Variable inlet guide vane
An inlet guide vane is disclosed. The inlet guide vane includes a strut and a flap having a radial length in a radial direction. The flap includes a radially inner portion having a first angular orientation with respect to the strut, a radially outer portion having a second angular orientation with respect to the strut, and a transition portion intermediate the radially inner portion and the radially outer portion, wherein the first angular orientation transitions to the second angular orientation along a portion of the radial length.
1. An inlet guide vane, comprising:
a strut and
a flap having a radial length in a radial direction, the flap comprising
a radially inner portion having a first angular orientation with respect to the strut,
a radially outer portion having a second angular orientation with respect to the strut, and
a transition portion intermediate the radially inner portion and the radially outer portion, where the first angular orientation transitions to the second angular orientation along a portion of the radial length,
wherein the flap comprises a radially outer flap and a radially inner flap separated by a split and wherein the radially outer flap is configured to pivot with respect to the strut independent from the radially inner flap.
2. The inlet guide vane of claim 1 , wherein the radially inner portion has a radially inner length in the radial direction ranging from 20% to 50% of the radial length of the flap.
3. The inlet guide vane of claim 2 , wherein the radially outer portion has a radially outer length in the radial direction ranging from 20% to 50% of the radial length of the flap.
4. The inlet guide vane of claim 3 , wherein the transition portion has a transition length in the radial direction ranging from 5% to 30% of the radial length of the flap.
5. The inlet guide vane of claim 4 , wherein the inlet guide vane includes a longitudinal reference and wherein the first angular orientation defines an angle ranging from 0 degrees to 45 degrees with respect to the longitudinal reference.
6. The inlet guide vane of claim 5 , wherein the second angular orientation defines an angle ranging from 0 degrees to 45 degrees with respect to the longitudinal reference.
7. The inlet guide vane of claim 6 , wherein the first angular orientation defines an angle ranging from 10 degrees to 20 degrees with respect to the longitudinal reference and wherein the second angular orientation defines an angle ranging from 0 degrees to 10 degrees with respect to the longitudinal reference.
8. The inlet guide vane of claim 6 , wherein the first angular orientation is defined as an average angle of attack of an inner chord along the radially inner length with respect to the longitudinal reference and wherein the second angular orientation is defined as an average angle of attack of an outer chord along the radially outer length with respect to the longitudinal reference.
9. A fan section of a gas turbine engine, comprising:
a first rotor having a plurality of rotor blades;
a first stator having a plurality of vanes and positioned downstream of the first rotor; and
a fan inlet guide vane positioned upstream of the first rotor, the fan inlet guide vane comprising:
a strut and
a flap having a radial length in a radial direction, the flap comprising
a radially inner portion having a first angular orientation with respect to the strut,
a radially outer portion having a second angular orientation with respect to the strut, and
a transition portion intermediate the radially inner portion and the radially outer portion, where the first angular orientation transitions to the second angular orientation along a portion of the radial length,
wherein the flap comprises a radially outer flap and a radially inner flap separated by a split and wherein the radially outer flap is configured to pivot with respect to the strut independent from the radially inner flap.
10. The fan section of claim 9 , wherein the radially inner portion has a radially inner length in the radial direction ranging from 20% to 50% of the radial length of the flap.
11. The fan section of claim 10 , wherein the radially outer portion has a radially outer length in the radial direction ranging from 20% to 50% of the radial length of the flap.
12. The fan section of claim 11 , wherein the transition portion has a transition length in the radial direction ranging from 5% to 30% of the radial length of the flap.
13. The fan section of claim 12 , wherein the fan inlet guide vane includes a longitudinal reference, wherein the first angular orientation defines an angle ranging from 10 degrees to 20 degrees with respect to the longitudinal reference and wherein the second angular orientation defines an angle ranging from 0 degrees to 10 degrees with respect to the longitudinal reference.
14. The fan section of claim 13 , wherein the first angular orientation is defined as an average angle of attack of an inner chord along the radially inner length with respect to the longitudinal reference and wherein the second angular orientation is defined as an average angle of attack of an outer chord along the radially outer length with respect to the longitudinal reference.
15. The fan section of claim 9 , further comprising:
a second rotor having a second plurality of rotor blades and positioned downstream of the first stator; and
a second stator having a second plurality of vanes and positioned downstream of the second rotor.
16. The fan section of claim 15 , wherein the first stator comprises: a second fan inlet guide vane, comprising: a second strut and a second flap having a radial length in the radial direction, the second flap comprising a radially inner portion having a first angular orientation with respect to the second strut, a radially outer portion having a second angular orientation with respect to the second strut, and a transition portion intermediate the radially inner portion and the radially outer portion, where the first angular orientation transitions to the second angular orientation along a portion of the radial length.
17. A gas turbine engine, comprising:
a fan section having
a first fan rotor having a plurality of rotor blades;
a first fan stator having a plurality of vanes and positioned downstream of the first fan rotor; and
a fan inlet guide vane positioned upstream of the first fan rotor, the fan inlet guide vane comprising:
a strut and
a flap having a radial length in a radial direction, the flap comprising
a radially inner portion having a first angular orientation with respect to the strut,
a radially outer portion having a second angular orientation with respect to the strut, and
a transition portion intermediate the radially inner portion and the radially outer portion,
where the first angular orientation transitions to the second angular orientation along a portion of the radial length,
wherein the flap comprises a radially outer flap and a radially inner flap separated by a split and wherein the radially outer flap is configured to pivot with respect to the strut independent from the radially inner flap; and
a compressor section having
a first compressor rotor having a plurality of rotor blades;
a first compressor stator having a plurality of vanes and positioned downstream of the first compressor rotor; and
a compressor inlet guide vane positioned upstream of the first compressor rotor, the compressor inlet guide vane comprising:
a second strut and
a second flap having a radial length in the radial direction, the second flap comprising
a radially inner portion having a first angular orientation with respect to the second strut,
a radially outer portion having a second angular orientation with respect to the second strut, and
a transition portion intermediate the radially inner portion and the radially outer portion, where the first angular orientation transitions to the second angular orientation along a portion of the radial length.
18. The gas turbine engine of claim 17 , wherein the fan inlet guide vane includes a fan longitudinal reference, wherein the first angular orientation of the fan inlet guide vane defines an angle ranging from 10 degrees to 20 degrees with respect to the fan longitudinal reference and wherein the second angular orientation of the fan inlet guide vane defines an angle ranging from 0 degrees to 10 degrees with respect to the fan longitudinal reference.
19. The gas turbine engine of claim 18 , wherein the compressor inlet guide vane includes a compressor longitudinal reference, wherein the first angular orientation of the compressor inlet guide vane defines an angle ranging from 10 degrees to 20 degrees with respect to the compressor longitudinal reference and wherein the second angular orientation of the compressor inlet guide vane defines an angle ranging from 0 degrees to 10 degrees with respect to the compressor longitudinal reference.