Loughborough University
Leicestershire, UK
LE11 3TU
+44 (0)1509 263171
Loughborough University

Loughborough University Institutional Repository

Please use this identifier to cite or link to this item: https://dspace.lboro.ac.uk/2134/37748

Title: Influence of purge flow swirl at exit to the high-pressure compressor on OGV/pre-diffuser and combustion system aerodynamics
Authors: Walker, Alastair Duncan
Koli, Bharat R.
Beecroft, Peter
Keywords: Gas turbine combustion system aerodynamics
Rim purge flow
Turbine cooling
Issue Date: 2019
Publisher: © American Society of Mechanical Engineers (ASME)
Citation: WALKER, A.D., KOLI, B.R. and BEECROFT, P., 2019. Influence of purge flow swirl at exit to the high-pressure compressor on OGV/pre-diffuser and combustion system aerodynamics. Journal of Turbomachinery, 141 (9), 091009.
Abstract: As aero gas turbine designs strive for ever greater efficiencies the trend is for engine overall pressure ratios to rise. Although this provides greater thermal efficiency it means that cycle temperatures also increase. One potential solution to managing the increasing temperatures is to employ a cooled cooling air system. In such a system a purge flow into the main gas path downstream of the compressor will be required to prevent hot gas being ingested into rotor drive cone cavity. However, the main gas path in compressors is aerodynamically sensitive and it is important to understand, and mitigate, the impact such a flow may have on the compressor outlet guide vanes, pre‐diffuser and the downstream combustion system aerodynamics. Initial CFD predictions demonstrated the potential of the purge flow to negatively affect the outlet guide vanes and alter the inlet conditions to the combustion system. The purge flow modified the incidence onto the outlet guide vane, at the hub, such that the secondary flows increased in magnitude. An experimental assessment carried out using an existing fully annular, isothermal test facility confirmed the CFD results and importantly demonstrated that the degradation in the combustor inlet flow resulted in an increased combustion system loss. At the proposed purge flow rate, equal to ~1% of the mainstream flow, these effects were small with the system loss increasing by ~4%. However, at higher purge flow rates (up to 3%) these effects became notable and the outlet guide vane and pre‐diffuser flow degraded significantly with a resultant increase in the combustion system loss of ~13%. To mitigate these effects CFD was used to examine the effect of varying the purge flow swirl fraction in order to better align the flow at the hub of the outlet guide vane. With a swirl fraction of 0.65 (x rotor speed) the secondary flows were reduced below that of the datum case (with no purge flow). Experimental data showed good agreement with the predicted flow topology and performance trends but the measured data showed smaller absolute changes. Differences in system loss were measured with savings of around 10% at the turbine feed ports for a mass flow ratio of 1% and a swirl fraction of 0.65.
Description: This paper is closed access until 14 June 2020.
Sponsor: Rolls‐Royce as part of SILOET II (Strategic Investment in Low‐carbon Engine Technology) Project 18 ‐ Future Core Engine Systems.
Version: Accepted for publication
DOI: 10.1115/1.4043781
URI: https://dspace.lboro.ac.uk/2134/37748
Publisher Link: https://doi.org/10.1115/1.4043781
ISSN: 0889-504X
Appears in Collections:Closed Access (Aeronautical and Automotive Engineering)

Files associated with this item:

File Description SizeFormat
Walker-2019-Influence_of_Purge_Flow_Swirl.pdfAccepted version5.06 MBAdobe PDFView/Open


SFX Query

Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.