Rotor with relief features and one-sided load slots
An exemplary turbomachine rotor assembly includes a pair of spaced rails that extend around a cylindrical surface to define a rotor hub. The rails define a space for receiving blades. Load slots are formed in one of the rails. A relief feature is formed in an opposite surface of an opposing rail. The load slots and relief feature utilized to move at least one of the blades into the space.
1. A turbomachine rotor assembly comprising:
a pair of spaced rails including a first rail and a second rail opposing the first rail, the pair of spaced rails extending around a cylindrical surface to define a rotor hub, and the pair of spaced rails defining a space for receiving blades;
a plurality of blade load slots formed in the first rail, the blade load slots extending from an outwardly facing surface of the first rail to an inwardly facing surface of the first rail; and
a plurality of relief features formed on an underside of the second rail and circumferentially aligned with the plurality of blade load slots, the blades moved into the space through one of the plurality of blade load slots and one of the plurality of relief features, and then moved circumferentially to be adjacent to other blades.
2. The turbomachine rotor assembly of claim 1 , wherein the first rail is a cold side rail when mounted in a turbomachine, and the second rail is a hot side rail when mounted in the turbomachine.
3. The turbomachine rotor assembly of claim 2 , wherein the second rail faces a combustion section when mounted in the turbomachine.
4. The turbomachine rotor assembly of claim 1 , including a plurality of lock slots formed in the first rail, the second rail, or both, the plurality of lock slots being utilized to move locks in the space, and the plurality of blade load slots being utilized to move the blades into the space.
5. The turbomachine rotor assembly of claim 4 , wherein the locks include a curved surface facing a curved surface of the lock slots, and an opposed relatively flat surface facing the second rail.
6. The turbomachine rotor assembly of claim 1 , wherein the turbomachine rotor assembly is a compressor section rotor.