DLR Portal
Home|Sitemap|Contact Imprint and terms of use Privacy |Deutsch
You are here: Home:Facilities:OHZ
Advanced Search
News
Institute
Departments
Facilities
APZ
SSC
HAT
HBK 1
HBK 2
HBK 3
HPCR - Kühlungsprüfstand
OHZ
M2VP
Modelteststände Berlin
NGG
Berlin oil channel
Radial Compressor
Rotierender Kühlkanal
SEG
Subsonic Cascade Tunnel Berlin
Acoustic Test Section Berlin
Transonic Cascade Tunnel
Windtunnel EGG
Windtunnel RGG
Ausgewählte EU-Projekte
Publications
Offers
Service & Links
Print

Optical-High Pressure-Atomizer (OHA)



Fuel placement has a major impact on the combustion process and hence on the pollutant building mechanisms. The Optical-High Pressure-Atomizer (OHA) is designed for the investigation of atomisation, vaporisation and mixing of kerosene under realistic operation conditions it the absence of combustion. The test facility with its test rig OSSI (Optical-Swirling-Spray-Injector) allows the integration of realistic aeronautical burner designs. Multiple high pressure windows enable the application of laser-optical measurement techniques. Therefore the test facility offers unique insights into the atomization processes in gas turbine combustors. The experimental data from this test rig is used by several European aeronautical gas turbine manufacturers to optimize their design practice. Moreover, the published database is used by research teams worldwide to validate their CFD based modelling approaches.  
 

zum Bild
 

GENERAL INFORMATION

  • Site: Cologne-Porz, Institute of propulsion technology
  • In service since: 1993, Modernisation: 2014
     

TECHNICAL DATA

  • Static pressure 25 bar
  • Air preheat temperature 850 K
  • Air mass flow 1,5 kg/s
  • Fuel mass flow 10 g/s
  • Catalytic after burner
  • Optische Messtechniken:
    • Particle-Image-Velocimetry (PIV)
    • Laser-Doppler-Anemometry (LDA)
    • Phase-Doppler-Anemometry (PDA)
    • Kerosene-LIF
    • Mie-Scattering
    • Tomographic Shadowgraphy
       

FIELD OF APPLICATION

  • Optical investigation of fuel vaporisation in gas turbine combustors, i.e. aero engines.
  • Unique test rig for isothermal investigation of sprays under realistic operating conditions (real pressure, real temperature, real fuels) of gas turbine injectors
    • Flow field
    • Droplet size distributions & droplet velocities
    • Spray placement
    • Transient droplet velocities
    • 3D- Spray trajectory
    • Placement of gaseous fuel
  • Provides experimental  boundary conditions for the two phase  flow of fuel sprays for combustion simulations
  • Testing and investigation of SLM-burner and SLM combustor parts

Contact
Ingo Otterpohl
German Aerospace Center

Institute of Propulsion Technology
, Combustor
Köln

Tel.: +49 2203 601-3286

Related Topics
Aerodynamic
Atomic and Molecular Physics
Lasers and Masers
Quality Assurance and Reliability
Copyright © 2021 German Aerospace Center (DLR). All rights reserved.