The Effect of MHD Energy Bypass on Specific Thrust for Supersonic Turbojet Engine

Benyo, Theresa L.

doi:10.2514/6.2010-232

Cited by 3 publications

(4 citation statements)

References 2 publications

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“…The enthalpy extraction ratio was found to be between 25% and 31% and varied for each calculated ambient (flight) Mach number. Using equations (1) and (2) of this paper, it was found that the applied magnetic field required for these results was around 3 Tesla which is consistent with previous work 4 .…”

Section: Results From Simulationsupporting

confidence: 79%

“…The MHD generator is a nonobstructing means of total temperature reduction that can be controlled by applied magnetic fields and load parameter adjustment. Previous published results 4 concentrated on the performance of the MHD generator by varying the amount of electrical power that is extracted out of the ionized flow and bypassed to the pre-ionizers and the MHD accelerator. The ratio of electrical power generated by the MHD generator and the power of the incoming flow is called the enthalpy extraction ratio and is represented by the following equation: (1) where P elec is the electrical power and is represented by the following equation:…”

Section: A Mhd Energy Bypassmentioning

confidence: 99%

“…al. and Benyo 4 . In order to achieve this goal, the NPSS environment is chosen since it can help further enhance a thermodynamic cycle analysis of a turbojet engine with a MHD generator and a MHD accelerator.…”

Section: Analysis Goalsmentioning

confidence: 99%

“…For this analysis, we set that ratio as a percent of the energy being extracted. Therefore, the stagnation (total) temperature at the exit of the pre-ionizer is calculated as follows: (4) In the traditional manner, the stagnation pressure ratio of the pre-ionizers is calculated as shown here 7 (Heiser, Eq. 2-114).…”

Section: Analysis Goalsmentioning

confidence: 99%

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Initial Flow Matching Results of MHD Energy Bypass on a Supersonic Turbojet Engine Using the Numerical Propulsion System Simulation (NPSS) Environment

Benyo

2010

41st Plasmadynamics and Lasers Conference

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Preliminary flow matching has been demonstrated for a MHD energy bypass system on a supersonic turbojet engine. The Numerical Propulsion System Simulation (NPSS) environment was used to perform a thermodynamic cycle analysis to properly match the flows from an inlet to a MHD generator and from the exit of a supersonic turbojet to a MHD accelerator. Working with various operating conditions such as the enthalpy extraction ratio and isentropic efficiency of the MHD generator and MHD accelerator, interfacing studies were conducted between the pre-ionizers, the MHD generator, the turbojet engine, and the MHD accelerator. This paper briefly describes the NPSS environment used in this analysis and describes the NPSS analysis of a supersonic turbojet engine with a MHD generator/accelerator energy bypass system. Results from this study have shown that using MHD energy bypass in the flow path of a supersonic turbojet engine increases the useful Mach number operating range from 0 to 3.0 Mach (not using MHD) to an explored and desired range of 0 to 7.0 Mach. = Mach number at the exit of a component P 0,6 = total pressure at the exit of the MHD accelerator P 6 = static pressure at the exit of the MHD acclerator P elec = power output of the MHD generator P elecA = power input into the MHD accelerator T 0,15 = stagnation temperature at the entrance of the MHD generator T 0,2 = stagnation temperature at the exit of the MHD generator T 0,53 = stagnation temperature at the entrance of the MHD accelerator 1 Aerospace Engineer, Aeropropulsion Division, 21000 Brookpark Rd. MS 5-11, AIAA Senior Member.

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Section: Results From Simulationsupporting

confidence: 79%

Section: A Mhd Energy Bypassmentioning

confidence: 99%

Section: Analysis Goalsmentioning

confidence: 99%

Section: Analysis Goalsmentioning

confidence: 99%

See 2 more Smart Citations

Initial Flow Matching Results of MHD Energy Bypass on a Supersonic Turbojet Engine Using the Numerical Propulsion System Simulation (NPSS) Environment

Benyo

2010

41st Plasmadynamics and Lasers Conference

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Preliminary Experimental Investigation on MHD Power Generation Using Seeded Supersonic Argon Flow as Working Fluid

et al. 2011

Chinese Journal of Aeronautics

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Flow Matching Results of an MHD Energy Bypass System on a Supersonic Turbojet Engine using the Numerical Propulsion System Simulation (NPSS) Environment

Benyo

2011

42nd AIAA Plasmadynamics and Lasers Conference

View full text Add to dashboard Cite

Flow matching has been successfully achieved for an MHD energy bypass system on a supersonic turbojet engine. The Numerical Propulsion System Simulation (NPSS) environment helped perform a thermodynamic cycle analysis to properly match the flows from an inlet employing a MHD energy bypass system (consisting of an MHD generator and MHD accelerator) on a supersonic turbojet engine. Working with various operating conditions (such as the applied magnetic field, MHD generator length and flow conductivity), interfacing studies were conducted between the MHD generator, the turbojet engine, and the MHD accelerator. This paper briefly describes the NPSS environment used in this analysis. This paper further describes the analysis of a supersonic turbojet engine with an MHD generator/accelerator energy bypass system. Results from this study have shown that using MHD energy bypass in the flow path of a supersonic turbojet engine increases the useful Mach number operating range from 0 to 3.0 Mach (not using MHD) to a range of 0 to 7.0 Mach with specific net thrust range of 740 N-s/kg (at ambient Mach = 3.25) to 70 N-s/kg (at ambient Mach = 7). These results were achieved with an applied magnetic field of 2.5 Tesla and conductivity levels in a range from 2 mhos/m (ambient Mach = 7) to 5.5 mhos/m (ambient Mach = 3.5) for an MHD generator length of 3 m. Nomenclatureγ specific heat ratio for air η N(a) enthalpy addition ratio of the MHD accelerator η N(g) enthalpy extraction ratio of the MHD generator η s (a) isentropic efficiency for the MHD accelerator η s (g) isentropic efficiency for the MHD generator π a stagnation pressure ratio of the MHD accelerator π g stagnation pressure ratio of the MHD generator π p stagnation pressure ratio of the pre-ionizer σ electrical conductivity χ fraction of MHD generator power diverted to pre-ionizer A g cross sectional area of the MHD generator B magnetic field intensity C p constant pressure specific heat K Faraday loading parameter L length of the MHD generator m  mass flow rate of the air and fuel through the turbojet M entrance Mach number at the entrance of a component M exit Mach number at the exit of a component P elec power output of the MHD generator P elecA power input into the MHD accelerator T 0,12 stagnation temperature at the entrance of the MHD generator NASA/TM-2011-217136 2 T 0,14 stagnation temperature at the exit of the MHD generator T 0,58 stagnation temperature at the entrance of the MHD accelerator T 0,6 stagnation temperature at the exit of the MHD accelerator T 0,entrance stagnation temperature at the entrance of a component T 0,exit stagnation temperature at the exit of a component v velocity of flow IntroductionThe magnetohydrodynamic (MHD) energy bypass system has been proposed (Ref. 1) to provide benefits for aeropropulsion systems. It is anticipated that combining technology developments in electromagnetics, aerodynamics, and chemical kinetics may lead to a breakthrough for improving aerospace vehicle performance. A growing interest is evident...

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The Effect of MHD Energy Bypass on Specific Thrust for Supersonic Turbojet Engine

Cited by 3 publications

References 2 publications

Initial Flow Matching Results of MHD Energy Bypass on a Supersonic Turbojet Engine Using the Numerical Propulsion System Simulation (NPSS) Environment

Initial Flow Matching Results of MHD Energy Bypass on a Supersonic Turbojet Engine Using the Numerical Propulsion System Simulation (NPSS) Environment

Preliminary Experimental Investigation on MHD Power Generation Using Seeded Supersonic Argon Flow as Working Fluid

Flow Matching Results of an MHD Energy Bypass System on a Supersonic Turbojet Engine using the Numerical Propulsion System Simulation (NPSS) Environment

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