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Sunday, October 11, 2020 | History

3 edition of Investigation of low NOx staged combustor concept in high-speed civil transport engines found in the catalog.

Investigation of low NOx staged combustor concept in high-speed civil transport engines

Investigation of low NOx staged combustor concept in high-speed civil transport engines

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Published by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, D.C.], [Springfield, Va .
Written in English

    Subjects:
  • Aircraft exhaust emissions.

  • Edition Notes

    StatementHung Lee Nguyen, David A. Bittker, and Richard W. Niedzwiecki.
    SeriesNASA technical memorandum -- 101977.
    ContributionsBittker, David A., Niedzwiecki, Richard W., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14662406M

    Investigation into the applicability of pollutant emission models for computer aided preliminary aircraft design, Book number , , pp. . on combustion-based technologies – i.e., low emissions combustion (LEC) – for lean burn reciprocating engines commonly used in interstate transmission and most likely subject to retrofit NOx control in the future (i.e., this older equipment is typically “grandfathered” and many units have not been subject to NOx regulations to date).

    High-Speed Civil Transport Mission Perspective Transport type Concorde U.S. SST HSCT Year In service Market North Atlantic North Atlantic Atlantic and Pacific Range (nml) 3, 3, 5,, Payload (passengers) TOGW (lb) , , , Community noise requirements None Stage II Stage III Revenue. § Engine mission characteristics, Fixed-geometry Rich-Quench-Lean (RQL) combustors, Fuel-staged combustors, and Ignition and prevaporized combustion in aero engines § NOx reduction potential, the advanced low emission and the high speed civil transport program.

      INFUB - 11th European Conference on Industrial Furnaces and Boilers, INFUB Combustor concept for industrial gas turbines with single digit NOx nd CO em ssi n values A. Al-Halbounia*, A. Giesea, E. Talia, J. Leichera, R. Albusa, K. GÃrnera aGas-und Wärme-Institut Essen e.V., Hafenstr. , Essen, Germany Abstract Natural gas, when. fuel allows us to achieve low NOx levels when it is applied to lean premixed combustion. This paper describes the concept of the dry low-NOx combustors and the test results for a kWe class simple-cycle and a kWe class recuperated-cycle MGT. 2. Concept of lean premixed combustion Conventional combustion, namely, diffusion.


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Investigation of low NOx staged combustor concept in high-speed civil transport engines Download PDF EPUB FB2

Investigation of low NOx staged combustor concept in high. Get this from a library. Investigation of low NOx staged combustor concept in high-speed civil transport engines. [Hung Lee Nguyen; David A Bittker; Richard W Niedzwiecki; United States. National Aeronautics and Space Administration.].

Investigation of low NOx staged combustor concept in high-speed civil transport engines. By Hung Lee Nguyen, Richard W. Niedzwiecki and David A. Bittker. Abstract. Levels of exhaust emissions due to high temperatures in the main combustor of high-speed civil transport (HSCT) engines during supersonic cruise are predicted.

Experimental investigation of the low NOx vortex airblast annular combustor. Investigation of Mixing and Flow Characteristics in a Dual-Mode Combustor.

Tarek Abdel-Salam, Investigation of low NOx staged combustor concept in high-speed civil transport engines.

Investigation of low NOx staged combustor concept in high-speed civil transport engines. Levels of exhaust emissions due to high temperatures in the main combustor of high-speed civil transport (HSCT) engines during supersonic cruise are predicted.

The work described in this paper is a part of the NASA Lewis Research Center High-Speed. tigation of Low NO, Staged Combustor Concept in High Speed Civil. Transport Engines," AIAA, AIAA/ASME/SAE/ASEE 25th gas turbine combustor concept to reduce NOx emissions in High Speed.

Methane-fueled low NO x combustor research had been conducted under the Japanese supersonic/hypersonic propulsion research program. A unique form of premixture jet swirl combustor (PJSC) was proposed for the ultra low NO x combustor of a Mach 3 turbojet engine.

Fuel-air mixing tests and fundamental combustion tests were conducted to obtain the design data and combustion. Aerosol particle evolution in an aircraft wake: Implications for the high-speed civil transport fleet impact on ozone 1 September | Journal of Geophysical Research:.

National Combustion Code Calculations of a NASA Low-NOx Hydrogen Injector Concept. Anthony Iannetti. The formation of NO x in lean-premixed, high-intensity combustion is examined as a function of several of the relevant variables.

The variables are the combustion temperature and pressure, fuel type, combustion zone residence time, mixture inlet temperature, reactor surface-to-volume ratio, and inlet jet size.

HCCI, and PCCI, combustion concepts are the examples of such systems wherein low temperatures are achieved by intensive premixing of fuel and air at very lean equivalence ratios.

Large scale application of such concepts is however reported to be difficult due to lack of proper control over ignition timing, limited operational range and.

Novel lean-burn combustor concepts were designed and evaluated for supersonic aircraft propulsion, with a focus on cruise NO x emissions.

Premixing to lean conditions is especially challenging at supersonic cruise because combustor inlet temperatures are high and autoignition times are short. GE Low-NOx Combustor achieves NOx GE 5-cup sector results: • Highest pressure data extrapolated up to 85, % ICAO points • Performance indicates better than 75% reduction below CAEP/6 standards • Cruise NOx % reduction below state-of-the-art TAPS combustor • >% efficiency at cruise.

industrial combustors (Mosier and Pierce, and Pierce et al., ), the RQL concept utilizes staged burning, as shown in Figure 1. Combustion is initiated in a fuel rich zone at equivalence ratios between andthereby reducing NO, formation by depleting the available oxygen.

Bypass combustion air is introduced in a quick-mix. For example, the Concorde was powered by turbojet engines that made use of afterburner, a very inefficient combustion system.

Next-generation high speed civil transport (HSCT) vehicles will likely. The Rich-burn/Quick–mix/Lean-burn (RQL) combustor concept has been proposed to minimize the formation of oxides of nitrogen (NOx) in gas turbine systems. The success of this low-NOx combustor strategy is dependent upon the links between the formation of NOx, inlet air preheat temperature, and the mixing of the jet air and fuel-rich streams.

An experimental program was conducted to evaluate low NO x combustor concepts applicable to natural-gas-burning aeroderivative gas turbine engines operating at a nominal pressure ratio of Gas sampling measurements at the exit of the primary zone of high-shear and lean premixed burners were acquired under elevated entrance pressure and temperature.

The success of this low-NOx combustor strategy is dependent upon the links between the formation of NOx, inlet air preheat temperature, and the mixing of the jet air and fuel-rich streams.

Low NOx heavy fuel combustor concept program. concept to reduce NOx emissions in High Speed Civil Transport (HSCT) aircraft. rich primary zone staged combustion provides environmentally. The NOx emissions of this combustor are significantly reduced by using the rich-lean combustion concept.

The basic idea of this concept is to avoid stoichiometric combustion conditions by splitting the combustion domain into a fuel-rich zone (low-oxygen zone) and a fuel-lean (low temperature zone).

Some examples included flue gas recirculation, fuel or air staged combustion, and low NOx burners. Compared with other low NOx emission technologies, air-staged combustion technology [9] is used to reduce NOx emissions with higher reliability, greater applicability and lower investment costs, and has been widely used in natural gas boilers [OR ADVANCED, LOW EMISSION LARGE CIVIL AIRCRAFT ENGINES Figure 8: Aero-engine emissions characteristics Low emission combustion systems for future engines The development of combustors for the next generation of aero-engines is mainly driven by future NOx requirements.

Beside the new emission legislation limits for NOx with. Of all the low-NOx combustor concepts, the Lean Premixed Prevaporized (LPP) combustion yields the lowest NOx. In the development of LPP combustors, the success of the LPP combustion process mainly depends on the flow field, evaporation characteristics of fuel spray and the fuel/air mixing in the combustion zone.