COMBUSTOR

摘要

A combustion method and combustor for use in a jet engine, the jet engine having a compressor portion and a turbine portion. The combustor includes an outer tube having a central axis that extends longitudinally intermediate the compressor portion and turbine portion and is positioned to receive air discharged by the compressor portion. An inner tube is positioned within the outer tube that includes an associated outer surface spaced from the inner surface of the outer tube thereby defining a combustion chamber. The outer tube and inner tube include fluid directing structure for communicating at least some of the air discharged by the compressor portion to the combustion chamber. The fluid directing structure directs air into the combustion chamber in a direction offset from the central axis, thereby causing rotation or swirling of the air about the central axis.

主权项

1. A jet engine comprising:
a housing having a first end and a second end and an interior passage that extends from the first end to the second end; a compressor positioned within the first end of the interior passage; a turbine positioned within the second end of the interior passage; and a combustor positioned within the interior passage between the compressor and the turbine, the combustor extending along a central axis and comprising: an outer tube having an outer surface and an inner surface defining a passage; an inner tube positioned within the passage of the outer tube and having an outer surface and an inner surface defining an interior, wherein a fluid passage is defined between the outer surface of the inner tube and the inner surface of the outer tube, the fluid passage being supplied with a mixture of air and combustible fuel, the inner tube and the outer tube having fluid directing structure for causing the mixture of air and combustible fuel within the fluid passage to rotate radially about the central axis.