Boas having radially extended protrusions

Patent metadata

Field	Value
Publication number	US-10557366-B2
Application number	US-201815863152-A
Country	US
Kind code	B2
Filing date	Jan 5, 2018
Priority date	Jan 5, 2018
Publication date	Feb 11, 2020
Grant date	Feb 11, 2020

Abstract

A blade outer air seal may comprise an arcuate segment. The arcuate segment may comprise an aft wall having a first radially extending protrusion at a circumferential end of the aft wall. A first hook may extend aft from the aft wall. A first gusset may extend from the first radially extending protrusion. A radial height of the first radially extending protrusion may be greater than a radial height of a second radially extending protrusion of the aft wall.

First claim

The invention claimed is:

1. A blade outer air seal, comprising:
a plurality of arcuate segments, wherein a first arcuate segment of the plurality of arcuate segments comprises:
a first wall located at an aft end of the first arcuate segment, the first wall comprising a first radially extending protrusion located at a first circumferential end of the first wall, a second radially extending protrusion located at a second circumferential end of the first wall opposite the first circumferential end, and a plurality of third radially extending protrusions disposed between the first radially extending protrusion and the second radially extending protrusion, wherein a radial height of the first radially extending protrusion and the second radially extending protrusion as measured from a radially inward surface of the first arcuate segment is greater than a radial height of the third radially extending protrusions as measured from the radially inward surface of the first arcuate segment;
a first hook extending aft from the first wall, wherein a radially outward surface of the first hook is radially inward of a midpoint of the first wall, the midpoint of the first wall being located halfway between the radially inward surface of the first arcuate segment and a radially outward surface of the third radially extending protrusions; and
a first gusset extending from the first radially extending protrusion.

2. The blade outer air seal of claim 1 , wherein a radial height of the first gusset as measured from the radially inward surface of the first arcuate segment is between 50% and 70% of the radial height of the first radially extending protrusion as measured from the radially inward surface of the first arcuate segment.

3. The blade outer air seal of claim 1 , wherein a circumferential width of the first gusset is between 20% and 40% of a circumferential width of the first radially extending protrusion.

4. The blade outer air seal of claim 1 , wherein the first arcuate segment further comprises:
a second wall located at a forward end of the first arcuate segment; and
a second hook extending from the second wall.

5. The blade outer air seal of claim 4 , wherein the first arcuate segment further comprises a feather seal slot defined, at least partially, by the first wall, the second wall, and a circumferential surface extending between the first wall and the second wall.

6. The blade outer air seal of claim 5 , wherein a second arcuate segment of the plurality of arcuate segments is disposed circumferentially adjacent to the first arcuate segment, and wherein an aft wall of the second arcuate segment comprises a fourth radially extending protrusion located at a circumferential end of the aft wall of the second arcuate segment, and wherein the fourth radially extending protrusion is circumferentially adjacent to the first radially extending protrusion.

7. The blade outer air seal of the claim 6 , further comprising a feather seal disposed between the first arcuate segment and the second arcuate segment.

8. A gas turbine engine, comprising:
an engine casing structure; and
a turbine disposed radially inward of the engine casing structure, the turbine comprising:
a blade configured to rotate about a central longitudinal axis of the gas turbine engine, and
a blade outer air seal disposed radially outward of the blade, the blade outer air seal comprising an arcuate segment, wherein a first radial distance between the engine casing structure and a first protrusion extending from an aft wall of the arcuate segment is less than a second radial distance between the engine casing structure and a second protrusion extending from the aft wall, wherein the arcuate segment includes a hook extending from the aft wall of the arcuate segment, and wherein a radially outward surface of the hook is radially inward of a midpoint of the aft wall of the arcuate segment, the midpoint being located halfway between a radially inward surface of the arcuate segment and a radially outward surface of the second protrusion.

9. The gas turbine engine of claim 8 , wherein the first protrusion is located proximate a circumferential end of the arcuate segment.

10. The gas turbine engine of claim 8 , wherein the blade outer air seal further comprises a gusset extending from the aft wall.

11. The gas turbine engine of claim 10 , wherein a radial height of the gusset as measured from the radially inward surface of the arcuate segment is between 50% and 70% of a radial height of the first protrusion as measured from the radially inward surface of the arcuate segment.

12. A turbine for a gas turbine engine, comprising:
a blade;
a blade outer air seal disposed radially outward of the blade, the blade outer air seal comprising an arcuate segment, the arcuate segment including:
an aft wall comprising a first radially extending protrusion and a second radially extending protrusion, the first radially extending protrusion being located proximate a circumferential end of the aft wall, and
an aft hook extending aft from the aft wall, wherein a radially outward surface of the aft hook is radially inward of a midpoint of the aft wall, the midpoint of the aft wall being located halfway between a radially inward surface of the arcuate segment and a radially outward surface of the second radially extending protrusion; and

a turbine case disposed around the blade outer air seal, the turbine case comprising a case hook, wherein a first radial distance between the case hook and the first radially extending protrusion is less than a second radial distance between the case hook and the second radially extending protrusion.

13. The turbine of claim 12 , wherein the blade outer air seal further comprises a gusset extending from the first radially extending protrusion.

Assignees

• United Technologies Corp

Inventors

• Ciamarra Christina G
• Barainca Brian
• Dabbs Thurman Carlo

Classifications

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D5/12

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title