A fixture (100, 300) for transferring a plurality of turbine blades, each having a dovetail, into a rotor wheel (130, 132) of a turbomachine, the rotor wheel (130, 132) including a plurality of circumferentially spaced dovetail slots (132, 146, 166, 170, 346, 366), the fixture (100, 300) comprising: a first body (140, 340) having an arcuate radially inward surface (142, 342) and a radially outward surface (144, 344) including a plurality of dovetail slots (132, 146, 166, 170, 346, 366) therein shaped to engage the dovetails of the plurality of turbine blades, wherein the arcuate radially inward surface of the first body is shaped to contact a rotor of the turbomachine and shaped to contact a platform, the platform being axially coupled to and/or mounted on an axial sidewall of the rotor wheel (130, 132); and a first alignment aperture (150, 350) extending axially through the first body (140, 340) relative to a centerline axis of the turbomachine, and positioned for alignment with a portion of the rotor wheel (130, 132) such that the plurality of dovetail slots (132, 146, 166, 170, 346, 366) of the first body (140, 340) are substantially axially aligned with the plurality of dovetail slots (132, 146, 166, 170, 346, 366) of the rotor wheel (130, 132) for at least partial transfer of the turbine blade thereto from the fixture (100, 300), wherein the dovetails of the plurality of turbine blades are slidably removable from the plurality of dovetail slots (132, 146, 166, 170, 346, 366) of the first body (140, 340) for guided insertion into the plurality of dovetail slots (132, 146, 166, 170, 346, 366) of the rotor wheel (130, 132), characterized in that said at least first alignment aperture is positioned circumferentially between dovetail slots of the fixture, and is designed and arranged in a way that it allows a user to align said dovetail slots of said fixture with said dovetail slots of said rotor wheel by receiving or at least partially engaging an alignment pin into said first alignment aperture. a first body (140, 340) having an arcuate radially inward surface (142, 342) and a radially outward surface (144, 344) including a plurality of dovetail slots (132, 146, 166, 170, 346, 366) therein shaped to engage the dovetails of the plurality of turbine blades, wherein the arcuate radially inward surface of the first body is shaped to contact a rotor of the turbomachine and shaped to contact a platform, the platform being axially coupled to and/or mounted on an axial sidewall of the rotor wheel (130, 132); and a first alignment aperture (150, 350) extending axially through the first body (140, 340) relative to a centerline axis of the turbomachine, and positioned for alignment with a portion of the rotor wheel (130, 132) such that the plurality of dovetail slots (132, 146, 166, 170, 346, 366) of the first body (140, 340) are substantially axially aligned with the plurality of dovetail slots (132, 146, 166, 170, 346, 366) of the rotor wheel (130, 132) for at least partial transfer of the turbine blade thereto from the fixture (100, 300), wherein the dovetails of the plurality of turbine blades are slidably removable from the plurality of dovetail slots (132, 146, 166, 170, 346, 366) of the first body (140, 340) for guided insertion into the plurality of dovetail slots (132, 146, 166, 170, 346, 366) of the rotor wheel (130, 132), characterized in that said at least first alignment aperture is positioned circumferentially between dovetail slots of the fixture, and is designed and arranged in a way that it allows a user to align said dovetail slots of said fixture with said dovetail slots of said rotor wheel by receiving or at least partially engaging an alignment pin into said first alignment aperture.