Effects of Fuel Nozzle Design on Performance of an Experimental Annular Combustor Using Natural Gas Fuel
Effects of Fuel Nozzle Design on Performance of an Experimental Annular Combustor Using Natural Gas Fuel

Author: Jerrold D. Wear

Publisher:

Published: 1972

Total Pages: 60

ISBN-13:

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Tests of various fuel nozzles were conducted with natural gas fuel in a full-annulus combustor. The nozzles were designed to provide either axial, angled, or radial fuel injection. Each fuel nozzle was evaluated by measuring combustion efficiency at relatively severe combustor operating conditions. Combustor blowout and altitude ignition tests were also used to evaluate nozzle designs. Results indicate that angled injection gave higher combustion efficiency, less tendency toward combustion instability, and altitude relight characteristics equal to or superior to those of the other fuel nozzles that were tested.

Effect of Combustor-inlet Conditions on Performance of an Annular Turbojet Combustor
Effect of Combustor-inlet Conditions on Performance of an Annular Turbojet Combustor

Author: J. Howard Childs

Publisher:

Published: 1947

Total Pages: 56

ISBN-13:

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The combustion performance and particularly the phenomenon of altitude operational limits was studied by operating the annular combustor of a turbojet engine over a range of conditions of air flow, inlet pressure, inlet temperature, and fuel flow. The combustor investigated was not the latest version of this combustor and the data are presented primarily because they are indicative of general trends and phenomena that apply to a large class of turbojet combustors.

Comparison of Simplex and Dual-orifice Fuel Nozzles with Ambient and Heated Fuel in an Annular Turbojet Combustor
Comparison of Simplex and Dual-orifice Fuel Nozzles with Ambient and Heated Fuel in an Annular Turbojet Combustor

Author: Donald F. Schultz

Publisher:

Published: 1971

Total Pages: 44

ISBN-13:

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A full-scale annular combustor was operated with simplex fuel nozzles of three flow ranges and with dual-orifice fuel nozzles. The dual-orifice nozzles provided combustion efficiencies within 2 to 3 percent of the peak values obtained with any of the simplex atomizers. A wide range of operating conditions including altitude relight, simulated takeoff, Mach 2.7 cruise, and Mach 3.0 cruise were studied. Measurements were made of combustion efficiency, pattern factor , flame radiation, smoke emission, and response to rapid increase in fuel flow. Fuel heated to 300 [degree] F (423 K) was used in many of the tests; heated fuel usually increased combustion efficiency.