BOAS retention assembly with interlocking ring structures

Patent metadata

Field	Value
Publication number	US-11085332-B2
Application number	US-201916249303-A
Country	US
Kind code	B2
Filing date	Jan 16, 2019
Priority date	Jan 16, 2019
Publication date	Aug 10, 2021
Grant date	Aug 10, 2021

Abstract

A blade outer air seal retention assembly may comprise a forward retention ring and an aft retention ring coupled to the forward retention ring. The forward retention ring may comprise a first shiplap flange extending aft from the forward retention ring. The aft retention ring may comprise a second shiplap flange extending forward from the aft retention ring.

First claim

What is claimed is:

1. A retention ring for a blade outer air seal retention assembly, comprising:
a radially extending wall;
an axially extending rail located at an outer circumference of the radially extending wall; and
a first shiplap flange extending axially from a surface of the radially extending wall, the first shiplap flange comprising:
a first surface located a first axial length from the surface of the radially extending wall;
a recessed surface located radially inward of the first surface, wherein the recessed surface is located a second axial length from the surface of the radially extending wall, the second axial length being less than the first axial length;
a first protrusion located at a radially outward surface of the first shiplap flange, wherein the first protrusion is located at a first circumferential end of the first shiplap flange; and
a second protrusion located at a radially inward surface of the first shiplap flange, the second protrusion being located at a second circumferential end of the first shiplap flange opposite the first circumferential end, wherein a circumferential distance between the first protrusion and the second protrusion is equal to a circumferential length of the recessed surface.

2. The retention ring claim 1 , further comprising a plurality of circumferentially spaced shiplap flanges, the plurality of circumferentially spaced shiplap flanges including the first shiplap flange.

3. The retention ring of claim 2 , wherein the radially extending wall extends continuously about a center axis of the retention ring.

4. A blade outer air seal retention assembly, comprising
a forward retention ring comprising:
a first wall, and
a first shiplap flange extending aft from a first surface of the first wall, wherein the first shiplap flange comprises a first radially outward protrusion and a first radially inward protrusion; and

an aft retention ring coupled to the forward retention ring, the aft retention ring comprising:
a second wall, and
a second shiplap flange extending forward from a second surface of the second wall, wherein the second shiplap flange comprises a second radially outward protrusion and a second radially inward protrusion, and wherein the first radially outward protrusion of the first shiplap flange engages the second radially inward protrusion of the second shiplap flange, and wherein the first radially inward protrusion of the first shiplap flange engages the second radially outward protrusion of the second shiplap flange.

5. The blade outer air seal retention assembly of claim 4 , wherein the first shiplap flange and the second shiplap flange define a ring orifice.

6. The blade outer air seal retention assembly of claim 5 , wherein a first axial width of the ring orifice is greater than a second axial width of the ring orifice, the first axial width extending from a first recessed surface of the first shiplap flange to a second recessed surface of the second shiplap flange, the second axial width extending from an aft-facing first surface of the first shiplap flange to a forward-facing first surface of the second shiplap flange.

7. A turbine section of a gas turbine engine, comprising:
a blade outer air seal comprising a first blade outer air seal segment; and
a blade outer air seal retention assembly coupled to the blade outer air seal, the blade outer air seal retention assembly comprising:
a forward retention ring including a first shiplap flange extending aft from a radially extending wall of the forward retention ring, and
an aft retention ring coupled to the forward retention ring, the aft retention ring including a second shiplap flange extending forward from a radially extending wall of the aft retention ring, wherein the first shiplap flange and the second shiplap flange are located in a retention ring channel defined by the first blade outer air seal segment.

8. The turbine section of claim 7 , wherein the blade outer air seal comprises a plurality of blade outer air seal segments arranged in circumferential series around an engine central longitudinal axis, the plurality of blade outer air seal segments including the first blade outer air seal segment, and wherein the forward retention ring comprises a plurality of forward ring shiplap flanges extending aft from the radially extending wall of the forward retention ring, the plurality of forward ring shiplap flanges including the first shiplap flange, and wherein at least one forward ring shiplap flange of the plurality of forward ring shiplap flanges is located within each blade outer air seal segment of the plurality of blade outer air seal segments.

9. The turbine section of claim 7 , further comprising a turbine case structure located radially outward of the blade outer air seal and the blade outer air seal retention assembly, wherein the blade outer air seal retention assembly couples the blade outer air seal to the turbine case structure.

10. The turbine section of claim 9 , wherein the first blade outer air seal segment comprises a radially outward portion and a radially inward portion, and wherein the retention ring channel is defined by the radially outward portion and the radially inward portion of the first blade outer air seal segment.

11. The turbine section of claim 10 , wherein the turbine case structure comprises a central flange, and wherein the central flange is located through a case orifice defined by the radially outward portion of the first blade outer air seal segment.

12. The turbine section of claim 11 , wherein the first shiplap flange and the second shiplap flange define a ring orifice, and wherein the central flange is located in the ring orifice.

13. The turbine section of claim 12 , wherein the central flange defines a groove, and wherein a first portion of the first shiplap flange and a second portion of the second shiplap flange are located in the groove.

14. The turbine section of claim 12 , wherein the first shiplap flange comprises a first radially outward protrusion and a first radially inward protrusion, and wherein the second shiplap flange comprises a second radially outward protrusion and a second radially inward protrusion, and wherein the first radially outward protrusion of the first shiplap flange engages the second radially inward protrusion of the second shiplap flange, and wherein the first radially inward protrusion of the first shiplap flange engages the second radially outward protrusion of the second shiplap flange.

15. The turbine section of claim 14 , wherein the central flange is located circumferentially between the first radially outward protrusion and the second radially outward protrusion and circumferentially between the first radially inward protrusion and the second radially inward protrusion.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Clark Thomas E
• Johnson Dean W

Classifications

• F02K3/04

  the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F01D11/08

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