Niedrigemissions-Brennkammer Stufe III - Niedriger Nox III, Teil 2: Pruefberichte und Ergebnisanalyse, Programm zur Niedrigemissions-Technologie, Phase III - LOW NOx III

Description: 1. Pilot Stage Combustor: In diesem Vorhaben wird das Konzept der Fett-Mager Verbrennung als Pilot-Stufe einer brennstoffgestuften Brennkammer untersucht. Dabei soll die Interaktion der Kuehlung, der fetten Stufe und der Mischluft derart optimiert werden, dass die Homogenitaet der fetten Stufe verbessert wird. 2. Applied CFD: In diesem Vorhaben werden Modelle, die die Interaktion der Waermefreisetzung mit der turbulenten Schwankungsbewegung getestet und anhand vorhandener Experimente verifiziert.

SupportProgram

Origins: /Bund/UBA/UFORDAT

Tags: Brennstoff ? Flugzeugabgas ? Kombinationswirkung ? Anlagenoptimierung ? Stickoxide ? Verbrennung ? Wärme ? Luftverschmutzung ? Antriebstechnik ? Brennkammer ? Emissionsminderung ? Luft- und Raumfahrttechnik ? Luftverkehr ? Troposphäre ? Verfahrenstechnik ? Luftschadstoff ? Minderungspotenzial ? Kühlung ? Pilotprojekt ? Turbulenz ? Verkehrsemission ? Versuchsanlage ? Schadstoff ? CFD ? Combustor ? Fett-Mager-Verbrennung ? Mischung ? Modellierung-Waermefreisetzung ?

Region: Bayern

Bounding boxes: 12.53381° .. 12.53381° x 47.795° .. 47.795°

License: cc-by-nc-nd/4.0

Language: Deutsch

Organisations

• BMW Rolls-Royce (Mitwirkende)
• Deutsches Zentrum für Luft- und Raumfahrt e.V., Institut für Antriebstechnik (Mitwirkende)
• Kommission der Europäischen Gemeinschaften Brüssel (Geldgeber*in)
• Motoren- und Turbinen Union Friedrichshafen (Betreiber*in)
• Societe Nationale d'Etude et de Construction de Moteurs d'Aviation (Mitwirkende)
• Technische Universität München, Lehrstuhl für Flugantriebe (Mitwirkende)
• Umweltbundesamt (Bereitsteller*in)
• Universität Karlsruhe (TH), Fakultät für Maschinenbau (Mitwirkende)

Time ranges: 1996-01-01 - 1999-12-31

Alternatives

• Language: Englisch/English
  Title: Low Emission Combustor Technology-Phase III - Low NOx III, Part 1: Pilot Stage Combustor Applied CFD
  Description: A major challenge is to respond to current and prospective public concerns regarding the atmospheric impact of aircraft exhaust gas emissions, in particular at high altitude. A particular concern relates to the possibility that emissions of oxides of nitrogen (NOx) and other trace species from aircraft flying in the upper troposphere and lower stratosphere (8 - 25 km) whether from current subsonic or, in the future, from possible supersonic operations, may make a contribution to global warning and ozone generation or depletion. In the preceding phases of this programme (Pilot Phase /I/ and Interim Phase /2/), three major methods of nitrogen oxide reduction were identified. These methods differ not only in their NOx reduction potential, but also in their complexity and technical feasibility. The first concept with the lowest NOx reduction potential incorporates the lean combustion method without premixing in a staged Double Annular Combustor - design. The second method also uses lean combustion but improvements in NOx reduction can be obtained by introducing a premix duct so that a Lean, Premixed and Prevaporized (LPP) combustion system is developed. The third concept, applying the Rich burn, quick Quench Lean burn (RQL) combustion has a smaller technical risk than LPP still providing a considerable amount in NOx reduction. The specific industrial target is: to enable a reduction in engine NOx emissions in excess of 80 per cent compared to current data. Thus the main objectives of the project are: - demonstration of the most promising NOx reduction techniques in test combustors at simulated engine operating condition for large and small engines, - the measurement of the potential of NOx reduction reached by application of the ultra low NOx combustion systems selected, - and the evaluation of these combustion systems concerning essential performance features such as safety, integrity and engine control. Development and demonstration of pre-competitive technology is proposed for: - the LPP combustion on a practicable experimental basis, eg integration into practical combustion hardware and evaluation of the emissions reduction potential over the full range of realistic engine operating conditions; - the application of a RQL pilot stage combustor in connection with a staged system of which the combustor architecture is most likely to lead to a practical combustor; - evaluation of possible improvements in designs and component technology in a study focused on fundamentals; - validation of CFD combustion model. The proposed investigations will not only he ot benefit to the development of low emission combustion chambers for all gas turbines burning liquid fuel (subsonic aero engines, SSTs and land based industrial gas turbines) but will also contribute to the improvement of several tools for the design of all gas turbine combustion chambers and their components. https://ufordat.uba.de/UFORDAT/pages/PublicRedirect.aspx?TYP=PR&DSNR=47841

Status

Aktiv

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