Pressurized gas turbine engine
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United States of America Patent
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Mar 18, 2003
Grant Date -
Mar 13, 2003
app pub date -
Mar 21, 2001
filing date -
Mar 21, 2001
priority date (Note) -
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Abstract
A pressurized gas turbine engine is disclosed which utilizes a new turbine design. Pressurized gas is supplied by nozzle gas ways in the turbine to gas nozzles affixed to the perimeter of the turbine. The gas nozzles may be recessed in the turbine perimeter or extend from the turbine perimeter. The gas nozzles may be equipped with gas exit cones to enhance the efficiency of the nozzles. The axis of the nozzles have an oblique angle with the direction of rotation of the turbine. Pressurized gas is supplied to the nozzle gas ways through one or more shaft gas ways in the turbine shaft, or is supplied through engine gas ports in the front wall of the turbine engine to gas supply zones which are hydraulically separated by seal rings on the front face of the turbine, each gas supply zone being hydraulically connected to one or more nozzle gas ways.
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