Complex intake flows and advanced non-intrusive measurement methods
Lead Research Organisation:
CRANFIELD UNIVERSITY
Department Name: Sch of Aerospace, Transport & Manufact
Abstract
Abstracts are not currently available in GtR for all funded research. This is normally because the abstract was not required at the time of proposal submission, but may be because it included sensitive information such as personal details.
People |
ORCID iD |
| David MacManus (Primary Supervisor) | |
| Matteo Migliorini (Student) |
Publications
Doll U
(2022)
Non-intrusive flow diagnostics for unsteady inlet flow distortion measurements in novel aircraft architectures
in Progress in Aerospace Sciences
McLelland G
(2020)
Influence of Upstream Total Pressure Profiles on S-Duct Intake Flow Distortion
in Journal of Propulsion and Power
Migliorini M
(2024)
Evaluation of Extreme Value Predictions for Unsteady Flow Distortion of Aero-Engine Intakes
in Journal of Engineering for Gas Turbines and Power
Migliorini M
(2022)
Novel Method for Evaluating Intake Unsteady Flow Distortion
in Journal of Propulsion and Power
Migliorini M
(2019)
An assessment on the unsteady flow distortion generated by an S-duct intake
Migliorini M
(2023)
S-duct flow distortion with non-uniform inlet conditions.
in Proceedings of the Institution of Mechanical Engineers. Part G, Journal of aerospace engineering
Studentship Projects
| Project Reference | Relationship | Related To | Start | End | Student Name |
|---|---|---|---|---|---|
| EP/P510464/1 | 30/09/2016 | 29/09/2021 | |||
| 2202953 | Studentship | EP/P510464/1 | 27/11/2017 | 26/11/2021 | Matteo Migliorini |
| Description | Increased fuel cost and stricter policies on emissions and noise drive aero-engine designers to seek a new balance between fuel consumption, weight, manufacturing, maintenance and operating costs. Many novel aircraft configurations propose a closer integration between the propulsion system and aircraft fuselage to reduce fuel consumption, weight, maintenance and operating costs. For some closely coupled propulsion-airframe configurations the engine is embedded or partially embedded in the airframe. In these cases, the use of convoluted intakes for the aero-engine, or propulsor, is known to generate complex flow distortions that can be detrimental for the propulsion system performance. The understanding of the unsteady distortion characteristics across the range of aircraft operating conditions is a key element for the design and integration of the intake with the engine. This work aims to investigate the flow distortion for complex aero-engine intakes with non-uniform inlet conditions. The outcome of this research could expand the knowledge on the flow distortion for future propulsion systems for novel aircraft. This could benefit the work of both intake and compressor designers, which could apply modifications in order to suppress or to tolerate the highly distorted flow field. The availability of devices to condition the flow upstream the S-duct intake could cost-benefit the experiments for the future generation of aircraft, reducing the complexity of testing and increasing the number of possible configurations that can be assessed. The use of high bandwidth measurement systems could help to identify compatibility issues between intake and aero-engine which could cause a reduction of the performance and operability problems. The main research findings are: • Enabled time-resolved synchronous measurements with cross flow Particle Image Velocimetry not previously possible. • Enabled understanding of the unsteady nature of the swirl distortion typical of S-duct intakes. • Characterization of the impact of non-uniform inlet conditions (thick inlet boundary layers and vortex ingestion) on the S-duct flow distortion. • Characterization of the main frequencies of the S-duct flow distortion for a range of different operating conditions of the intake. • Analysis of the duration, magnitude and likelihood of distortion events during an envisaged rotation of the compressor blades. |
| Exploitation Route | Outcomes of the work could aid the development of distortion tolerant propulsion systems by aiding the design of closely coupled fans and intakes. The experimental data could be used for further validation of computational simulations and investigations for S-duct intakes. |
| Sectors | Aerospace Defence and Marine |
| URL | https://arc.aiaa.org/doi/10.2514/6.2019-4202 |