US 11,867,195 B2
Gas turbine engine airfoil
Edward J. Gallagher, West Hartford, CT (US); Lisa I. Brilliant, Middletown, CT (US); Joseph C. Straccia, Middletown, CT (US); Stanley J. Balamucki, The Villages, FL (US); Mark A. Stephens, Wethersfield, CT (US); and Kate Hudon, Superior, CO (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed on Apr. 18, 2022, as Appl. No. 17/722,449.
Application 17/722,449 is a continuation of application No. 16/744,749, filed on Jan. 16, 2020, granted, now 11,408,436.
Application 16/744,749 is a continuation of application No. 15/115,360, granted, now 10,570,916, previously published as PCT/US2015/016018, filed on Feb. 16, 2015.
Claims priority of provisional application 61/941,685, filed on Feb. 19, 2014.
Prior Publication US 2022/0235792 A1, Jul. 28, 2022
Int. Cl. F04D 29/32 (2006.01); F04D 29/54 (2006.01); F01D 5/14 (2006.01); F01D 9/02 (2006.01); F02C 3/04 (2006.01); F02C 7/36 (2006.01); F02K 3/06 (2006.01); F04D 29/38 (2006.01)
CPC F04D 29/324 (2013.01) [F01D 5/14 (2013.01); F01D 5/141 (2013.01); F01D 9/02 (2013.01); F02C 3/04 (2013.01); F02C 7/36 (2013.01); F02K 3/06 (2013.01); F04D 29/384 (2013.01); F04D 29/544 (2013.01); F05D 2220/32 (2013.01); F05D 2240/35 (2013.01); F05D 2250/71 (2013.01); F05D 2260/4031 (2013.01); Y02T 50/60 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a combustor section arranged between a compressor section and a turbine section, wherein the compressor section includes at least a low pressure compressor and a high pressure compressor, the high pressure compressor arranged upstream of the combustor section;
a fan section, wherein the low pressure compressor is downstream from the fan section;
an airfoil arranged in the low pressure compressor and including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has an axial stacking offset defined as a distance between a center of gravity for a particular span section and a reference point, the reference point corresponding to an axial center of one of a root of the airfoil or a rotor bore, a positive axial stacking offset being on an axially aft side of the reference point and a negative axial stacking offset being on an axially forward side of the reference point; and
wherein the axial stacking offset at a 10% span position is positive and greater than or equal to an axial stacking offset at the 100% span position, and a maximum positive axial stacking offset value of the axial stacking offset across the 0% span position to the 100% span position of the airfoil is greater than an absolute value of any negative axial stacking offset at the 100% span position.