Turbine engine with composite airfoils
A turbine engine includes a turbomachine having a compressor section, a combustor, and a turbine section. The turbine engine includes a set of composite airfoils, where a composite airfoil of the set of composite airfoils includes a composite body that extends chordwise between a composite leading edge and a trailing edge. A leading edge protector is coupled to the composite body. A platform extends from the composite airfoil.
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;
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, and receiving at least a portion of, the composite body,
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
a platform comprising a structural body portion and a flowpath surface portion joined to the structural body portion, wherein the flowpath surface portion defines a radially outer surface that extends from the at least one composite fan blade or the at least one composite outlet guide vane, and wherein the flowpath surface portion defines at least one wing having a resilient seal member.
2 . The turbine engine of claim 1 , wherein the radially outer surface of the platform fixes an inner flowpath boundary.
3 . The turbine engine of claim 2 , wherein the flowpath surface portion extends circumferentially and the at least one wing includes a pair of wings.
4 . The turbine engine of claim 2 , wherein the at least one wing is frangible.
5 . The turbine engine of claim 1 , wherein the APF1 relates to the APF2 by an expression:
APF
1
APF
2
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).
6 . The turbine engine of claim 5 , wherein the SPF is greater than or equal to 0.95 and less than or equal to 2.5 (0.95≤SPF≤2.5).
7 . The turbine engine of claim 1 , wherein a bypass ratio is from 10:1 to 22:1.
8 . The turbine engine of claim 1 , wherein the speed reduction device is a power gearbox.
9 . The turbine engine of claim 1 , wherein the composite body is a polymer matrix composite.
10 . The turbine engine of claim 9 , wherein the leading edge protector is a metallic leading edge protector.
11 . The turbine engine of claim 1 , wherein the resilient seal member is silicone.
12 . The turbine engine of claim 1 , wherein the at least one composite fan blade is a plurality of composite fan blades and the radially outer surface extends between adjacent composite fan blades of the plurality of composite fan blades.
13 . The turbine engine of claim 1 , wherein the at least one composite outlet guide vane is a plurality of composite outlet guide vanes and the radially outer surface extends between adjacent composite outlet guide vanes of the plurality of composite outlet guide vanes.