Journal ArticleDOI
A review of shaped hole turbine film-cooling technology
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TLDR
In this article, a review examines the origins of shaped film cooling and summarizes the extant literature knowledge concerning the performance of such film holes, showing the basic shaping geometries, parameter ranges, and types of data obtained.Abstract:
Film cooling represents one of the few game-changing technologies that has allowed the achievement of today's high firing temperature, high-efficiency gas turbine engines. Over the last 30 years, only one major advancement has been realized in this technology, that being the incorporation of exit shaping to the film holes to result in lower momentum coolant injection jets with greater surface coverage. This review examines the origins of shaped film cooling and summarizes the extant literature knowledge concerning the performance of such film holes. A catalog of the current literature data is presented, showing the basic shaping geometries, parameter ranges, and types of data obtained. Specific discussions are provided for the flow field and aerodynamic losses of shaped film hole coolant injection. The major fundamental effects due to coolant-to-gas blowing ratio, compound angle injection, cooling hole entry flow character, and mainstream turbulence intensity are each reviewed with respect to the resulting adiabatic film effectiveness and heat transfer coefficients for shaped holes. A specific example of shaped film effectiveness is provided for a production turbine inlet vane with comparison to other data. Several recent unconventional forms of film hole shaping are also presented as a look to future potential improvementsread more
Citations
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Journal ArticleDOI
Turbine blade film cooling using psp technique
TL;DR: In this article, the pressure sensitive paint (PSPSPP) mass transfer analogy is used to determine the film cooling effectiveness. But the PSP method is not suitable for high-temperature applications, as it does not take into account the conduction error in high thermal gradient regions near the hole.
Journal ArticleDOI
A Novel Anti-Vortex Turbine Film Cooling Hole Concept
TL;DR: In this paper, the anti-vortex film cooling hole concept has been modeled computationally for a single row of 30 degree angled holes on a flat surface using the 3D Navier-Stokes solver Glenn-HT.
Journal ArticleDOI
Review on active thermal protection and its heat transfer for airbreathing hypersonic vehicles
TL;DR: In this paper, the authors present a comprehensive literature review on three active cooling methods, i.e., regenerative cooling, film cooling, and transpiration cooling, including the fluids flow, heat transfer, and thermal cracking characteristics of different hydrocarbon fuels.
Journal ArticleDOI
Gas Turbine Heat Transfer: Ten Remaining Hot Gas Path Challenges
TL;DR: In this paper, the authors identify ten major thermal issues for the turbine hot gas path (HGP) today, including uniformity of internal cooling, ultimate film cooling, micro-cooling, reduced incident heat flux, secondary flows as prime cooling, contoured gas paths, thermal stress reduction, controlled cooling, low emission combustor-turbine systems, and regenerative cooling.
Proceedings ArticleDOI
Adiabatic Effectiveness Measurements for a Baseline Shaped Film Cooling Hole
TL;DR: In this article, the authors proposed a baseline shaped cooling hole design that includes the following features: hole inclination angle of 30° with a 7° expansion in the forward and lateral directions; hole length of 6 diameters; hole exit-to-inlet area ratio of 2.5; and lateral hole spacing of 6 diameter.
References
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Journal ArticleDOI
Effects of hole geometry and density on three-dimensional film cooling
TL;DR: In this article, the effects of hole geometry, secondary fluid density, and mainstream boundary layer thickness on the film cooling performance of secondary gas injection through discrete holes have been studied experimentally.
Proceedings ArticleDOI
Film Cooling With Compound Angle Holes: Adiabatic Effectiveness
TL;DR: In this paper, film cooling effectiveness was studied experimentally in a flat plate test facility with zero pressure gradient using a single row of inclined holes, which injected high-density, cryogenically cooled air.
Proceedings ArticleDOI
Adiabatic Wall Effectiveness Measurements of Film-Cooling Holes With Expanded Exits
TL;DR: In this article, the authors present detailed measurements of the film-cooling effectiveness for three single scaled-up film cooling hole geometries, including a cylindrical hole and two holes with a diffuser-shaped exit portion.
Proceedings ArticleDOI
Film Cooling With Compound Angle Holes: Heat Transfer
TL;DR: In this paper, the authors measured the heat transfer coefficient of a single row of holes laterally directed with a compound angle of 60 degrees, and showed that the results were combined with adiabatic effectiveness results to evaluate the overall performance of the three geometries.
Proceedings ArticleDOI
Flowfield Measurements for Film-Cooling Holes With Expanded Exits
TL;DR: In this article, a comparison of detailed flowfield measurements for three different single scaled-up hole geometries, all at a blowing ratio and density ratio of unity, is presented.