Author

Austin Click

Date of Award

2020

Document Type

Thesis

Degree Name

Master of Science in Engineering (MSE)

Department

Mechanical and Aerospace Engineering

Committee Chair

Phillip M. Ligrani

Committee Member

Jason T. Cassibry

Committee Member

Guangsheng Zhang

Subject(s)

Heat--Transmission., Cooling systems., Gas-turbines--Thermodynamics.

Abstract

Presented are experimental heat transfer data for five different experimental configurations, where results are provided on different sides of the effusion plate, with full-coverage effusion cooling, both with and without louver slot injection. Three different coolant supply arrangements are considered, including a cross flow only arrangement, an impingement jet array only arrangement, and a combination cross flow and impingement jet array arrangement. Contraction ratios of 1 and 4 are used within the main flow passage to provide streamwise development with a zero pressure gradient, as well as with a strong favorable pressure gradient. With the five configurations, data are given for: (1) the film cooled side of the effusion plate, for effusion only cooling, with a combination coolant supply arrangement, (2) the cross flow side of the effusion plate, for effusion only cooling, with a combination coolant supply arrangement, (3) the film cooled side of the effusion plate, with louver and effusion combination cooling, with a combination coolant supply arrangement, (4) the cross flow side of the effusion plate, with louver and effusion combination cooling, with a combination coolant supply arrangement, and (5) the cross flow side of the effusion plate, with louver and effusion combination cooling, with an impingement only coolant supply. For configurations (1) and (2), also considered are the effects of different coolant supply arrangements on surface thermal performance for both sides of a double-wall cooled effusion plate. Configuration (1) results show that, overall, for larger x/de values, the cross flow/impingement combination behaves in a manner which is similar to the impingement only arrangement. For Configuration (2) Nusselt numbers generally increase with BR for each x/de location. Near impingement jets, Nusselt numbers approach impingement only values. Away from impingement jets, Nusselt numbers approach cross flow only configuration values. Configuration (3) results show that, when compared at the same effective blowing ratio or the same impingement jet Reynolds number, spanwise-averaged heat transfer coefficients are consistently lower, especially for the downstream portions of the test plate, when the louver is utilized. The presence of the louver slot additionally results in significantly larger adiabatic film cooling effectiveness values which are line-averaged, particularly at and near the upstream portions of the test plate. Nusselt numbers increase with BR (as x/de is constant) and proximity to impingement holes for Configuration (4) and for Configuration (5) for high and low mainstream Reynolds numbers.

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