Turbofan flow path trenches
An integrally bladed disk includes a rim and blades. The blades are circumferentially spaced and extend integrally outward from the rim to define a flow path therebetween. The periphery of the rim forms a flow surface and includes a trench that is disposed adjacent the blades.
1. An integrally bladed disk, comprising:
a rotor disk having a rim the periphery of which forms a flow surface; and
circumferentially spaced blades extending integrally outward from the rim to define a flow path therebetween, wherein a base of each of the blades has a fillet;
wherein the rim includes a plurality of trenches that are disposed adjacent and between the blades along the flow surface, wherein a deepest point of one of the trenches circumferentially aligns with a location of highest stress concentration at a leading edge of the fillet.
2. The integrally bladed disk of claim 1 , wherein the trench extends axially forward and rearward of a leading edge of the blades.
3. The integrally bladed disk of claim 1 , wherein the trench extends axially to a trailing edge of the blades.
4. The integrally bladed disk of claim 1 , wherein the trench has a depth of between 0.005 inch (0.127 mm) and 0.060 inch (1.52 mm).
5. The integrally bladed disk of claim 1 , wherein the trench extends into at least one fillet.
6. The integrally bladed disk of claim 1 , wherein the blades have at least one trench disposed therebetween.
7. The integrally bladed disk of claim 1 , wherein the trench has a radius with a smooth transition from the deepest point of the trench to a radius of one of the fillet or the flow surface.
8. A gas turbine engine having a stress relief feature, the engine comprising:
an integral rotary body having a plurality of blades extending from a peripheral rim thereof, the peripheral rim having a plurality of depressions that are disposed adjacent and between the plurality of blades, wherein a base of the blade has a fillet and a deepest point of one of the depressions circumferentially aligns with a location of highest stress concentration at a leading edge of the fillet, and wherein the one depression extends into the fillet in at least one location along the base of the blade.
9. The gas turbine engine of claim 8 , wherein the depression extends axially forward and rearward of a leading edge of the blade.
10. The gas turbine engine of claim 8 , wherein the depression extends axially to a trailing edge of the blade.
11. The gas turbine engine of claim 8 , wherein the depression has a depth of between 0.005 inch (0.127 mm) and 0.060 inch (1.52 mm).
12. The gas turbine engine of claim 8 , wherein the blade comprises a plurality of blades and at least one depression is disposed between the blades.
13. The gas turbine engine of claim 8 , wherein the depression has a radius with a smooth transition from the deepest point of the trench to a radius of the fillet.
14. A stress relief feature for an integral rotary body having a plurality of blades extending from a peripheral rim, the feature comprising:
a plurality of depressions are disposed in the peripheral rim of the integral rotary body between the plurality of blades, a deepest portion of one of the depressions is circumferentially aligned with a location of highest stress concentration at a leading edge of a fillet of the blade.
15. The stress relief feature of claim 14 , wherein the depression is disposed between two blades and extends axially forward and rearward of a leading edge of the two blades.
16. The stress relief feature of claim 14 , wherein the depression has a depth of between 0.005 inch (0.127 mm) and 0.060 inch (1.52 mm).
17. The stress relief feature of claim 14 , wherein the depression extends into the fillet.
18. The stress relief feature of claim 14 , wherein the depression has a radius with a smooth transition from the deepest point of the trench to a radius of one of the fillet or a flow surface of the peripheral rim.