Notched turbine airfoils for weight reduction in gas turbine engines
View Patent ↗An airfoil adapted for use in a gas turbine engine includes a base and an airfoil body that extends radially outward from the base relative to an axis to a tip of the airfoil body. The airfoil body has a leading edge, a trailing edge, a suction side, and a pressure side. The airfoil body is formed to include notches that extend into the airfoil body to reduce a weight of the airfoil.
1. A turbine wheel assembly adapted for use in a gas turbine engine, the turbine wheel assembly comprising,
a rotor hub configured to rotate about an axis, and
an airfoil coupled with the rotor hub and configured to rotate the rotor hub about the axis in response to gases acting on the airfoil during use of the turbine wheel assembly, the airfoil including a base coupled with the rotor hub and an airfoil body that extends radially outward from the base to a tip of the airfoil body, the airfoil body having a leading edge, a trailing edge spaced apart axially from the leading edge, a suction side that extends between the leading edge and the trailing edge, and a pressure side that extends between the leading edge and the trailing edge opposite the suction side,
wherein the pressure side of the airfoil is formed to define a plurality of notches that extend into an external surface of the airfoil toward the suction side, at least one of the plurality of notches extends chordwise between the leading edge and the trailing edge along a majority of a chord length of the airfoil body, and each of the plurality of notches are spaced apart radially from a neighboring one of the plurality of notches between the base and the tip so that a weight of the airfoil is minimized while isolating radial separation of pressure surface boundary layer separation within each of the plurality of notches to allow airflow along the airfoil,
wherein each of the plurality of notches includes an inner surface and an outer surface spaced radially apart from the inner surface towards the tip of the airfoil, the inner surface and the outer surface are planar, and the radial distance between the inner surface and the outer surface of each of the plurality of notches defines a height for each of the plurality of notches, the plurality of notches includes a first notch having a first height and a second notch spaced radially apart from the first notch and having a second height equal to the first height, wherein a radial distance between the outer surface of the first notch and the inner surface of the second notch is less than the first height.
2. The turbine wheel assembly of claim 1 , wherein the plurality of notches includes a first notch having a first height and a second notch spaced radially apart from the first notch and having a second height less than the first height.
3. The turbine wheel assembly of claim 1 , wherein each of the plurality of notches is airfoil shaped when viewed radially inward.
4. The turbine wheel assembly of claim 1 , wherein at least one notch of the plurality of notches includes a radially extending support that extends between and interconnects the inner surface and the outer surface to define a first portion of the at least one notch located near the leading edge and a second portion of the at least one notch located near the trailing edge, and the support provides a portion of the external surface of the pressure side.
5. The turbine wheel assembly of claim 1 , wherein a depth of at least one of the plurality of notches varies along a chord length of the of the airfoil body.
6. The turbine wheel assembly of claim 1 , wherein at least one of the plurality of notches is spaced axially apart from the leading edge of the airfoil body, the leading edge disposed at the axially forward most point of the airfoil body.
7. An airfoil adapted for use in a gas turbine engine, the airfoil comprising,
a base, and
an airfoil body that extends radially outward from the base relative to an axis to a tip of the airfoil body, the airfoil body having a leading edge, a trailing edge spaced apart axially from the leading edge, and a first side that extends between the leading edge and the trailing edge,
wherein the first side is formed to define a plurality of notches that extend into an external surface of the airfoil body, at least one of the plurality of notches extends to and opens into the trailing edge of the airfoil body, and each of the plurality of notches are spaced apart radially from a neighboring one of the plurality of notches between the base and the tip so that a weight of the airfoil is minimized while isolating radial separation of pressure surface boundary layer separation within each of the plurality of notches to allow airflow along the airfoil, wherein a depth of at least one of the plurality of notches extends a majority of the way into the airfoil body from the pressure side toward the suction side.
8. The airfoil of claim 7 , wherein each of the plurality of notches extend chordwise between the leading edge and the trailing edge of the airfoil body.
9. The airfoil of claim 7 , wherein each of the plurality of notches includes an inner surface and an outer surface spaced radially apart from the inner surface towards the tip of the airfoil, and the radial distance between the inner surface and the outer surface defines a height for each of the plurality of notches.
10. The airfoil of claim 9 , wherein the inner surface and the outer surface are planar.
11. The airfoil of claim 9 , wherein the plurality of notches includes a first notch having a first height and a second notch spaced radially apart from the first notch and having a second height equal to the first height, and a radial distance between the outer surface of the first notch and the inner surface of the second notch is less than the first height.
12. The airfoil of claim 9 , wherein the plurality of notches includes a first notch having a first height and a second notch spaced radially apart from the first notch and having a second height equal to the first height, and a radial distance between the outer surface of the first notch and the inner surface of the second notch is equal to the first height.
13. The airfoil of claim 9 , wherein the plurality of notches includes a first notch having a first height and a second notch spaced radially apart from the first notch and having a second height less than the first height.
14. The airfoil of claim 7 , wherein each of the plurality of notches is airfoil shaped when viewed radially inward.
15. The airfoil of claim 7 , wherein the plurality of notches includes a first notch having an inner surface, an outer surface radially spaced apart from the inner surface, and a radially extending support that extends between and interconnects the inner surface and the outer surface to define a first portion of the first notch located near the leading edge and a second portion of the notch located near the trailing edge, and the support provides a portion of the external surface of the first side.
16. A turbine wheel assembly adapted for use in a gas turbine engine, the turbine wheel assembly comprising,
a rotor hub configured to rotate about an axis, and
an airfoil coupled with the rotor hub and configured to rotate the rotor hub about the axis in response to gases acting on the airfoil during use of the turbine wheel assembly, the airfoil including a base coupled with the rotor hub and an airfoil body that extends radially outward from the base to a tip of the airfoil body, the airfoil body having a leading edge, a trailing edge spaced apart axially from the leading edge, a suction side that extends between the leading edge and the trailing edge, and a pressure side that extends between the leading edge and the trailing edge opposite the suction side,
wherein the pressure side of the airfoil is formed to define a plurality of notches that extend into an external surface of the airfoil, a depth of at least one of the plurality of notches extends a majority of the way into the airfoil body from the pressure side toward the suction side, and each of the plurality of notches are spaced apart radially from a neighboring one of the plurality of notches between the base and the tip so that a weight of the airfoil is minimized while isolating radial separation of pressure surface boundary layer separation within each of the plurality of notches to allow airflow along the airfoil.