# US 8,769,817 B2 · Seal assembly retention method

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- Number: US 8,769,817 B2
- Document ID: US8769817B2
- Status: Granted
- Kind: B2
- Application number: 13/646,281
- Filed: 2012-10-05
- Published: 2013-02-28
- Granted: 2014-07-08
- Earliest claimed: 2007-10-09
- Assignees: United Technologies Corporation
- Applicants: Joseph W. Bridges, Jr.; Tracy A. Propheter-Hinckley
- Inventors: Joseph W. Bridges, Jr.; Tracy A. Propheter-Hinckley
- Web page: https://patentgrep.com/patent/US8769817B2

## CPC

- F16J 15/0887: {the sealing effect being obtained by elastic deformation of the packing}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 11/005: {Sealing means between non relatively rotating elements}
- F01D 11/008: {by spacer elements between the blades, e.g. independent interblade platforms}
- F02C 7/28: Arrangement of seals
- F05D 2240/80: Platforms for stationary or moving blades
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- Y10T 29/49297: Seal or packing making
- Y10T 29/49321: Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
- Y10T 29/49922: by bending over projecting prongs
- F16J: PISTONS {(specially adapted for dampers F16F9/32)}; CYLINDERS; SEALINGS
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A seal assembly includes a body having two circumferential sides, a leading end, and a trailing end. At least one of the circumferential sides includes a first channel sidewall, a second channel sidewall, and a channel bottom wall that together define a seal channel for receiving a seal. The seal channel includes a slot that cooperates with a tab on the seal to facilitate securing the seal within the seal channel.

## Claims

### Claim 1

A method of assembling a seal and a seal channel of a gas turbine engine component, comprising:
providing the gas turbine engine component such that the gas turbine engine component includes the seal channel;
wherein the seal channel includes an open top, a first sidewall, a second sidewall, a bottom wall, and a slot that extends through the bottom wall;
compressing a resilient non-planar tab and inserting the resilient non-planar tab into the slot and through the bottom wall of the seal channel until the resilient non-planar tab decompresses and a portion of the tab is in contact with at least one of the first sidewall, the second sidewall, and the bottom wall such that the contact retains the seal within the seal channel and limits movement between the seal and the seal channel.

### Claim 2 (depends on 1)

The method as recited in claim 1, wherein the deformed tab has an acute angle.

### Claim 3 (depends on 1)

The method as recited in claim 1, wherein the tab is substantially rectangular in shape.

### Claim 4 (depends on 1)

The method as recited in claim 1, wherein the tab extends substantially perpendicularly from the seal.

### Claim 5 (depends on 1)

The method as recited in claim 1, wherein the slot extends partially through at least one of the first sidewall and the second sidewall.