Vane assembly of a gas turbine engine
A first stage vane array of a high pressure turbine that may be for a geared turbofan engine includes a plurality of airfoils circumferentially spaced from one-another and orientated about an engine axis. Each airfoil has a leading edge and a trailing edge with the trailing edge being circumferentially separated by the next adjacent trailing edge by a pitch distance. The leading a trailing edges of each one of the plurality of airfoils are axially separated by an axial chord length. A pitch-to-chord ratio of the pitch distance over the axial chord length is equal to or greater than 1.7.
1. A high pressure turbine of a gas turbine engine comprising:
a first stage vane assembly comprising a first airfoil circumferentially spaced from an adjacent second airfoil and orientated about an engine axis, wherein the first airfoil has a leading edge and a trailing edge with the trailing edge configured to be circumferentially separated from the trailing edge of the second airfoil by a pitch distance, and the leading and trailing edges of the first airfoil are axially separated by an axial chord length, and wherein a pitch-to-chord ratio of pitch distance over axial chord length is equal to or greater than 1.7.
2. The high pressure turbine set forth in claim 1 , wherein the first airfoil has a thickness-to-axial chord ratio that is greater than forty percent.
3. The high pressure turbine set forth in claim 2 , wherein the thickness-to-axial chord ratio is about fifty-three percent.
4. The high pressure turbine set forth in claim 1 , wherein the trailing edge has an angle that is greater than seventy-five degrees relative to the engine axis.
5. The high pressure turbine set forth in claim 4 , wherein the pitch-to-chord ratio is within a range of about 1.7 to 2.0.
6. The high pressure turbine set forth in claim 1 , wherein the pitch-to-chord ratio is within a range of about 1.7 to 2.0.
7. The high pressure turbine set forth in claim 1 , wherein the pitch-to-chord ratio is about 1.8.
8. The high pressure turbine set forth in claim 1 further comprising:
an inner endwall, wherein the first airfoil projects radially outward from an outward surface of the inner endwall and the outward surface includes at least in-part a concave region located axially between the leading and trailing edges and circumferentially adjacent to the first airfoil.
9. The high pressure turbine set forth in claim 8 , wherein the outward surface includes a convex region proximate to the leading edge of the first airfoil.
10. The high pressure turbine set forth in claim 1 further comprising:
an outer endwall, wherein the first airfoil projects radially inward from an inward surface of the outer endwall and the inward surface includes at least in-part a concave region located axially between the leading and trailing edges and circumferentially adjacent to the first airfoil.
11. The high pressure turbine set forth in claim 10 , wherein the inward surface includes a convex region proximate to the leading edge of the first airfoil.
12. A gas turbine engine comprising:
a low pressure turbine; and
a high pressure turbine upstream of the low pressure turbine with respect to a core airflow, the high pressure turbine comprising a vane array including a plurality of airfoils circumferentially spaced from one-another and orientated about an engine axis, wherein each one of the plurality of airfoils have a leading edge and a trailing edge with each one of the trailing edges being circumferentially separated by the next adjacent trailing edge by a pitch distance, and the leading and trailing edges of each one of the plurality of airfoils are axially separated by an axial chord length, and wherein a pitch-to-chord ratio of pitch distance over axial chord length is equal to or greater than 1.7.