Gas turbine engine with seal having protrusions

Patent metadata

Field	Value
Publication number	US-10301958-B2
Application number	US-201415021945-A
Country	US
Kind code	B2
Filing date	Aug 21, 2014
Priority date	Sep 17, 2013
Publication date	May 28, 2019
Grant date	May 28, 2019

Abstract

A gas turbine engine includes a turbine section. The turbine section includes a disk that is rotatable about an axis. A plurality of turbine blades are mounted around a periphery of the disk, and a plurality of seals are arranged between the turbine blades and the periphery of the disk. Each of the seals includes, with respect to the axis, a radially outer surface and a radially inner surface. The radially inner surface includes a plurality of protrusions.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a turbine section including:
a disk rotatable about an axis and including a periphery,
a plurality of turbine blades mounted around the periphery of the disk, and
a plurality of seals arranged between the plurality of turbine blades and the periphery of the disk, each of the plurality of seals including, with respect to the axis, a radially outer surface and a radially inner surface, the radially inner surface including a plurality of protrusions, wherein the plurality of protrusions are elongated ridges, and wherein the elongated ridges extend in an elongation direction that is obliquely angled to the axis.

2. The gas turbine engine as recited in claim 1 , wherein the radially outer surface is smooth.

3. The gas turbine engine as recited claim 1 , wherein the protrusions are chevron-shaped.

4. The gas turbine engine as recited in claim 1 , wherein the protrusions have a uniform height.

5. The gas turbine engine as recited in claim 1 , wherein the protrusions have a uniform height, H, and a pitch spacing, S, and a ratio of S/H is from 5 and 25.

6. The gas turbine engine as recited in claim 1 , wherein each of the plurality of seals includes at least one respective exit passage configured to allow flow across the seals.

7. The gas turbine engine as recited in claim 1 , wherein the protrusions have a height, H, and a channel height, CH, between the periphery of the disk and a base surface of the plurality of seals, and a ratio of H/CH is from 0.2 to 0.4.

8. The gas turbine engine as recited in claim 1 , further comprising a plurality of platform seals arranged radially outwards of the plurality of seals.

9. A seal for a gas turbine engine, the seal comprising:
a seal body configured to be arranged in a turbine section of a gas turbine engine between a periphery of a disk rotatable about an axis and a turbine blade mounted on the periphery of the rotatable disk, the seal body including forward and aft edges and first and second sides joining the forward and aft edges, the first side including a plurality of protrusions, wherein the plurality of protrusions are elongated ridges, and wherein the elongated ridges extend in an elongation direction that is obliquely angled to the axis.

10. The seal as recited in claim 9 , wherein the second side is smooth.

11. The seal as recited claim 9 , wherein the protrusions are chevron-shaped.

12. The seal as recited in claim 9 , wherein the protrusions have a uniform height.

13. The seal as recited in claim 9 , wherein the protrusions have a uniform height, H, and a pitch spacing, S, and a ratio of S/H is from 5 and 25.

14. The seal as recited in claim 9 , wherein each of the plurality of seals includes a through-hole between its respective radially inner surface and radially outer surface.

15. A method for facilitating thermal transfer in a gas turbine engine, the method comprising:
providing a turbine section that includes:
a disk rotatable about an axis and including a periphery,
a plurality of turbine blades mounted around the periphery of the disk, and
a plurality of seals arranged between the plurality of turbine blades and the periphery of the disk, each of the plurality of seals including a plurality of protrusions, the plurality of protrusions extending radially inward towards the axis;

providing a cooling fluid between the periphery of the disk and the plurality of seals; and turbulating the cooling fluid using the plurality of protrusions of the seals, wherein the plurality of protrusions are elongated ridges, and wherein the elongated ridges extend in an elongation direction that is obliquely angled to the axis.

16. A gas turbine engine comprising:
a turbine section including:
a disk rotatable about an axis and including a periphery,
a plurality of turbine blades mounted around the periphery of the disk, and
a plurality of seals arranged between the plurality of turbine blades and the periphery of the disk, each of the plurality of seals including, with respect to the axis, a radially outer surface and a radially inner surface, the radially inner surface including a plurality of protrusions, wherein the protrusions have a height, H, and a channel height, CH, between the periphery of the disk and a base surface of the plurality of seals, and a ratio of H/CH is from 0.2 to 0.4.

Assignees

• United Technologies Corp

Inventors

• Hough Matthew Andrew
• Corcoran Christopher
• Beattie Jeffrey S

Classifications

• F05D2250/183

  zigzag · CPC title

• F05D2260/22141

  using fins or ribs · CPC title

• F05D2250/182

  crenellated, notched · CPC title

• F05D2250/75

  given by its similarity to a letter, e.g. T-shaped · CPC title

• F05D2250/181

  ridged · CPC title