This work showcases an experimental sub-saturation spray cooling setup for a range of heat fluxes from 0.93 W/cm 2 to 4.66 W/cm 2 . The system consists of a 12” Aluminum square heat source unit with 28 embedded 1800 W cartridge heaters. An external high-pressure air tank provides the system with spraying pressures ranging from 500 to 3000 Psi. User-defined control algorithms command four piezoelectric actuated injectors allowing for the manipulation of the spray frequency, duration, duty cycle, and coordination between multiple piezo-injectors. Thus far, experiments in the horizontal configuration have shown that at 60°C, surface temperatures for all heat fluxes prove difficult to control. At 90°C, however, successful results show that heat fluxes of 1.86 W/cm 2 and 2.79 W/cm 2 are sustainable. Conducting experiments at aggressive power loads and surface temperatures significantly below saturation intro-duce spray-pooling, coolant pools which inhibit the evaporation rate, significantly diminishing the spray cooling efficiency. To counteract this effect, additional experiments were performed in a vertical configuration to avoid the pooling of non-evaporated coolant and enhance the heat transfer through the falling film. The results show surface temperature control for 60°C and 90°C within 6°C of the average surface temperature for heat fluxes up to 0.93 W/cm 2 and 3.72 W/cm 2 , respectively.
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A Numerical Heat Transfer Investigation of Lattice Structures As an Alternative AM-Enabled Design for Cooled sCO2 Airfoils
Abstract Supercritical Carbon dioxide (sCO2) power cycles are rapidly developing and gaining popularity in waste heat recovery systems, as primary power cycles for a variety of heat sources such as nuclear, or as a stand-alone power cycle where fossil fuels are combusted. Akin to conventional gas turbines, sCO2-powered systems are pushing the boundaries for firing temperatures for higher efficiencies. Direct oxy-fired sCO2 systems will demand internal cooling of the airfoils for safe and reliable operations. Gas turbine cooling technology can be leveraged for that purpose. However, two key differences exist. First, the coolant medium is sCO2 instead of air, and second, sCO2 airfoils are much smaller compared to power-generation gas turbines. Novel AM manufacturing techniques promise advanced internal cooling geometries. This paper investigates a novel trailing edge cooling design to replace conventional pin fin arrays. Here, a lattice structure with microchannels is introduced. The study presents the changes in heat transfer due to the substitution of the heat transfer medium and the new geometry. The component is assumed to be printed Inconel 718. Based on an oxy-fired combustion sCO2 power cycle, coolant temperature and pressure and hot gas path temperature and pressure are chosen. The converging trailing edge duct is simulated in StarCCM+ using COOLPROP for sCO2 properties as a conjugate heat transfer model.
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- PAR ID:
- 10475701
- Publisher / Repository:
- American Society of Mechanical Engineers
- Date Published:
- Journal Name:
- ASME Turbo Expo 2023
- ISBN:
- 978-0-7918-8707-3
- Format(s):
- Medium: X
- Location:
- Boston, Massachusetts, USA
- Sponsoring Org:
- National Science Foundation
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