US 12,345,177 B2
Turbine engine with composite airfoils
Nicholas Joseph Kray, Mason, OH (US); and Arthur William Sibbach, Boxford, MA (US)
Assigned to General Electric Company, Evendale, OH (US)
Filed by General Electric Company, Evendale, OH (US)
Filed on Aug. 16, 2024, as Appl. No. 18/807,233.
Application 18/807,233 is a continuation in part of application No. 18/741,419, filed on Jun. 12, 2024.
Application 18/741,419 is a continuation in part of application No. 18/171,533, filed on Feb. 20, 2023, granted, now 12,158,082.
Prior Publication US 2024/0410285 A1, Dec. 12, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. F01D 5/14 (2006.01); F01D 5/28 (2006.01); F02C 3/06 (2006.01)
CPC F01D 5/282 (2013.01) [F02C 3/06 (2013.01); F05D 2300/603 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A turbine engine, comprising:
an engine core defining an engine centerline and comprising a rotor and a stator;
a first stage of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor, a first airfoil of the first stage of composite airfoils comprising:
a first composite portion extending chordwise between a first composite leading edge and a first trailing edge;
a first leading edge protector receiving at least a portion of the first composite leading edge of the first composite portion, the first leading edge protector extending chordwise from a first leading edge towards the first composite portion for a first leading length (FLL); and
the first composite portion and the first leading edge protector together defining an exterior surface of the first airfoil and extending chordwise between the first leading edge and the first trailing edge to define a first chord length (FCL);
a second stage of composite airfoils located downstream of the first stage of composite airfoils and circumferentially arranged about the engine centerline, a second airfoil of the second stage of composite airfoils comprising:
a second composite portion extending chordwise between a second composite leading edge and a second trailing edge;
a second leading edge protector receiving at least a portion of the second composite leading edge of the second composite portion, the second leading edge protector extending chordwise from a second leading edge towards the second composite portion for a second leading length (SLL); and
the second composite portion and the second leading edge protector together defining an exterior surface of the second airfoil and extending chordwise between the second leading edge and the second trailing edge to define a second chord length (SCL);
wherein the FLL and the FCL are related to the SLL and the SCL by a stage protection factor (SPF),
wherein the

OG Complex Work Unit Math
and the SPF is greater than or equal to 0.7 and less than or equal to 4 (0.7≤SPF≤4);
wherein at least one of the first stage of composite airfoils or the second stage of composite airfoils includes a row of individual airfoils, the row including no more than 18 and no less than 13 fan blades, wherein each of the fan blades has a solidity defined by a ratio of airfoil chord over a circumferential pitch of the fan blades, measured at 60% of a radial distance from the engine centerline to a tip, of less than about 1.6, and wherein a ratio of the solidity measured at 60% of the radial distance from the engine centerline to the tip to a relative Mach number at the same radial location is no greater than about 1.50.