US 11,885,233 B2
Turbine engine with airfoil having high acceleration and low blade turning
Ernesto Sozio, Orbassano (IT); Francesco Bertini, Piossasco (IT); Jeffrey Donald Clements, Mason, OH (US); Jonathan Ong, Garching (DE); Lyle Douglas Dailey, West Chester, OH (US); Paul Hadley Vitt, Liberty Twp, OH (US); and Matteo Renato Usseglio, Turin (IT)
Assigned to General Electric Company, Schenectady, NY (US); and GE Avio S.r.l., Rivolta di Torino (IT)
Filed by General Electric Company, Schenectady, NY (US); and GE Avio S.r.l., Rivalta di Torino (IT)
Filed on Jul. 28, 2022, as Appl. No. 17/876,009.
Application 17/876,009 is a continuation of application No. 17/148,635, filed on Jan. 14, 2021, granted, now 11,434,765.
Claims priority of application No. 102020000005146 (IT), filed on Mar. 11, 2020.
Prior Publication US 2023/0130213 A1, Apr. 27, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. F01D 5/14 (2006.01); F04D 29/32 (2006.01); F04D 29/54 (2006.01)
CPC F01D 5/141 (2013.01) [F04D 29/324 (2013.01); F04D 29/544 (2013.01); F05D 2220/32 (2013.01); F05D 2240/30 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An airfoil assembly comprising:
at least two airfoils carried by a rotor and configured to rotate about a rotational axis, the at least two airfoils being circumferentially spaced from each other, with respect to the rotational axis, to define a pitch (P) therebetween, each airfoil of the at least two airfoils comprising:
an outer wall defining a pressure side and a suction side extending in a chord-wise direction between a leading edge to a trailing edge and extending in a span-wise direction between a root and a tip;
a mean camber line extending between the leading edge and the trailing edge and intersecting the leading edge to define a leading edge intersection, and intersecting the trailing edge to define a trailing edge intersection;
an inlet angle, βin, in degrees, defined by an included angle between a line parallel to the mean camber line at the leading edge intersection and the rotational axis; and
an outlet angle, βout, in degrees, defined by an included angle between a line parallel to the mean camber line at the trailing edge intersection and the rotational axis;
an axial chord length (Cax) extending between the leading edge and the trailing edge in an axial direction with respect to the rotational axis;
a blade turning (BT) of less than 100 degrees along at least 30% of a span of the airfoil, wherein the blade turning (BT) is determined by:

OG Complex Work Unit Math
 and
an airfoil solidity (Sl) of the at least two airfoils is determined by:

OG Complex Work Unit Math
wherein the airfoil solidity (Sl) is greater than or equal to 0.6 and less than or equal to 1.2 (0.6≤Sl≤1.2); and
wherein βin is constant along the span from the root to the tip, or βout is constant along the span from the root to the tip.