Rotor blade for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10808539-B2
Application number	US-201615218376-A
Country	US
Kind code	B2
Filing date	Jul 25, 2016
Priority date	Jul 25, 2016
Publication date	Oct 20, 2020
Grant date	Oct 20, 2020

Abstract

A rotor blade for a gas turbine engine includes a blade extending from a root and a contoured tip portion at a first end of the blade. The first end is opposite the root. The contoured tip portion includes a first sloped region and a second sloped region. The second sloped region is steeper than the first sloped region, relative to a platform.

First claim

The invention claimed is:

1. A rotor for a gas turbine engine comprising:
a blade extending from a root;
a contoured tip portion at a first end of the blade, the first end being opposite the rub event;
wherein the contoured tip portion includes a first sloped region and a second sloped region, wherein the second sloped region is steeper than the first sloped region, relative to a platform, wherein the first sloped region is a radially outward facing surface having a constant slope, the contoured tip portion includes an interference zone extending from a radially outward tip of the contoured tip portion to a radially innermost position along the second-sloped region, the interference zone being at least an expected maximum interference of the blade during the rub event.

2. The rotor of claim 1 , wherein the second sloped region is downstream of the first sloped region, relative to an expected fluid flow across the blade in an installed position.

3. The rotor of claim 1 , further comprising a third sloped region downstream of the second sloped region.

4. The rotor of claim 3 , wherein the third sloped region has a slope, relative to the platform, equal to a slope of the first sloped region.

5. The rotor of claim 3 , wherein the second sloped region is steeper than the first sloped region and the third sloped region.

6. The rotor of claim 5 , wherein the third sloped region is steeper than the first sloped region.

7. The rotor of claim 3 , wherein the third sloped region is at least partially within the interference zone.

8. The rotor of claim 3 , wherein the third sloped region is outside of the interference zone.

9. A gas turbine engine comprising:
a compressor section;
a combustor section connected to the compressor section by a primary flowpath;
a turbine section connected to the combustor section by the primary flowpath;
a plurality of rotors arranged circumferentially about an engine centerline, at least one of the rotors including a platform, a root extending radially inward from the platform, and a blade extending radially outward and at least partially spanning the primary flowpath;
at least one shroud component radially outward of the plurality of rotors, the at least one shroud being abradable relative to the blade;
the blade including a contoured tip portion configured to interfere with said at least one shroud during a rub event, and the contoured tip portion including an interference zone and a first region and a second region, the interference zone extending from a radially outward tip of the blade to a radially innermost position along the second region, and the interference zone being at least an expected maximum interference between the blade and the at least one shroud during the rub event; and
a slope of the first region being approximately equal to a slope of the shroud relative to the engine centerline and the second region downstream of the first region has a steeper slope, relative to the engine centerline, and wherein the first region has a constant slope.

10. The gas turbine engine of claim 9 , wherein the at least one shroud comprises a sculpted pocket radially outward of the tip portion, the sculpted pocket including a rear facing flowpath step at a forward edge, and a forward facing flowpath turn at an aft edge, wherein the forward facing flowpath turn is less than ninety degrees.

11. The gas turbine engine of claim 9 , wherein the tip portion of the blade includes a third sloped region downstream of the second region.

12. The gas turbine engine of claim 11 , wherein the third sloped region has a shallower slope, relative to the engine centerline, than the second region.

13. The gas turbine engine of claim 12 , wherein the third sloped region has the same slope as the first region, relative to the engine centerline.

14. The gas turbine engine of claim 9 , wherein the at least one shroud includes a sculpted pocket radially outward of the blade, and wherein the sculpted pocket defines a rear facing flowpath step at a forward edge of the sculpted pocket, and a forward facing flowpath bend at a rear edge of the flowpath pocket, and wherein the forward facing flowpath bend induces a flowpath turn of less than 90 degrees.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Narrow Taryn
• Bintz Matthew E
• Sorensen Lucas D
• Monahan Daniel J
• Roberts Steven D
• Wall Jordan T
• Dong Yuan
• Brilliant Lisa I
• Murphy Andrew J

Classifications

• F01D11/122 Primary

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• F05D2250/192

  bevelled · CPC title

• F05D2250/314

  the axes being inclined in relation to each other · CPC title

• F04D29/526

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title