US 12,270,310 B2
Test rotor blade for an aircraft engine blade-off test
Dikran Mangardich, Richmond Hill (CA); and Paul Stone, Guelph (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on Aug. 25, 2023, as Appl. No. 18/238,315.
Prior Publication US 2025/0067195 A1, Feb. 27, 2025
Int. Cl. F01D 21/00 (2006.01); F01D 5/12 (2006.01); G01M 15/14 (2006.01)
CPC F01D 21/003 (2013.01) [F01D 5/12 (2013.01); G01M 15/14 (2013.01); F05D 2240/30 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A test rotor blade for an aircraft engine bladed rotor, the test rotor blade comprising:
a blade body, the blade body extends between and to a base end and a tip end, the blade body extends between and to a leading edge and a trailing edge, the blade body forms a first side surface and a second side surface, each of the first side surface and the second side surface extend from the leading edge to the trailing edge, the blade body forms:
a leading-edge pocket at the leading edge;
a trailing-edge pocket at the trailing edge; and
a hole extending through the blade body from the leading-edge pocket to the trailing edge pocket, the hole includes a first linear segment extending from a first end, a second linear segment extending from a second end, and a hole length from the first end to the second end, the first end is disposed at the leading-edge pocket, and the second end is disposed at the trailing-edge pocket;
the blade body includes a first side wall and a second side wall, the first side wall has a first wall thickness extending between and to the first side surface and the hole, the second side wall has a second wall thickness extending between and to the second side surface and the hole, and the second wall thickness is 0.4 to 0.9 times the first wall thickness.