# US 8,769,814 B2 · Device and method for repairing a forward frame V-blade in an aircraft engine

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- Number: US 8,769,814 B2
- Document ID: US8769814B2
- Status: Granted
- Kind: B2
- Application number: 12/828,836
- Filed: 2010-07-01
- Published: 2011-01-06
- Granted: 2014-07-08
- Earliest claimed: 2009-07-06
- Assignees: United Technologies Corporation
- Applicants: Brian Kenneth Holland; Michael J. Madel; William Bogue
- Inventors: Brian Kenneth Holland; Michael J. Madel; William Bogue
- Web page: https://patentgrep.com/patent/US8769814B2

## CPC

- F01D 5/005: {Repairing methods or devices}
- B23P 6/005: {using only replacement pieces of a particular form}
- F01D 5/141: {Shape, i.e. outer, aerodynamic form (F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147)}
- F05B 2260/301: Retaining bolts or nuts
- Y10T 29/49316: Impeller making
- Y10T 29/49318: Repairing or disassembling
- Y10T 29/4932: Turbomachine making
- Y10T 29/49321: Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
- Y10T 29/49721: with disassembling
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q)
- F05B: INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A repair device and method for repairing a forward frame v-blade on an aircraft engine are described in which the repair device replaces a section of the forward frame v-blade. In one embodiment, the repair device includes a supplemental part, which is secured to the forward frame v-blade. The supplemental part includes a central web and a pair of legs with a leg thickness that is greater than the thickness of corresponding flanges on the forward frame v-blade. Fasteners such as rivets are used to couple the supplemental part to the forward frame v-blade.

## Claims

### Claim 1

A repair device for a v-blade in a gas turbine engine on an aircraft, said repair device comprising:
a supplemental part comprising a central web and a first leg and a second leg projecting from and spaced apart by the central web to form a channel;
wherein the supplemental part has a first portion and a second portion with an outer dimension that is greater than the outer dimension of the first portion;
wherein the channel is wider in the first portion of the supplemental part than in the second portion of the supplemental part;
wherein the first portion has a first array of openings therethrough; and
wherein the second portion of the supplemental part has a second array of openings therethrough, and wherein a number of openings in the first array of openings is equal to a number of openings in the second array of openings.

### Claim 2 (depends on 1)

The repair device according to claim 1 wherein the first leg is thicker than the second leg in the first portion.

### Claim 3 (depends on 1)

The repair device according to claim 1 wherein the supplemental part comprises a plurality of pieces including a repair part, a splice plate, and fasteners securing the repair part to the splice plate.

### Claim 4 (depends on 3)

The repair device according to claim 3 wherein the splice plate only supports a portion of the repair part.

### Claim 5 (depends on 3)

The repair device according to claim 3, wherein the fasteners have a nominal body diameter, and wherein the fasteners are separated by a distance that is from about three to about twelve times the nominal body diameter.

### Claim 6 (depends on 5)

The repair device according to claim 5 wherein the fasteners comprise aircraft-grade rivets, and wherein the nominal body diameter is at least about 0.15 in.

### Claim 7 (depends on 1)

The repair device according to claim 1 wherein the first leg and the second leg are thicker in the first portion than the second portion.