressor and pump problems.

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“…Supersonic rotor operation with (relative) subsonic flow at the rotor exit involves the effects of a normalshock compression to achieve most of the work interaction. This mode of operation, con ventionally referred to as shock-in-rotor [20][21][22], is typically associated with a relatively high stage-reaction due to the resulting large static pressure (or enthalpy) rise through the rotor shock. Conversely, operation of a supersonic rotor at low back-pressure, often with axial-supersonic exit flow, involves little or no static-pressure rise through the rotor, and may even involve a substantial decrease in static pressure.…”

Section: Historical Considerations Of Supersonic Compressor Developmentmentioning

confidence: 99%

The aerodynamics of a baseline supersonic throughflow fan rotor

Tweedt

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A baseline supersonic throughflow fan has been designed and tested at the NASA Lewis Research Center in order to demonstrate proof-of-concept and provide an experi mental data base for this unique type of turbomachine. The aerodynamics of the rotor, which was tested in both an isolated and a stage configuration, is discussed in somewhat generic terms for conditions covering most of the practical operating range. Much detailed and quantitative information is also included. In addition to the experimental results, viscous computational fluid dynamics (CFD) results and simple analytical solu tions are discussed, having been used extensively to understand and assess the aerody namic performance of the rotor and to understand and interpret the experimental results. In general, most of the operational and performance characteristics for steady-state rotor operation can be explained and quantified using the various analytical methods.

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Résumé of the Supersonic-Compressor Research at NACA Lewis Laboratory

Cited by 4 publications

References 0 publications

Insertion of Shock Wave Compression Technology Into Micro Turbines for Increased Efficiency and Reduced Costs

Insertion of Shock Wave Compression Technology Into Micro Turbines for Increased Efficiency and Reduced Costs

Some Results of NASA-Iowa State University Research on Axial-Flow Pumps

The aerodynamics of a baseline supersonic throughflow fan rotor

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