US 12,326,154 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, Cincinnati, OH (US)
Filed on Jun. 12, 2024, as Appl. No. 18/741,419.
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 2024/0328431 A1, Oct. 3, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. F01D 5/14 (2006.01); F02K 3/06 (2006.01); F04D 29/38 (2006.01)
CPC F04D 29/388 (2013.01) [F02K 3/06 (2013.01); F05D 2220/36 (2013.01); F05D 2300/603 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An indirect drive turbine engine, comprising:
a fan;
a turbomachine defining an engine centerline and comprising a compressor section, a combustor in fluid communication with the compressor section, a turbine section in fluid communication with the combustor, and a speed reduction device driven by the turbine section for rotating the fan;
the fan comprising a first stage of composite airfoils circumferentially arranged about the engine centerline, 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 comprising a first sheath 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 comprising a second sheath 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 relate 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); and
wherein the first airfoil extends spanwise between a first root and a first tip to define a first span length and the second airfoil extends spanwise between a second root and a second tip to define a second span length less than the first span length.