Turbine engine with composite airfoils
A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
1 . A turbine engine comprising:
a fan;
a turbomachine comprising a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor;
a speed reduction device driven by the turbine section and configured for rotating the fan; and
composite airfoils comprising at least one composite fan blade and at least one composite outlet guide vane downstream from the at least one composite fan blade;
wherein an airfoil of the composite airfoils comprises:
a composite body extending chordwise from a body leading edge to a body trailing edge, and
a leading edge protector having a protector leading edge different from the body leading edge, the leading edge protector receiving at least a portion of the body leading edge;
wherein a leading length (LL) extends chordwise from the protector leading edge to an end of the leading edge protector and a chord length (CL) extends chordwise from the protector leading edge to the body trailing edge, and
wherein the LL is related to the CL by an airfoil protection factor
(
APF
)
=
(
LL
)
(
CL
)
;
and a first APF (APF1) for the at least one composite fan blade is greater than or equal to 0.2 and less than or equal to 0.30 (0.2≤APF1≤0.3) and a second APF (APF2) for the at least one composite outlet guide vane is greater than or equal to 0.08 and less than or equal to 0.17 (0.08≤APF2≤0.17); and
wherein at least one portion of the composite body of the at least one composite fan blade or the at least one composite outlet guide vane is configured to flex or configured to break.
2 . The turbine engine of claim 1 , wherein the at least one portion of the composite body comprises a matrix having first reinforcing fibers and an adjacent portion of the composite body includes a matrix having second reinforcing fibers, the second reinforcing fibers different from the first reinforcing fibers.
3 . The turbine engine of claim 2 , wherein the first reinforcing fibers are glass fibers and the second reinforcing fibers are carbon fibers.
4 . The turbine engine of claim 3 , wherein the leading edge protector comprises at least one metallic cladding element.
5 . The turbine engine of claim 4 , wherein the leading edge protector covers a smaller area as compared to a leading edge protector for the composite body without the at least one portion.
6 . The turbine engine of claim 3 , wherein the glass fibers provide a higher strain to failure capability compared to carbon fibers in the composite body alone.
7 . The turbine engine of claim 3 , wherein the at least one portion of the composite body is disposed adjacent to the body leading edge or the body trailing edge.
8 . The turbine engine of claim 1 , wherein the APF1 relates to the APF2 by an expression: APF1/APF2 to define a stage protection factor (SPF), and wherein the SPF is greater than or equal to 0.7 and less than or equal to 4 (0.7≤SPF≤4).
9 . The turbine engine of claim 8 , wherein the SPF is greater than or equal to 0.95 and less than or equal to 2.5 (0.95≤SPF≤2.5).
10 . The turbine engine of claim 8 , wherein the at least one composite fan blade extends spanwise between a first root and a first tip to define a first span length and the at least one composite outlet guide vane extends spanwise between a second root and a second tip to define a second span length and the SPF is determined at a location between 20% and 80% of the first span length and the second span length, inclusive of endpoints.
11 . The turbine engine of claim 1 , wherein the speed reduction device is a power gearbox.
12 . The turbine engine of claim 1 , wherein a bypass ratio is from 10:1 to 22:1.
13 . The turbine engine of claim 1 , wherein a primary region of the composite body comprises first reinforcing fibers having a first stiffness and a first elongation and a secondary region of the composite body comprises second reinforcing fibers having a second stiffness and a second elongation, wherein the second stiffness is less than the first stiffness and the second elongation is greater than the first elongation.
14 . The turbine engine of claim 13 , wherein the secondary region comprises a polymeric matrix including high-elongation reinforcing fibers.
15 . The turbine engine of claim 14 , wherein the high-elongation reinforcing fibers include E-glass fibers, S-glass fibers, or a combination thereof.
16 . The turbine engine of claim 13 , wherein the leading edge protector covers a portion of the secondary region.