A nozzle segment is disclosed that includes a first platform configured to be connected with a casing of a gas turbine engine, a second platform configured to be connected with the casing, the second platform being disposed apart from the first platform in a radial direction of the gas turbine engine, and a plurality of blades disposed between the first and second platforms and connected thereto, a portion of an inside surface of the first platform or the second platform being scalloped so as to increase a throat area of the nozzle segment in order to increase the nozzle segment's mass flow rate handling capability.

Title
Turbine inlet guide vane with scalloped platform and related method
Application Number
11/959928
Publication Number
20090162193
Application Date
December 19, 2007
Publication Date
June 25, 2009
Inventor
Luciano Mei
Michele D Ercole
Craig Allen Bielek
Simpsonville
SC, US
Massimiliano Mariotti
Agent
GE Global Patent Operation
CT, US
General Electric Company
CT, US
IPC
F01D 09/04
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