Apparatus for circumferential separation of turbine blades

An apparatus for expanding a circumferential separation between a first turbine blade and a second turbine blade each positioned within a rotor wheel of a turbomachine, the apparatus comprising:

• a length-adjustable elongate member having opposing first and second ends, and configured to impart a separating force against the first and second turbine blades circumferentially outward from a targeted turbine blade of the rotor wheel, thereby increasing the circumferential separation between the targeted turbine blade and shroud portions of the first and second turbine blades;
• a first clasp coupled to the first end of the length-adjustable elongate member, the first clasp shaped to at least partially engage an airfoil profile of the first turbine blade proximal to the shroud portion of the first turbine blade;
• and
• a second clasp coupled to the second end of the length-adjustable elongate member, the second clasp shaped to at least partially engage an airfoil profile of the second turbine blade proximal to the shroud portion of the second turbine blade, the first and second turbine blades being separated by the targeted turbine blade positioned circumferentially therebetween.

An apparatus for expanding a circumferential separation between a first turbine blade and a second turbine blade each positioned within a rotor wheel of a turbomachine, wherein the first and second turbine blades are separated by a targeted turbine blade positioned circumferentially therebetween, the apparatus comprising:

• a length-adjustable elongate member having opposing first and second ends;
• a first clasp rotatably coupled to the first end of the length-adjustable elongate member, the first clasp shaped to at least partially engage an airfoil profile of the first turbine blade proximal to a shroud portion of the first turbine blade;
• and
• a second clasp rotatably coupled to the second end of the length-adjustable elongate member, the second clasp shaped to at least partially engage an airfoil profile of the second turbine blade proximal to a shroud portion of the second turbine blade;
• wherein each of the first and second clasps impart a separating force against the first and second turbine blades circumferentially outward, to expand the circumferential separation between targeted turbine blade and the shroud portions of the first and second turbine blades.