Turbomachinery blade mounting arrangement

In a turbomachine with an annular flowpath radially bounded by first and second casings, an improvement comprising:

• a one-piece first casing having at least one circumferential recess disposed in a surface facing said flowpath, each recess having a plurality of first blades mounted therein;
• and
• a one-piece second casing having at least one circumferential recess disposed in a surface facing said flowpath, each recess including a first circumferential slot and, axially disposed therefrom, concentric second and third circumferential slots, said third slot being disposed between said second slot and said flowpath;
• and
• a plurality of second blades, each with first and second axially facing tangs on a mounting platform adapted to mate with respective ones of said first slot and third slot in said second casing recess.

In a turbomachine with an annular flowpath radially bounded by first and second casings, an improvement comprising:

• a one-piece first casing having a circumferential recess disposed in a surface facing said flowpath, said recess including axially opposite circumferential slots;
• a one-piece second casing having a circumferential recess disposed in a surface facing said flowpath, each recess including a first circumferential slot and, axially disposed therefrom, concentric second and third circumferential slots, said third slot being disposed between said second slot and said flowpath;
• a plurality of first blades, each with axially facing tangs on a mounting platform adapted to mate with said slots in said first casing recess;
• and
• a plurality of second blades, each with first and second axially facing tangs on a mounting platform adapted to mate with respective ones of said first slot and third slot in said second casing recess.

In a turbomachine with an annular flowpath radially mounted by first and second casings, an improvement comprising:

• a one-piece first casing having a plurality of circumferential recesses disposed in a surface facing said flowpath, each of said recesses including first and second axially opposite circumferential slots;
• a one-piece second casing having a plurality of circumferential recesses disposed in a surface facing said flowpath, each of said recesses including a first circumferential slot and, axially disposed therefrom, concentric second and third circumferential slots, said third slot being disposed between said second slot and said flowpath;
• a plurality of first blades, each with axially facing tangs on a mounting platform adapted to mate with said slots in said first casing recess;
• and
• a plurality of second blades, each with first and second axially facing tangs on a mounting platform adapted to mate with respective ones of said first slot and third slot in said second casing recess.

In a gas turbine engine including a turbine with an annular flowpath therethrough, an improvement comprising:

• a one-piece outer casing bounding said flowpath and having a plurality of circumferential recesses disposed in a radially inner facing surface thereof, each of said recesses including axially opposite circumferential slots;
• a one-piece inner casing bounding said flowpath with a plurality of circumferential recesses disposed in a radially outer facing surface thereof, each of said recesses including a forward circumferential slot and concentric aft radially outer and radially inner circumferential slots;
• a plurality of first turbine blades, each with axially facing tangs on a mounting platform adapted to mate with said slots in said radially inner facing surface recess;
• and
• a plurality of second turbine blades, each with forward and aft axially facing tangs on a mounting platform adapted to mate with respective ones of said forward slot and aft radially outer slot in said radially outer facing surface recess.