Design considerations of jet pumps with supersonic two-phase flow and shocks

Lear, W. E.; Sherif, S. A.; Hunt, Patrick; Holladay, Jon

doi:10.2514/6.1999-461

Cited by 6 publications

(7 citation statements)

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“…1, the momentum equation [Eq. (10)] can be combined with Eq. (11) and the de nition of entrainment ratio to obtain Eq.…”

Section: Mixing Chambermentioning

confidence: 99%

“…This includes the works of Bredikhin et al, 1 Cunningham and Dopkin, 2 Cunningham, 3 Elger et al, 4 Fabri and Paulon, 5 Fabri and Siestrunk, 6 Fairuzov and Bredikhin, 7 Holmes et al, 8 Jiao et al, 9 Lear et al, 10 Marini et al, 11 Neve, 12 and Sherif et al 13 Other works involving thermally actuated cooling systems include those of Kakabaev and Davletov, 14 Chen, 15 Lansing and Chai, 16 and Chai and Lansing. 17 With the exception of the works of Fairuzov and Bredikhin, 7 Sherif et al, 13 and Lear et al, 10 which all dealt with two-phase ow in jet pumps, all of the other works mentioned were primarily focused on single-phase ows. The works of Fabri and Paulon 5 and Fabri and Siestrunk 6 discussedthe possibility of choking the secondary ow in jet pumps under certain conditions.…”

Section: Introductionmentioning

confidence: 97%

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Analysis of Heat-Driven Jet-Pumped Cooling System for Space Thermal Management

Nord

Lear

Sherif

2001

Journal of Propulsion and Power

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The solar integrated thermal management and power cycle is a new system that combines a thermal management cycle and a power producing cycle into a single self-contained unit. The system is powered entirely by solar thermal input via a concentrating solar collector. A jet pump provides the compression in the thermal management subsystem, reducing vibration and weight while increasing reliability. Other advantages of the system include constant temperature cooling, reduced number of system components, the ability to use a single working uid, and the incorporation of a waste heat recovery unit. The methods used to analyze the jet pump and the overall system are described separately and in detail. Performance curves based on these analyses are then discussed. NomenclatureA = cross-sectionalarea, m 2 a = speed of sound, m/s h = speci c enthalpy, kJ/kg M = Mach number m = mass ow rate, kg/s P = pressure, MPa Q = heat transfer rate, kW r = heat exchanger pressure ratio s = speci c entropy, kJ/kg K T = temperature, C V = velocity, m/s W = work rate, kW g = ef ciency, dimensionless q = density, kg/m 3 r = Stefan-Boltzmann constant, 5.67E 8 W/m 2 K 4 u = entrainment ratio, m s / m p Subscripts de = diffuser exit ei = evaporator inlet evap = evaporator me = mixing chamber exit ne = primary nozzle exit nt = primary nozzle throat p = primary ow pi = primary nozzle inlet pe = pump exit pump = mechanical pump rad = radiator re = radiator exit s = secondary ow sc = solar collector se = secondary nozzle exit si = secondary nozzle inlet ss = state immediately downstream of shock t = turbine ti = turbine inlet ts = isentropic turbine exit state

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“…1, the momentum equation [Eq. (10)] can be combined with Eq. (11) and the de nition of entrainment ratio to obtain Eq.…”

Section: Mixing Chambermentioning

confidence: 99%

Section: Introductionmentioning

confidence: 97%

Analysis of Heat-Driven Jet-Pumped Cooling System for Space Thermal Management

Nord

Lear

Sherif

2001

Journal of Propulsion and Power

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“…Again the pressure at the nozzle exit, P ne , is assumed and the following system of equations is solved by iteration [20].…”

Section: Primary Nozzlementioning

confidence: 99%

“…The geometry of the primary nozzle and analysis of the resulting ow through it are parallel to that presented by Lear et al [20]. F igure 1 shows the ejector and the appropriate stations, including 'ni' for the nozzle inlet, 'nt' for the nozzle throat and 'ne' for the nozzle exit, used in this analysis.…”

Section: Primary Nozzlementioning

confidence: 99%

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Analysis of two-phase ejectors with Fabri choking

Lear

Parker

Sherif

2002

Proceedings of the Institution of Mechanical Engineers, Part C:

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A one-dimensional mathematical model was developed using the equations governing the ow and thermodynamics within a jet pump with a mixing region of constant cross-sectional area. The analysis is capable of handling two-phase ows and the resulting ow phenomena such as condensation shocks and the F abri limit on the secondary mass owrate. This work presents a technique for quickly achieving rst-approximation solutions for two-phase ejectors. The thermodynamic state of the working uid, R -134a for this analysis, is determined at key locations within the ejector. F rom these results, performance parameters are calculated and presented for varying inlet conditions. The F abri limit was found to limit the operational regime of the two-phase ejector because, in the two-phase region, the speed of sound may be orders of magnitude smaller than in a single-phase uid. NOTATIONa speed of sound (m/s) A area (m 2 ) C p diffuser pressure recovery coef cient P e 7P i P o, i 7P i h speci c enthalpy (kJ/kg) m m mass owrate (kg/s) M M ach number P absolute pressure (kPa) s speci c entropy (kJ/kg K ) T absolute temperature (K ) V velocity (m/s) x quality r density (kg/m 3 ) F entrainment ratio

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Effect of Fabri choking on the performance of two-phase jet pumps

Lear

Sherif²,

Parker³

Collection of Technical Papers. 35th Intersociety Energy Conversion Engineering Conference and Exhibit (IECEC) (Cat. No.00CH370

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Design considerations of jet pumps with supersonic two-phase flow and shocks

Cited by 6 publications

References 0 publications

Analysis of Heat-Driven Jet-Pumped Cooling System for Space Thermal Management

Analysis of Heat-Driven Jet-Pumped Cooling System for Space Thermal Management

Analysis of two-phase ejectors with Fabri choking

Effect of Fabri choking on the performance of two-phase jet pumps

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