A new experimental facility to investigate combustor–turbine interactions in gas turbines with multiple can combustors
- Submitting institution
-
University of Sussex
- Unit of assessment
- 12 - Engineering
- Output identifier
- 290160_52086
- Type
- D - Journal article
- DOI
-
10.1115/1.4028714
- Title of journal
- Journal of Engineering for Gas Turbines and Power
- Article number
- 051503
- First page
- -
- Volume
- 137
- Issue
- 5
- ISSN
- 0742-4795
- Open access status
- Out of scope for open access requirements
- Month of publication
- December
- Year of publication
- 2014
- URL
-
http://dx.doi.org/10.1115/1.4028714
- Supplementary information
-
-
- Request cross-referral to
- -
- Output has been delayed by COVID-19
- No
- COVID-19 affected output statement
- -
- Forensic science
- No
- Criminology
- No
- Interdisciplinary
- No
- Number of additional authors
-
5
- Research group(s)
-
-
- Proposed double-weighted
- No
- Reserve for an output with double weighting
- No
- Additional information
- A high-speed test facility with a test section that includes several novel concepts for testing the complex aero-thermodynamics of combustor exit flow entering the 1st HP vane in a gas turbine is described. Unique techniques to simulate and test engine realistic conditions are designed into this unique test facility. The paper should be viewed in the context of the development of a novel design concept that combines the combustor-wall trailing-edge with the downstream vane, a strategy that could save up to 20% of the total coolant spent. Mitsubishi Heavy Industries LTD, contact Dr.Eng. Sumiu Uchida, Tel: +81-79-445-6710, E-mail: sumiu_uchida@mhi.co.jp
- Author contribution statement
- -
- Non-English
- No
- English abstract
- -
