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CFD-Based Performance Characterisation of a Reaction Engines SABRE Intake / REBECCA DURRANT

Swansea University Author: REBECCA DURRANT

Abstract

Reaction Engines Limited (REL) have been developing their Synergetic Air-Breathing Rocket Engine (SABRE) since 1989. SABRE is a hypersonic, pre-cooled, hybrid airbreathing rocket engine which is being developed alongside Skylon. Skylon is a spaceplane vehicle concept designed to achieve single-stage...

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Published: Swansea University, Wales, UK 2024
Institution: Swansea University
Degree level: Master of Research
Degree name: MSc by Research
Supervisor: Evans, B. and Walton, S.
URI: https://cronfa.swan.ac.uk/Record/cronfa66844
first_indexed 2024-06-21T14:53:44Z
last_indexed 2024-11-25T14:18:59Z
id cronfa66844
recordtype RisThesis
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spelling 2024-06-21T15:53:46.3924702 v2 66844 2024-06-21 CFD-Based Performance Characterisation of a Reaction Engines SABRE Intake 613a5d06ee0cbb2359e7a4beab68b062 REBECCA DURRANT REBECCA DURRANT true false 2024-06-21 Reaction Engines Limited (REL) have been developing their Synergetic Air-Breathing Rocket Engine (SABRE) since 1989. SABRE is a hypersonic, pre-cooled, hybrid airbreathing rocket engine which is being developed alongside Skylon. Skylon is a spaceplane vehicle concept designed to achieve single-stage-to-orbit hypersonic flight with a horizontal take-off and landing.This study aimed to investigate the impact of flow spillage on the overall performance of SABRE over the air-breathing Mach range for each position of the moveable intake cone to understand how the intake performs at different mass capture ratios. The FLITE3D CFD system was used to run steady-state simulations. Spillage drag occurs when the airflow of the captured streamtube airflow exceeds the maximum airflow the engine requires. The excess air spills over the cowl lip and causes drag. Pressure recovery, the ratio of freestream total pressure to the mean total pressure of the intake surface, was used to quantify the intake performance.This thesis includes an overview of a previous turbulence model study carried out on the Skylon geometry, and an investigation into the stability of the FLITE3D solver at flows of up to Mach 5, also using the Skylon geometry. A converged solution for the SABRE intake was not achieved at Mach 2.00 or above, and unstart is observed at this flow speed. A method of gradually relaxing the massflow rate imposed on the intake surface is used, increasing pressure recovery predictions.It is suspected that the actual solution for flows of Mach 2.00 and above are transient and future work will need to be carried out to meet the original project aims. E-Thesis Swansea University, Wales, UK CFD, SABRE, pressure recovery 15 5 2024 2024-05-15 Due to Embargo and/or Third Party Copyright restrictions, this thesis is not available via this service. COLLEGE NANME COLLEGE CODE Swansea University Evans, B. and Walton, S. Master of Research MSc by Research 2024-06-21T15:53:46.3924702 2024-06-21T15:14:45.3345568 Faculty of Science and Engineering School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering REBECCA DURRANT 1
title CFD-Based Performance Characterisation of a Reaction Engines SABRE Intake
spellingShingle CFD-Based Performance Characterisation of a Reaction Engines SABRE Intake
REBECCA DURRANT
title_short CFD-Based Performance Characterisation of a Reaction Engines SABRE Intake
title_full CFD-Based Performance Characterisation of a Reaction Engines SABRE Intake
title_fullStr CFD-Based Performance Characterisation of a Reaction Engines SABRE Intake
title_full_unstemmed CFD-Based Performance Characterisation of a Reaction Engines SABRE Intake
title_sort CFD-Based Performance Characterisation of a Reaction Engines SABRE Intake
author_id_str_mv 613a5d06ee0cbb2359e7a4beab68b062
author_id_fullname_str_mv 613a5d06ee0cbb2359e7a4beab68b062_***_REBECCA DURRANT
author REBECCA DURRANT
author2 REBECCA DURRANT
format E-Thesis
publishDate 2024
institution Swansea University
college_str Faculty of Science and Engineering
hierarchytype
hierarchy_top_id facultyofscienceandengineering
hierarchy_top_title Faculty of Science and Engineering
hierarchy_parent_id facultyofscienceandengineering
hierarchy_parent_title Faculty of Science and Engineering
department_str School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering{{{_:::_}}}Faculty of Science and Engineering{{{_:::_}}}School of Aerospace, Civil, Electrical, General and Mechanical Engineering - Aerospace Engineering
document_store_str 0
active_str 0
description Reaction Engines Limited (REL) have been developing their Synergetic Air-Breathing Rocket Engine (SABRE) since 1989. SABRE is a hypersonic, pre-cooled, hybrid airbreathing rocket engine which is being developed alongside Skylon. Skylon is a spaceplane vehicle concept designed to achieve single-stage-to-orbit hypersonic flight with a horizontal take-off and landing.This study aimed to investigate the impact of flow spillage on the overall performance of SABRE over the air-breathing Mach range for each position of the moveable intake cone to understand how the intake performs at different mass capture ratios. The FLITE3D CFD system was used to run steady-state simulations. Spillage drag occurs when the airflow of the captured streamtube airflow exceeds the maximum airflow the engine requires. The excess air spills over the cowl lip and causes drag. Pressure recovery, the ratio of freestream total pressure to the mean total pressure of the intake surface, was used to quantify the intake performance.This thesis includes an overview of a previous turbulence model study carried out on the Skylon geometry, and an investigation into the stability of the FLITE3D solver at flows of up to Mach 5, also using the Skylon geometry. A converged solution for the SABRE intake was not achieved at Mach 2.00 or above, and unstart is observed at this flow speed. A method of gradually relaxing the massflow rate imposed on the intake surface is used, increasing pressure recovery predictions.It is suspected that the actual solution for flows of Mach 2.00 and above are transient and future work will need to be carried out to meet the original project aims.
published_date 2024-05-15T05:22:50Z
_version_ 1861603002291322880
score 11.100739

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