Nozzle guide vane structure for a gas turbine engine
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United States of America Patent
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-
Jan 17, 1989
Issued Date -
N/A
app pub date -
Jun 24, 1980
filing date -
May 5, 1977
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
A nozzle guide vane assembly for a gas turbine engine comprises inner and outer porous sheet metal platform rings and a plurality of aerofoils extending between the rings, each of the aerofoil portions having mounting means at its inner and outer extremities by which the aerofoils, and thus the rings, are supported from fixed engine structure.
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