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  • SE²A - Sustainable and Energy-Efficient Aviation
  • Research
  • ICA B "Flight Physics and Vehicle Systems"
Logo Sustainable and Energy Efficient Aviation of TU Braunschweig
B1.2 - Aerodynamic analysis of partly embedded boundary layer ingesting propulsors
  • ICA B "Flight Physics and Vehicle Systems"
    • B5.2 - Application of physics-based finite-element tools in stiffness tailored structures for cryogenic hydrogen storage for improved mechanical and thermo-mechanical response
    • B4.2 - Consistent Multilevel Model Coupling and Knowledge Representation in Multidisciplinary Analysis and Design
    • B4.1- Collaborative Multidisciplinary Structural Design and Thermal Management for Electric Aircraft
    • B3.5 - Production technologies for hybrid suction designs - Bonding of micro-perforated sheets for hybrid laminar flow control suction panels
    • B3.2 - Advancing the additive xHLFC suction panel concept towards wind-tunnel readiness
    • B3.1 - Protective, multifunctional suction shells for hybrid laminar flow control: Design, integration, simulation and testing
    • B2.5 - EverScale - Enhancement and verification of load alleviation technologies by subscale flight testing
    • B2.4- Hybrid load alleviation by fluidic/reversed control and nonlinear structures
    • B2.3 - ARGO2 - Integrated design of control methods for stability of elastic aircraft
    • B1.9 - Validation of turbulent boundary layer-induced sound transmission through a fuselage section
    • B1.8 - Wind-tunnel experiments of advanced design of swept-wing with suction surfaces
    • B1.7 - Extension of Correlation-based Transition Transport Models for Laminar Aircraft Design
    • B1.6 - Effective Design Methods and Design Exploration for Laminar Wing and Fuselage
    • B1.5 - Sensitivities of Laminar Suction Boundary Layers for Large Reynolds Numbers
    • B1.3- Physics of broadband noise of sound sources from installed propulsors
    • JRG-B1 - Physics of Laminar Wing and Fuselage
    • JRG-B2 - Flow Physics of Load Reduction
    • B1.1 - Propeller and wing aerodynamics of distributed propulsion
    • B1.2 - Aerodynamic analysis of partly embedded boundary layer ingesting propulsors
    • B1.3 - Fast non empiric prediction of propulsion installation related noise
    • B1.4 - Transition Prediction and Design of Hybrid Laminar Flow Control on Blended Wing Bodies Based on 3D Parabolized Stability Equations
    • B2.1 - Load reduction potential of nonlinear stiffness and damping technologies
    • B2.2 - Structural technologies enabling load alleviation
    • B2.3 - Active load Reduction for enabling a 1-G wing using fOrward-looking and distributed sensors (ARGO)
    • B2.4 - Morphing structures for the 1g-wing
    • B3.1 - Global and Local Design Methodology for Laminar Flow Control
    • B3.2 - Process simulation and multiscale manufacturing of suction panels for laminar flow control
    • B3.3 - Thin Plies in Application for Next Generation Aircraft (TANGA)
    • B3.4 - New methods for failure and fatigue analysis of suction panels for laminar flow control
    • B5.1 - ADEMAO: Aircraft Design Engine based on Multidisciplinary Analysis and Optimization
    • JRG-B5 - Long-Range Aircraft Configurations and Technology Analyses
    • JRP - Permeation assessment for cryogenic applications by means of Fiber Bragg Grating sensors
    • ⯇ back to research

B1.2 - Aerodynamic analysis of partly embedded boundary layer ingesting propulsors

BWB aircraft with BLI

To reduce the carbon footprint of the future air transport system, it is inevitable to radically improve the aircraft and propulsion efficiency. This should not only reduce the fuel consumption but also enable the usage of new game-changing technologies (i.e. electric engines). For significantly reducing the total energy demand of the aircraft, new approaches have to be taken account of. Boundary layer ingestion (BLI) is considered to be such a promising method to improve the efficiency of future aircraft. By increasing the momentum of the aircraft boundary layer flow the propulsion efficiency can increase and thereby save propulsive energy. Due to the close coupling of BLI to other aircraft drag reduction measures like aircraft active laminar flow control (LFC) on both, wing and aircraft body, both effects have to be assessed in parallel for maximising the overall aircraft benefit. As this directly effects the propagation of the airframe boundary layer sucked into the embedded propulsion system, obviously, an interaction has to be considered.

On the other hand BLI-based power saving does only work if the propulsor itself, i.e., the fan, will not be adversely affected be the incoming inhomogeneous flow. Therefore, effective ROM (Reduced Order Modells) supported by detailed validation studies of partially embedded BLI engines plus LFC are required. The proposed research project covers investigations with analytical tools and detailed high-fidelity numerical simulations of asymmetric BLI configurations with integrated UHBR propulsors. The synergies of BLI and LFC are mainly examined with an enhanced parallel compressor method (PCM) in order to identify an optimum configuration. State-of-the-art RANS simulations are carried out to analyse the sensitivities of boundary layer ingestion on the aircraft and the propulsion side of a blended wing body (BWB) aircraft configuration with a rear mounted propulsor array.

Due to the unsteady interaction of the propulsor with a local incoming BLI flow field, asymmetric BLI represents also a new noise source on propulsion and aircraft level. Hence, URANS simulations of selected configurations will also generate high-fidelity flow field data for acoustic analysis within SE²A.

Objectives

Non-Uniform Inlet Distorton (NID)
  1. Extention of the parallel compressor model  (PCM) to a reduced-order model of fan aerodynamics
  2. Modeling fan effects from boundary layer ingestion and laminar flow control employing the extended parallel compressor model
  3. CFD of embedded BWB engine inlets and derivation of fan design rules
  4. Investigation of interactions between fan and boundary layer to validate the PCM

Publications

  • Budziszewski, N.; Friedrichs, J.: Modelling of A Boundary Layer Ingesting Propulsor, Energies 2018, 11, 708; doi;10.3390 / en11040708
Members

Prof. Dr.-Ing. Jens Friedrichs

Institute of Jet propulsion and Turbomachinery (IFAS), 206
+49 531 391 94200

Jonas Voigt, M.Sc.

Institute of Jet propulsion and Turbomachinery (IFAS), 216
+49 531 391 94216
 

Contact

Project lead

Prof. Dr.-Ing. Jens Friedrichs

Institute of Jet propulsion and Turbomachinery
+49 531 391 94200

 

Organisation

Institute of Jet propulsion and Turbomachinery

TU Braunschweig
Hermann-Blenk-Straße 37
38108 Braunschweig

 

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Contact information

Cluster of Excellence SE²A –
Sustainable and Energy-Efficient Aviation
Technische Universität Braunschweig
Hermann-Blenk-Str. 42
38108 Braunschweig

se2a(at)tu-braunschweig.de
+49 531 391 66661

 

 

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