Design and Performance of an Experimental Annular Turbojet Combustor With High-Velocity-Air Admission Through One Wall

Carl T Norgren

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NASA NTRS · 19670022691

Design and Performance of an Experimental Annular Turbojet Combustor With High-Velocity-Air Admission Through One Wall

Carl T Norgren

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Abstract

An experimental, annular, turbojet combustor was designed to eliminate the conventional combustor-inlet diffuser. Instead, high-velocity air was supplied directly to the combustor. This stream was split into two parts: (1) the primary in which combustion was sustained, and (2) the secondary in which the stream momentum was used to facilitate mixing with the hot primary gases. The air was admitted through only one wall of the combustor liner except for approximately 5 percent that was used to cool the inner combustor surfaces. By integrating the inlet and outlet diffuser design with the combustion chamber, an overall reduction in length of 30 percent was obtained over conventional configurations. A rectangular segment of this combustor was tested with vaporized propane fuel.

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BibTeX RIS

Carl T Norgren. 1958-12-01. Design and Performance of an Experimental Annular Turbojet Combustor With High-Velocity-Air Admission Through One Wall. https://ntrs.nasa.gov/citations/19670022691

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