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A rotor body rotates about an axis of rotation. A ledge provides a holding structure for holding blades. A plurality of blades are positioned beneath the ledge. A load slot is sized to allow a mount portion of the blades to be moved radially inwardly of the ledge. The blades are moved circumferentia

A rotor body rotates about an axis of rotation. A ledge provides a holding structure for holding blades. A plurality of blades are positioned beneath the ledge. A load slot is sized to allow a mount portion of the blades to be moved radially inwardly of the ledge. The blades are moved circumferentially to have the mounted structure radially inwardly of the ledge. A lock slot is positioned on one circumferential side of the load slot. The lock slot is formed to receive a lock, and the lock is partially received within a portion of at least one of the blades, to lock the blades within the rotor, and a shield slot on a second circumferential side of the load slot. The shield slot is sized to be different from the lock slot such that a lock cannot be inadvertently positioned within the shield slot.

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1. A rotor for use in a gas turbine engine comprising: a rotor body, said rotor body for rotation about an axis of rotation and said rotor body extending circumferentially about said axis of rotation, and also having an axial direction along said axis of rotation;a ledge to provide a holding structu

1. A rotor for use in a gas turbine engine comprising: a rotor body, said rotor body for rotation about an axis of rotation and said rotor body extending circumferentially about said axis of rotation, and also having an axial direction along said axis of rotation;a ledge to provide a holding structure for holding blades radially inwardly of said ledge;a plurality of blades have mount structure positioned beneath said ledge, said blades having an airfoil extending upwardly from a platform, and said mount structure extending inwardly from said platform;a load slot in said ledge, said load slot being sized to allow said mount structure of said blades to be moved radially inwardly of said ledge by positioning said mounting structure to move through said load slot, and said blades then being moved circumferentially to have said mount structure radially inwardly of said ledge; anda lock slot in said ledge on one circumferential side of said load slot, said lock slot receiving a lock, said lock also being partially received within an opening in said platform of at least one of said blades, said lock being separate from said blade and inserted into said opening, and a shield slot in said ledge on a second circumferential side of said load slot, said shield slot being sized to be different from said lock slot such that a lock cannot be inadvertently positioned within said shield slot. 2. The rotor as set forth in claim 1, wherein said shield slot and said lock slot each extend axially into said ledge for a depth, with a depth of said shield slot being less than a depth of said lock slot. 3. The rotor as set forth in claim 2, wherein each of said lock slot and said shield slot are curved portions each formed at at least one radius. 4. The rotor as set forth in claim 3, wherein said curved portions of both said lock slot and said shield slot are part circular portions. 5. The rotor as set forth in claim 4, wherein a radius of said lock slot is greater than a radius of said shield slot. 6. The rotor as set forth in claim 2, wherein a circumferential distance from a circumferential edge of said load slot most adjacent said lock slot to an edge of said lock slot most adjacent said load slot is defined as a first distance, and a second distance is defined from a circumferential edge of said load slot closest to said shield slot, to an edge of said shield slot most adjacent to said load slot, with said second distance being less than said first distance. 7. The rotor as set forth in claim 1, wherein each of said lock slot and said shield slot are curved portions each formed at at least one radius. 8. The rotor as set forth in claim 7, wherein said curved portions of both said lock slot and said shield slot are part circular portions. 9. The rotor as set forth in claim 8, wherein a radius of said lock slot is greater than a radius of said shield slot. 10. The rotor as set forth in claim 1, wherein a circumferential distance from a circumferential edge of said load slot most adjacent said lock slot to an edge of said lock slot most adjacent said load slot is defined as a first distance, and a second distance is defined from a circumferential edge of said load slot closest to said shield slot, to an edge of said shield slot most adjacent to said load slot, with said second distance being less than said first distance. 11. The rotor as set forth in claim 1, wherein there are a greater number of said plurality of blades than there are said locks. 12. A gas turbine engine comprising: a compressor, a combustion section, and a turbine section; andsaid compressor section, including at least a first compressor rotor, a rotor body for rotation about an axis of rotation and said rotor body extending circumferentially about said axis of rotation, and also having an axial direction along said axis of rotation;a ledge to provide a holding structure for holding blades radially inwardly of said ledge;a plurality of blades have mount structure positioned beneath said ledge, said blades having an airfoil extending upwardly from a platform, and said mount structure extending inwardly from said platform;a load slot in said ledge, said load slot being sized to allow said mount structure of said blades to be moved radially inwardly of said ledge by positioning said mounting structure to move through said load slot, and said blades then being moved circumferentially to have said mount structure radially inwardly of said ledge; anda lock slot in said ledge on one circumferential side of said load slot, said lock slot receiving a lock, said lock also being partially received within an opening in said platform of at least one of said blades, said lock being separate from aid blade and inserted into said opening, and a shield slot in said ledge on a second circumferential side of said load slot, said shield slot being sized to be different from said lock slot such that a lock cannot be inadvertently positioned within said shield slot. 13. The engine as set forth in claim 12, wherein said shield slot and said lock slot each extend axially into said ledge for a depth, with a depth of said shield slot being less than a depth of said lock slot. 14. The engine as set forth in claim 13, wherein each of said lock slot and said shield slot are curved portions each formed at at least one radius. 15. The engine as set forth in claim 14, wherein said curved portions of both said lock slot and said shield slot are part circular portions. 16. The engine as set forth in claim 15, wherein a radius of said lock slot is greater than a radius of said shield slot. 17. The engine as set forth in claim 13, wherein a circumferential distance from a circumferential edge of said load slot most adjacent said lock slot to an edge of said lock slot most adjacent said load slot is defined as a first distance, and a second distance is defined from a circumferential edge of said load slot closest to said shield slot, to an edge of said shield slot most adjacent to said load slot, with said second distance being less than said first distance. 18. The engine as set forth in claim 12, wherein each of said lock slot and said shield slot are curved portions each formed at at least one radius. 19. The engine as set forth in claim 18, wherein said curved portions of both said lock slot and said shield slot are part circular portions. 20. The engine as set forth in claim 19, wherein a radius of said lock slot is greater than a radius of said shield slot. 21. The engine as set forth in claim 12, wherein a circumferential distance from a circumferential edge of said load slot most adjacent said lock slot to an edge of said lock slot most adjacent said load slot is defined as a first distance, and a second distance is defined from a circumferential edge of said load slot closest to said shield slot, to an edge of said shield slot most adjacent to said load slot, with said second distance being less than said first distance. 22. The engine as set forth in claim 12, wherein there are a greater number of said plurality of blades than there are said locks.