Methods and devices for turbine blade installation alignment

A gas turbine engine blade alignment device for use with a turbine rotor component comprising an annular disk portion extending in a radial direction from a central axis, a rim portion surrounding the annular disk portion in a circumferential direction, and a plurality of blade root slots extending through the rim portion in an axial direction, each blade root slot having a silhouette of a root geometry profile, the gas turbine engine blade alignment device comprising:

• a guide tool comprising:
• a guide body including a guide slot having a shape matching the silhouette of the root geometry profile;
• and
• an axial projection extending from the guide body circumferentially spaced from the guide slot, the axial projection having a shape of the root geometry profile;
• wherein the turbine rotor component defines a first distance between adjacent blade root slots of the plurality of blade root slots, and a second distance between the guide slot and the axial projection equals the first distance.

A guide for installing an airfoil component in a slotted component of a gas turbine engine, the guide comprising:

• a guide body comprising:
• a slot-facing side;
• an entry side;
• and
• a radially outer side surface connecting the slot-facing side and the entry side;
• a guide slot extending from the entry side to the slot-facing side and penetrating the radially outer side surface, the guide slot having a silhouette matching that of a root portion of the airfoil component;
• and
• an alignment appendage extending from the guide body and having a geometry for axial engagement with a circumferential feature of the slotted component into which the airfoil component is to be installed;
• wherein the alignment appendage comprises a guide rail extending axially from the slot-facing side;
• and
• wherein the guide rail is configured to engage a broach slot in the slotted component radially inward of a root slot in the slotted component, the broach slot aligned with and disposed radially inward of the root slot.

A guide for installing an airfoil component in a slotted component of a gas turbine engine, the guide comprising:

• a guide body comprising:
• a slot-facing side;
• an entry side;
• and
• a radially outer side surface connecting the slot-facing side and the entry side;
• a guide slot extending from the entry side to the slot-facing side and penetrating the radially outer side surface, the guide slot having a silhouette matching that of a root portion of the airfoil component;
• and
• an alignment appendage extending from the guide body and having a geometry for axial engagement with a circumferential feature of the slotted component into which the airfoil component is to be installed;
• wherein the alignment appendage comprises a wing extending circumferentially from the guide body;
• and
• wherein the wing extends radially outward of the guide slot and is configured to be disposed between platforms of the airfoil component and an adjacent airfoil component installed in the slotted component.