Development of a Low NOx Lean Premixed Annular Combustor

1982 ◽  
Vol 104 (1) ◽  
pp. 28-35 ◽  
Author(s):  
P. B. Roberts ◽  
A. J. Kubasco ◽  
N. J. Sekas
Keyword(s):  
Performance Criteria ◽  
Variable Geometry ◽  
Test Results ◽  
Test Program ◽  
Air Blast ◽  
Lean Premixed ◽  
Annular Combustor ◽  
Development Phases ◽  
And Performance ◽  
Aircraft Application

An atmospheric test program was conducted to define a low NOx annular combustor concept suitable for a supersonic, high-altitude aircraft application. The lean premixed combustor, known as the Vortex Air Blast (VAB) concept, was tested as a 22.0 cm diameter model in the early development phases to arrive at basic design and performance criteria. Final demonstration testing was carried out on a full scale combustor of 0.66 m diameter. Variable geometry dilution ports were incorporated to allow operation of the combustor across the range of conditions between idle (Tin = 422 K, Tout = 917 K) and cruise (Tin = 833 K, Tout = 1778 K). Test results showed that the design could meet the program NOx goal of 1.0 g NO2/kg fuel at a reduced atmospheric cruise condition.

scholarly journals Experimental Evaluation of a Low Emissions, Variable Geometry, Small Gas Turbine Combustor

1990 ◽  
Author(s):  
K. O. Smith ◽  
M. H. Samii ◽  
H. K. Mak
Keyword(s):  
Gas Turbine ◽  
Experimental Evaluation ◽  
Premixed Combustion ◽  
Nox Emissions ◽  
Variable Geometry ◽  
Test Results ◽  
Gas Turbine Combustor ◽  
Lean Premixed Combustion ◽  
Primary Zone ◽  
Lean Premixed

The results of an on-engine evaluation of an ultra-low NOx, natural gas-fired combustor for a 200 kW gas turbine are presented. The combustor evaluated used lean-premixed combustion to reduce NOx emissions and variable geometry to extend the range over which low emissions were obtained. Test results showed that ultra-low NOx emissions could be achieved from full load down to approximately 50% load through the combination of lean-premixed combustion and variable primary zone airflow.

Variable Geometry, Lean, Premixed, Prevaporized Fuel Combustor Conceptual Design Study

1980 ◽  
Vol 102 (4) ◽  
pp. 896-902 ◽  
Author(s):  
A. J. Fiorentino ◽  
W. Greene ◽  
J. C. Kim ◽  
E. J. Mularz
Keyword(s):  
Conceptual Design ◽  
Combustion Efficiency ◽  
Operating Conditions ◽  
Nox Emissions ◽  
Variable Geometry ◽  
Design Study ◽  
Flow Modulation ◽  
Lean Premixed ◽  
Unburned Hydrocarbons ◽  
And Performance

Four lean premixed prevaporized (LPP) combustor concepts have been identified which utilize variable geometry and/or other flow modulation techniques to control the equivalence ratio of the initial burning zone. Lean equivalence ratios are maintained at high power engine operating conditions for low NOx emissions, while near stoichiometric conditions are maintained at low power for good combustion efficiency and low emissions of carbon monoxide and unburned hydrocarbons. The primary goal of this program was to obtain a low level of NOx emissions (≤3 g/kg fuel) at stratospheric cruise conditions; additional goals are to achieve the currently proposed 1984 EPA emission standards over the landing/take off cycle and performance and operational requirements typical of advanced aircraft engines. Based on analytical projections made during this conceptual design study, two of the concepts offer the potential of achieving the emission goals. However, the projected operational characteristics and reliability of these concepts to perform satisfactorily over an entire flight envelope would require extensive experimental substantiation before an engine application can be considered.

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