TURBOFAN FLOW PATH TRENCHES

• US 20110064580A1
• Filed: 09/16/2009
• Published: 03/17/2011
• Est. Priority Date: 09/16/2009
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Yilmaz, Cagdas, Barnes, Roland R.
• Granted Patent: US 8,403,645 B2
• Time in Patent Office: Days
• US Class Current: 416/204.A
• CPC Class Codes: F01D 5/143 Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
• CPC Class Codes: F01D 5/145 Means for influencing boundary layers or secondary circulations for compressors F04D29/68
• CPC Class Codes: F01D 5/34 Rotor-blade aggregates of unitary construction , e.g. formed of sheet laminae; discs formed of sheet laminae F01D5/028; ceramic materials F01D5/284, composite materials F01D5/282
• CPC Class Codes: F05D 2230/53 by integrally manufacturing a component, e.g. by milling from a billet or one piece construction
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

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.

Claims

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 the rim includes a trench that is disposed adjacent the blades along the flow surface.

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 about a trailing edge of the blades.

4. The integrally bladed disk of claim 1, wherein the trench has a depth of between about 0.005 inch (0.127 mm) and 0.060 inch (1.52 mm).

5. The integrally bladed disk of claim 1, wherein a base of each of the blades has a fillet.

6. The integrally bladed disk of claim 5, wherein a deepest point of the trench circumferentially aligns with a location of highest stress concentration at a leading edge of the fillet.

7. The integrally bladed disk of claim 5, wherein the trench extends into at least one fillet.

8. The integrally bladed disk of claim 1, wherein the blades comprise a row and at least one trench is disposed between the blades in the row.

9. The integrally bladed disk of claim 1, wherein the blades comprise a row and a plurality of trenches are disposed between each of the blades in the row.

10. A gas turbine engine having a stress relief feature, the engine comprising:

an integral rotary body having a blade extending from a peripheral rim thereof, the peripheral rim having a depression that is disposed adjacent the blade.

11. The gas turbine engine of claim 10, wherein the depression extends axially forward and rearward of a leading edge of the blade.

12. The gas turbine engine of claim 10, wherein the depression extends axially to about a trailing edge of the blade.

13. The gas turbine engine of claim 10, wherein the depression has a depth of between about 0.005 inch (0.127 mm) and 0.060 inch (1.52 mm).

14. The gas turbine engine of claim 10, wherein a base of the blade has a fillet and a deepest point of the depression circumferentially aligns with a location of highest stress concentration at a leading edge of the fillet.

15. The gas turbine engine of claim 14, wherein the depression extends into at least one fillet.

16. The gas turbine engine of claim 10, wherein the blade is one of a row of blades and at least one depression is disposed between the blades in the row.

17. The gas turbine engine of claim 10, wherein the blade is one of a row of blades and a plurality of depressions are disposed between the blades in the row.

18. A stress relief feature for a integral rotary body having a blade extending from a peripheral rim, the feature comprising:

a depression in the peripheral rim, a deepest portion of the depression is circumferentially aligned with a location of highest stress concentration at a leading edge of a fillet of the blade.

19. The stress relief feature of claim 18, wherein the depression is disposed between two blades and extends axially forward and rearward of a leading edge of the two blades.

20. The stress relief feature of claim 18, wherein the depression has a depth of between about 0.005 inch (0.127 mm) and 0.060 inch (1.52 mm).