NASA Technical Reports Server (NTRS) : Reverse pdf

NASA Technical Reports Server (NTRS) : Reverse

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Description of the Book:

A reverse flow combustor suitable for a small gas turbine (2 to 3 kg/s mass flow) was used to evalute the effect of pressure atomizing fuel injectors on combustor performance. In these tests an experimental combustor was designed to operate with 18 simplex pressure atomizing fuel injectors at sea level takeoff conditions. To improve performance at low power conditions, fuel was redistributed so that only every other injector was operational. Combustor performance, emissions, and liner temperature were compared over a range of pressure and inlet air temperatures corresponding to simulated idle, cruise, and takeoff conditions typical of a 16 to 1 pressure ratio turbine engine

• Creator/s: NASA Technical Reports Server (NTRS
• Date: 8/1/1978
• Year: 1978
• Book Topics/Themes: NASA Technical Reports Server (NTRS), COMBUSTION CHAMBERS, FUEL INJECTION, GAS TURBINE ENGINES, PRESSURE DISTRIBUTION, REVERSED FLOW, CARBON MONOXIDE, EXHAUST GASES, FLIGHT SIMULATION, PARTICLE EMISSION, TEST FACILITIES, Norgren, C. T., Mularz, E. J., Riddlebaugh, S. M

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