Methods and apparatus for assembling gas turbine engines

A guide vane assembly for a gas turbine engine, said guide vane assembly comprising a plurality of circumferentially-spaced guide vanes comprising at least a first, a second,a third, and a fourth guide vane, said second guide vane between said first and third guide vanes, said plurality of guide vanes oriented such that a first circumferential spacing is defined between said first and second guide vanes, and a second circumferential spacing is defined between said second and third guide vanes, said second circumferential spacing is different than said first circumferential spacing, said second guide vane is substantially parallel to said third guide vane, said first and fourth guide vanes are obliquely aligned with respect to said second and third guide vanes.

A gas turbine engine comprising:

• an annular compressor discharge flow path bounded by inner and outer engine casings;
• and
• a plurality of circumferentially-spaced guide vanes disposed within said flow path, said plurality of guide vanes comprising at least a first, second, a third, and a fourth guide vane, said second guide vane positioned between said first and third guide vanes, said plurality of guide vanes oriented such that a first circumferential spacing is defined between said first and second guide vanes and a second circumferential spacing is defined between said second and third guide vanes, said second circumferential spacing is different than said first circumferential spacing, said second guide vane is substantially parallel to said third guide vane, said first and fourth guide vanes are obliquely aligned with respect to said second and third guide vanes.