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RISLocal Heat Transfer Measurements for an Impinging Synthetic Jet
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Research results demonstrate the heat transfer effectiveness of an impinging synthetic jet toward cooling a plane normal to it. The utility of the synthetic jet lies in that the supply of coolant comes from the device ...
An Experimental Study of Sister Holes Film Cooling With Various Secondary-to-Primary Hole Diameter Ratios
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: For increased specific thrust and efficiency, more effective film-cooling schemes are developed with each successive gas turbine design. Adding secondary film-cooling holes to each primary film-cooling hole represents such ...
High-Performance Perovskite Solar Cells Fabricated by a Hybrid Physical–Chemical Vapor Deposition
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: For the first time, we used a hybrid physical–chemical vapor deposition (HPCVD) method to fabricate perovskite solar cells (PSCs) based on perovskite films with both organic cations and halogen anions. A high power conversion ...
Endwall Film Cooling Performance for a First-Stage Guide Vane With Upstream Combustor Walls and Inlet Injection
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Effects of an upstream combustor wall on turbine nozzle endwall film cooling performance are numerically examined in a linear cascade in this paper. Film cooling is by two rows of cooling holes at 20% of the axial chord ...
Turbine Vane Passage Experiments Documenting Evolution of Secondary Flows With Changes in Combustor Coolant Injection Flowrates
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: A secondary flow system with a dominant passage vortex pattern has been observed in many gas turbine vane passage studies in which there is no upstream coolant injection or only near-passage endwall coolant injection (no ...
Comparisons of Endwall Overall Effectiveness From Two Film Hole Distribution Patterns at Low and High Exit Mach Numbers
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: In this paper, detailed overall cooling effectiveness and associated flow patterns are presented for two distinct film hole distribution patterns over a turbine endwall: an axial-row pattern and an iso-Mach number line row ...
Nozzle Passage Endwall Effectiveness Values With Various Combustor Coolant Flowrates—Part 1: Flowfield Velocity and Coolant Concentration Measurements
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The stators of the first stage of a gas turbine are exposed to severe temperatures. The coolant streams introduced to prevent the stators from thermal damage further complicate the highly three-dimensional vane passage ...
Nozzle Passage Endwall Effectiveness Values With Various Combustor Coolant Flowrates—Part 2: Endwall and Vicinity Surface Effectiveness Measurements
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Effective coolant schemes are required for providing cooling to the first-stage stator vanes of gas turbines. To correctly predict coolant performance on the endwall and vane surfaces, these coolant schemes should also ...
Turbine Vane Passage Cooling Experiments With a Close-Coupled Combustor-Turbine Interface Geometry—Part I: Describing the Flow
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: Due to the proximity of the first-stage gas turbine vanes to the combustor, coolant introduced to the combustor walls interacts with the endwall film coolant and changes the vane passage flow physics. Recent results show ...
Turbine Vane Passage Cooling Experiments With a Close-Coupled Combustor–Turbine Interface Geometry Part II: Describing the Coolant Coverage
Publisher: The American Society of Mechanical Engineers (ASME)
Abstract: The first-stage gas turbine vane surfaces and endwalls require aggressive cooling. This two-part paper introduces a modified design of the combustor–turbine (C–T) interface, the “close-coupled interface,” that is expected ...