Patent ID: 9702253
Date: 2017-07-11
CPC Classifications: F01D,F02C,F02K,F05D,Y10T

Claim:
1. Low pressure turbine for a gas turbine engine, the turbine extending along an axis, having an annular conduit for guiding a gas flow and comprising a plurality of stator arrays of blades and a plurality of rotor arrays of blades; the last of said stator arrays, along the advancement direction of the gas flow, comprising a plurality of blades, which define a plurality of spaces between them in circumferential direction; said spaces being split by respective splitters in a radially outer conduit and in a radially inner conduit; characterized in that the radial position of each said splitter is in the neighborhood of a radial reference position which corresponds to a condition in which at least one acoustic mode is of a cut-on type in said radially inner conduit, for a given circumferential order of said at least one acoustic modes, wherein the radial position of each said splitter is optimized by: expressing the acoustic pressure field in said annular conduit in terms of acoustic modes, each defined by a circumferential order and a radial order; selecting one of said circumferential orders; calculating a radial reference position corresponding to a condition in which at least one of the acoustic modes is of the cut-on type in the radially inner conduit for the selected circumferential order; and positioning said splitter in the neighborhood of said radial reference position.