Modeling and impact of high-pressure turbine blade trailing edge film cooling hole variations
Modeling and impact of high-pressure turbine blade trailing edge film cooling hole variations
Inevitable uncertainties and their potential negative impact on performance are a widely known problem in the field of turbomachinery. Based on a representative sample of optically scanned film cooled turbine blades, the impact of real manufacturing variations is investigated. Geometric models with realistic blade shape and film cooling hole variations are constructed using an accurate reverse engineering workflow. It is shown that positional deviations of film cooling holes from nominal are largely due to blade shape variations as opposed to other sources. Film cooling variability is introduced using a novel mapping approach termed “virtual manufacture”, which replicates the real manufacturing process. The methodology essentially exploits the finding that blade shape variations are a major cause of film cooling hole variations. The presented workflow uses fully-featured geometric turbine blade models and supports the analysis of realistic blade shape and film cooling hole variations. Through a comparison with an uncooled setup at the same operating point, it is also shown that trailing edge film cooling variability is important, especially for setting the turbine capacity. Artificially constructed blade models are shown to exhibit the same performance variation as the original measured sample of blade scans and can be used to compute blade statistics for uncertainty quantification. The analysis model choice, either approximate continuous film cooling strips, accurate discrete holes or a combination of both, impacts uncertainty quantification options. It is shown that the simpler strip model is sufficient to model the influence of film cooling variations on capacity and mass flow rate.
Aerospace Research Central
Kamenik, Jan
6a80b527-28d9-492c-9e50-91b4000c881b
Toal, David
dc67543d-69d2-4f27-a469-42195fa31a68
Keane, Andrew
26d7fa33-5415-4910-89d8-fb3620413def
Högner, Lars
55489b20-4d3d-442b-94e0-560f55e7c408
Meyer, Marcus
c240eafe-6ff2-4862-abc2-e531ef4a5549
Shahpa, Shahrokh
ced3eb5d-1211-4d7a-b539-618b16f22b4b
2020
Kamenik, Jan
6a80b527-28d9-492c-9e50-91b4000c881b
Toal, David
dc67543d-69d2-4f27-a469-42195fa31a68
Keane, Andrew
26d7fa33-5415-4910-89d8-fb3620413def
Högner, Lars
55489b20-4d3d-442b-94e0-560f55e7c408
Meyer, Marcus
c240eafe-6ff2-4862-abc2-e531ef4a5549
Shahpa, Shahrokh
ced3eb5d-1211-4d7a-b539-618b16f22b4b
Kamenik, Jan, Toal, David, Keane, Andrew, Högner, Lars, Meyer, Marcus and Shahpa, Shahrokh
(2020)
Modeling and impact of high-pressure turbine blade trailing edge film cooling hole variations.
In AIAA SciTech 2020 Forum.
vol. 1 PartF,
Aerospace Research Central..
(doi:10.2514/6.2020-0905).
Record type:
Conference or Workshop Item
(Paper)
Abstract
Inevitable uncertainties and their potential negative impact on performance are a widely known problem in the field of turbomachinery. Based on a representative sample of optically scanned film cooled turbine blades, the impact of real manufacturing variations is investigated. Geometric models with realistic blade shape and film cooling hole variations are constructed using an accurate reverse engineering workflow. It is shown that positional deviations of film cooling holes from nominal are largely due to blade shape variations as opposed to other sources. Film cooling variability is introduced using a novel mapping approach termed “virtual manufacture”, which replicates the real manufacturing process. The methodology essentially exploits the finding that blade shape variations are a major cause of film cooling hole variations. The presented workflow uses fully-featured geometric turbine blade models and supports the analysis of realistic blade shape and film cooling hole variations. Through a comparison with an uncooled setup at the same operating point, it is also shown that trailing edge film cooling variability is important, especially for setting the turbine capacity. Artificially constructed blade models are shown to exhibit the same performance variation as the original measured sample of blade scans and can be used to compute blade statistics for uncertainty quantification. The analysis model choice, either approximate continuous film cooling strips, accurate discrete holes or a combination of both, impacts uncertainty quantification options. It is shown that the simpler strip model is sufficient to model the influence of film cooling variations on capacity and mass flow rate.
This record has no associated files available for download.
More information
e-pub ahead of print date: 5 January 2020
Published date: 2020
Additional Information:
Funding Information:
The financial support from Rolls-Royce plc and the EPSRC through grant EP/L015382/1 is gratefully acknowledged. Special thanks are also due to TU Dresden’s Chair of Turbomachinery and Jet Propulsion for the provision of their blade scans and in-house software and to Rolls-Royce plc for the permission to publish the results.
Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
Venue - Dates:
AIAA SciTech 2020 Forum, , Orlando, United States, 2020-01-06 - 2020-01-10
Identifiers
Local EPrints ID: 436927
URI: http://eprints.soton.ac.uk/id/eprint/436927
PURE UUID: 4f606dd5-8d8e-4a0b-bf6b-4547a147fb31
Catalogue record
Date deposited: 14 Jan 2020 17:30
Last modified: 17 Mar 2024 03:10
Export record
Altmetrics
Contributors
Author:
Jan Kamenik
Author:
Lars Högner
Author:
Marcus Meyer
Author:
Shahrokh Shahpa
Download statistics
Downloads from ePrints over the past year. Other digital versions may also be available to download e.g. from the publisher's website.
View more statistics
