US 11,897,065 B2
Composite turbine disc rotor for turbomachine
Mark Morris, Phoenix, AZ (US); Paul Kurlak, Scottsdale, AZ (US); Stuart Harman, Peoria, AZ (US); Daira Legzdina, Phoenix, AZ (US); and Jason Smoke, Phoenix, AZ (US)
Assigned to HONEYWELL INTERNATIONAL INC., Charlotte, NC (US)
Filed by HONEYWELL INTERNATIONAL INC., Morris Plains, NJ (US)
Filed on Jan. 30, 2020, as Appl. No. 16/777,343.
Claims priority of provisional application 62/934,173, filed on Nov. 12, 2019.
Prior Publication US 2021/0140318 A1, May 13, 2021
Int. Cl. B23P 15/06 (2006.01); F01D 5/30 (2006.01); B23P 15/00 (2006.01); B23K 101/00 (2006.01)
CPC B23P 15/006 (2013.01) [F01D 5/3007 (2013.01); B23K 2101/001 (2018.08); F05D 2230/239 (2013.01); F05D 2230/60 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A method of manufacturing a rotor that defines an axis of rotation for a turbomachine, the method comprising:
providing a lug with a lug body and an interface material disposed on the lug body;
friction welding the lug to a hub member using the interface material, thereby defining a projected structure for an outer radial area of a disc assembly of the rotor;
disposing the projected structure proximate another projected structure that projects from the disc assembly, the projected structure and the other projected structure spaced apart in a circumferential direction relative to the axis of rotation to at least partly define a space for a rotor blade;
removably attaching the rotor blade to the disc assembly within the space; and
the lug body and the hub member made from different materials.