Patent ID: 11952943
Assignee: PRATT & WHITNEY CANADA CORP.
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 8:
9. A gas turbine engine comprising:
a compressor for pressurizing air;
a combustor in which compressed air from the compressor is mixed with fuel and ignited for generating a stream of hot combustion gases; and
a turbine section for extracting energy from the combustion gases;
the compressor including:
a substantially annular gas path having a central axis and extending axially along the central axis;
a strut extending radially in the gas path;
a strut passage defined in the gas path, the strut passage extending axially along the central axis between a leading edge of the strut and a trailing edge of the strut;
a plurality of variable orientation guide vanes extending radially in the gas path, the variable orientation guide vanes being uniformly angularly spaced-apart around the central axis, two adjacent variable orientation guide vanes of the plurality of variable orientation guide vanes having a leading edge axially overlapping the strut passage and a trailing edge disposed downstream of the strut passage at one or more orientations of the two adjacent variable orientation guide vanes; and
a rotor disposed downstream of the plurality of variable orientation guide vanes and configured to compress the air,

wherein:
the strut is angularly positioned between the two adjacent variable orientation guide vanes of the plurality of variable orientation guide vanes;
a first of the two adjacent variable orientation guide vanes is pivotable about a pivot point; and
a first angular spacing between the strut and the first of the two adjacent variable orientation guide vanes is greater than a chordwise distance between the leading edge of the first of the two adjacent variable orientation guide vanes and the pivot point.